Thermoplastic composites（TPCs）have exhibited immense potential in aerospace applications, attributed to their exceptional toughness, weldability, recyclability, and efficient processing cycles. However, the manufacturing of complex structures is hindered by the high melting points and viscosities of their constituent resins. Resistance welding, leveraging Joule heating to induce interfacial melting and bonding, emerges as a viable alternative to mechanical fastening and adhesive bonding. This review delves into the fundamental principles underlying resistance welding, strategies for optimizing key process parameters, recent advancements in heating elements, and large-scale welding techniques, such as sequential and continuous resistance welding. The findings indicate that optimizing process parameters and improving heating elements can significantly enhance joint strength. To achieve engineering application of resistance welding technology, further research should be focused on process stability, reliability of welded joints, large-scale welding, and other issues.

As a critical strategic material for aero-engines and industrial gas turbines, the composition/process design, optimization and process control of superalloys remain at the core of industry concerns. The present work focuses on addressing practical challenges in the development and production of superalloys and their components. It identifies key influencing factors in typical processes within the manufacturing workflow and employs a combination of advanced characterization techniques such as synchrotron radiation and high-throughput experimental methods. This integrated approach enables the design and optimization of critical process parameters for superalloy manufacturing, thereby providing foundational support for enhancing process technology, product performance, research and development efficiency, and reducing costs. Taking representative manufacturing processes involving liquid-solid and solid-solid phase transformations as examples, we explore precision tailoring strategies and validation methods for key stages including master alloy melting/remelting, synergistic particle size/morphology control in gas atomization, shrinkage porosity control during casting solidification, powder storage/desorption treatments, powder consolidation through hot isostatic pressing（HIP） and heat treatment procedures. In addition, optimal usage conditions are investigated for auxiliary materials or consumables integral to superalloy production, particularly ceramics, isothermal forging dies and brazing repair materials. Notably, the research on process tailoring reveals significant phenomena: （1）the impact of oxygen existence forms in cast and powder metallurgy alloys; （2）the influence of the initial microstructural state of alloys on the phase transformation temperature during HIP consolidation and heat treatment; （3）the formation and control of abnormal phases and defects in cast, powder metallurgy and additive manufacturing alloys, along with repair materials for brazing and ceramic refractories. The aforementioned findings establish a theoretical foundation for optimizing and tailoring superalloy process parameters and achieving precise manufacturing control, while also providing feasible technical pathways for industrial implementation.

The machine learning technology has broad prospects in the field of aerospace materials and plays an important role in material selection, design, and optimization. Firstly, a brief discussion was made on the advantages and potential of machine learning technology in the aerospace field, outlining the technological developments, algorithm categories, features, and limitations. The conventional or potential applications of machine learning in scientific exploration, especially in complex material data formats, are introduced. Secondly, the research status of machine learning in aviation materials is mainly focused on, discussing the recent progress in utilizing machine learning to assist in the research of high-temperature alloy materials, high-strength structural materials, thermal protection coating materials, as well as functional and smart materials. The strategies and methods of machine learning-driven aviation material research are elucidated. Finally, the challenges encountered in machine learning-assisted aerospace material research and development are examined. Facilitating the transformation of aerospace material research towards the fourth paradigm of data-driven materials science necessitates efforts in promoting the open sharing of data resources, integrating domain knowledge and physical laws more deeply into machine learning models, and ensuring feature consistency across different data types.

With advancements in material technology, a surge in research and development has been witnessed for various high-performance materials, including metamaterials, each possessing unique functionalities. However, meeting the demands of high performance has rendered the application of a single material insufficient for achieving the required interface mechanical and functional integration properties. Functionally gradient composite materials have emerged as a pivotal breakthrough to address this issue. This paper introduces the application background, as well as the research and application status of functionally gradient composite materials in foreign countries. Furthermore, based on the prevalent issues in the domestic engineering field concerning functionally gradient composite materials, the challenges faced in their utilization are highlighted. When compared to international advanced levels, the development of functionally gradient composite materials in China encounters three major hurdles. Firstly, the preparation process remains relatively underdeveloped, impeding large-scale engineering applications. Secondly, due to the scarcity of performance evaluation methods, there is an urgent necessity to establish a coupled functional evaluation system. Thirdly, there is a scarcity of proprietary intellectual property rights pertaining to material design and simulation methods, coupled with the absence of a comprehensive database. Consequently, material design still largely relies on the experience of designers. Lastly, suggestions for the future application and development of functionally gradient composite materials are proposed.

Poly（aryl ether ketone）（PAEK） thermoplastic composites exhibit exceptional impact resistance and possess significant application potential in the aerospace industry. To address mechanical performance limitations of PAEK composites fabricated through automated in-situ placement, this study systematically investigates the impacts of post-processing parameters-including temperature, pressure and time-on pore elimination and mechanical properties. Utilizing the automated fiber placement, PAEK prepregs are processed into laminates. A viscosity-pressure-time coupling model is formulated through differential scanning calorimetry（DSC）, rheological assessments and mechanical characterizations. The results demonstrate the model predicts reasonably pore elimination across varying process parameters and the critical post-processing temperature is identified as 340 ℃. The pore elimination is facilitated rapidly due to low and stable resin viscosity at 340-360 ℃. The post-processing pressure significantly influences pore removal efficiency, with a critical pressure of 0.7 MPa at 360 ℃ and requiring 60 min for complete pore elimination. Higher pressures lead to only marginal performance enhancements. The time dependency of material performance depends on pressure: at 0.7 MPa and 360 ℃, full pore elimination is achieved within 60 min, whereas at 1.6 MPa, the required time is reduced to 20 min. At 0.7 MPa, 360 ℃ and 60 min, the tensile strength, flexural strength and interlaminar shear strength are 2844, 1653 MPa and 103 MPa, respectively.

This article provides an overview of the latest research status and application prospects of titanium/titanium alloy composite materials, highlighting their advantages in high specific strength, lightweight properties, thermal stability, and wear resistance, which position them as crucial materials in high-tech sectors such as aerospace, military equipment, and medicine. It summarizes research outcomes demonstrating the steady enhancement of mechanical properties, wear resistance, and thermal stability of titanium matrix composites through the addition of reinforcing phases. The review also reveals advancements in various processing technologies that have improved the grain structure and performance of these composites, while pointing out that challenges persist regarding the stability of these materials under high temperature and pressure conditions, as well as the bonding strength at interfaces. These issues necessitate the optimization of reinforcement distribution, bonding methods, and the exploration of novel composite systems. Furthermore, the combination of surface nanotechnology with digital simulation offers new avenues for optimizing the properties of titanium-based composites. Interface reinforcement and thermal stability research are identified as pivotal for future developments. Ultimately, the essay underscores that the enhancement of titanium-based composite properties and innovations in processing technologies are central to realizing their extensive application in extreme environments. This dual focus also constitutes the direction for pushing the boundaries of composite material performance even further.

High-performance thermoplastic resin-based composites have shown broad application prospects in the aviation manufacturing technology due to their excellent mechanical properties, environmental resistance, chemical resistance, recyclability, and rapid molding. In recent years, with the accelerated commercialization of high-performance thermoplastic resins such as polyphenylene sulfide（PPS）, polyetherimide（PEI）, and polyaryletherketone（PAEK）, the related prepregs and molding technologies have been continuously optimized, promoting the industrial application of such materials. This paper systematically reviews the current development status of high-performance thermoplastic resin-based composites, focusing on their material systems and commercialization progress, prepreg preparation, advanced manufacturing technology and application. It proposes key development directions for high-performance thermoplastic resin matrix composites, in order to provide reference for personnel in engineering and technical fields such as aerospace, and promote the innovative development and application of high-performance thermoplastic resin matrix composites.

The application of advanced composite materials in aeroengines has become one of the key technologies for improving engine performance, reducing mass and enhancing fuel efficiency. This article reviews the current status and development of advanced composite materials in foreign aero-turbofan engines, with a focus on the application of polymer composite PMC materials such as epoxy resin and polyimide, metal matrix composite MMC materials such as titanium alloy and aluminum alloy, and ceramic matrix composite (CMC) such as silicon carbide and aluminum oxide in engine components such as fan casings, low-pressure compressors, high-pressure compressors, high-pressure turbines, low-pressure turbines and nozzles. By analyzing the application and research and development progress of foreign aircraft engines in matrix, metal matrix and ceramic matrix composite, this paper explores their advantages in improving thrust to mass ratio and temperature resistance performance. At the same time, this article also looks forward to the future development direction of various composite materials in aeroengines, including the research and development of new composite materials, optimization of manufacturing processes, and potential applications and development trends of various composite materials in future aeroengines.

High-temperature high-entropy alloys（HEAs）show potential to surpass traditional Ni-based alloys through multi-principal element synergy and microstructural regulation. This review systematically examines three systems: high-entropy superalloys（HESAs）, refractory HEAs（RHEAs） and refractory high-entropy superalloys（RSAs）. HESAs emulate the γ/γ′ dual-phase structure of Ni-based alloys, achieving comparable strength at 800-1000 ℃. RHEAs utilize refractory elements to form high-melting-point solid solutions with superior performance above 1200 ℃. RSAs innovate with BCC/B2 nanobasket structures, outperforming Ni-based alloys across 25-1200 ℃. Current challenges include poor room-temperature ductility, oxidation resistance and phase stability, demanding breakthroughs in multi-scale microstructure control, dynamic phase transformation mechanisms and high-throughput design. Future directions prioritize multi-objective composition optimization, advanced processing, cross-scale characterization, and service-condition evaluation systems to guide extreme-environment applications like aeroengine components and nuclear reactors, etc.

Carbon fiber reinforced thermoplastic composite（CFRTP） is increasingly utilized in aerospace and automotive manufacturing sectors owing to its exceptional specific strength, strong toughness, and weldability. Induction welding stands as a pivotal method for fabricating typical CFRTP components. However, the intricate interplay of magnetic, thermal, and stress coupling during the induction welding process, along with its evolution and distribution characteristics, remains unclear, significantly impeding the cost-effective, efficient, and high-quality production of CFRTP components. In this study, a magnetic-thermal-mechanical coupling simulation model is developed for the induction welding of CFRTP stringer skin structures. This model is employed to investigate the distribution and evolution patterns of the magnetic field, temperature field, and residual stress field. The results show that under the influence of an alternating electromagnetic field, the magnetic field strength peaked at 1.45 mT in the component’s edge region. Notably, the simulated magnetic, temperature, and stress field all exhibit significant edge effects, which are intimately tied to the skin effect induced by high-frequency eddy currents. During welding, asymmetric and nearly elliptical high-temperature zones emerge on both sides of the skin’s bottom, with temperatures in proximity to the stringer area notably higher than those farther away. When the current frequency increases from 150 kHz to 250 kHz, the maximum stress of the induction joint increases from 637 MPa to 778 MPa, and the asymmetric stress concentration area at the welding interface expands accordingly. The measured temperature field and stress results are in high agreement with the simulation outcomes, effectively validating the model’s accuracy and applicability. This study offers theoretical backing for process optimization and quality control in the induction welding of intricate CFRTP components.

IN718 superalloy is extensively utilized in the aerospace and nuclear industries due to its outstanding oxidation resistance, heat-corrosion resistance, good structural stability, fatigue performance and safety reliability. It is one of irreplaceable materials for the hot-end components of next-generation advanced aircraft engines. Recently, laser powder bed fusion（LPBF） technology has developed as an innovative rapid prototyping technique, transcending the limitations of traditional shaping methods and structural designs. This technology has realized one-step laser near-net shaping of complex thin-walled structures, demonstrating substantial application potential. However, during the laser additive manufacturing process, the thin-walled surfaces are exposed to high laser input energy, which can readily induce warping, deformation, and even cracking, significantly impacting the service performance of these structures. To address these challenges, this work provides an overview of the working principle and recent advancements in LPBF technologies. It systematically analyses the multi-scale microstructural evolution and precipitation phase behavior of IN718 superalloy thin wall fabricated by LPBF. Special emphasis is placed on the initiation, propagation mechanisms and mitigation strategies for metallurgical defects, including optimized thin-walled structural designs, laser forming process parameters and alloy composition. In addition, the strengthening mechanisms underlying the mechanical properties of IN718 superalloy thin wall at both room and high temperatures are analyzed and discussed. Finally, the work summarizes the existing challenges such as insufficient critical performance under harsh conditions and future development directions of superalloy thin wall fabricated by LPBF, including establishment of laser forming process databases specialized for superalloy thin wall, investigation of solidification defect formation and novel control strategies in superalloy thin wall fabricated by LPBF, and optimization of the chemical composition design for high-performance superalloy thin-walled components.

The resistance welding process of 7075 aluminum alloy（7075AA） and carbon fiber reinforced polyether ether ketone（CF/PEEK） is optimized through the activation of the aluminum alloy surface and its subsequent integration with a thermoplastic layer. A microgroove network is fabricated on the aluminum alloy surface using laser treatment, which notably augmented the mechanical coupling with the polyetherimide（PEI） thermoplastic layer. In contrast, the bonding effectiveness of sandblasted and untreated samples are inferior. Surface analysis conducted via Fourier transform infrared spectroscopy（FT-IR） and X-ray photoelectron spectroscopy（XPS） reveal the formation of Al—O—Si bonds and a silane coupling film transition layer, both of which fortified the interface. In the resistance welded joints, incomplete bonding between the sandblasted/laser-etched aluminum alloy and the PEI layer lead to debonding of the thermoplastic layer, which emerge as the predominant failure mode. The single lap shear strength（LSS） of the sandblasted joint is 10.47 MPa, whereas the LSS of the laser-etched joint attains 15.35 MPa. Following silane treatment, the bonding of the PEI thermoplastic layer is markedly enhanced, resulting in an LSS of 19.03 MPa for the laser-etched and silane-treated joint—a 23.97% increase compared to simple laser etching. At this juncture, the cross-section of the joint exhibites characteristics indicative of heating element fracture, with the failure mode transitioning to interlayer fracture.

Cast aluminum alloys are widely used in aerospace, automotive and other industries due to their excellent mechanical properties. However, traditional alloy design faces challenges such as vast composition space, high costs of trial-and-error experiments and difficulty in predicting the nonlinear relationship between composition and properties. This paper proposes a machine learning model that combines backpropagation neural networks, principal component analysis, and genetic algorithms for multi-objective property prediction of cast aluminum alloys. The model establishes the relationship between alloy composition and properties through the nonlinear mapping of backpropagation neural networks, reduces dimensionality via principal component analysis, and optimizes network parameters using genetic algorithms-thereby improving prediction accuracy and training efficiency. The results show that the optimized model has mean squared error of 36.28, correlation coefficient of 0.91, and mean absolute error of 2.44. In the experimental verification of ultimate strength, yield strength, and elongation after fracture, the error between experimental values and predicted values is controlled within the range of ±5%. This high prediction accuracy demonstrates the efficiency and reliability of the proposed model.

To address the challenge of inconsistent forming quality observed in carbon fiber-reinforced polyaryl ether ketone（CF/PAEK）composites during in-situ automated fiber placement（AFP）, this study introduces a vacuum-assisted in-situ annealing（VIA）process implemented subsequent to layup. The study systematically examines the impact of VIA parameters—specifically annealing temperature and holding time—on various aspects of CF/PAEK unidirectional laminates, including temperature field uniformity, warpage deformation, porosity, crystallinity, and interlaminar properties. Experimental findings reveal that the VIA process facilitates a uniform temperature field, mitigates crystallinity gradients, and progressively diminishes warpage deformation with an increase in annealing temperature, ultimately achieving complete elimination of warpage. Notably, when the annealing temperature surpasses the resin melting point, internal pores formed during the CF/PAEK prepreg or AFP process undergo substantial reduction, resulting in a porosity level of merely 2%. Furthermore, the interlaminar performance exhibits a remarkable enhancement, with an interlaminar shear strength（ILSS）of 64.66 MPa—representing a 58.6% improvement compared to specimens that have not undergone VIA treatment.

The tribological properties and wear mechanisms of PTFE filled with graphene at mass fractions of 0.5%, 1%, 3%, 5%, and 7% are investigated, and these are compared with those of PTFE filled with the traditional modifier MoS₂ at mass fractions ranging from 5% to 25%（in increments of 5%）. Additionally, a synergistic modification of PTFE with a combination of "graphene+MoS₂" is conducted, focusing specifically on the tribological properties and wear mechanisms of composites containing MoS₂ at a mass fraction of 15% combined with graphene at mass fractions of 1%, 3%, and 5%. The findings reveal that the incorporation of graphene significantly enhances the tribological performance of PTFE and its composites. Notably, the optimal tribological properties are observed when graphene is present at a mass fraction of 5%, exhibiting an average friction coefficient of 0.0763 and a volumetric wear rate of 230.34×10⁻⁹ mm³·N⁻¹·m⁻¹. The predominant wear mode shifts from adhesive wear to fatigue wear under these conditions. When graphene is used in conjunction with MoS₂ for synergistic modification, it effectively addresses the issue of poor compatibility between MoS₂ and PTFE, mitigating the tendency of MoS₂ to be worn away and causing abrasive wear during friction.

Titanium alloys are widely used in the fields of aviation, aerospace and marine due to their excellent strength, weldability and plasticity. This study focuses on a near-α titanium alloy Ti-6.5Al-2Zr-Mo-V（TA15）, fabricated by selective laser melting（SLM） technology. The impact of laser scanning speed on the macroscopic morphology and microstructure of the TA15 alloy is investigated using a range of analytical methods such as confocal laser scanning microscopy（CLSM）, optical microscopy（OM）, scanning electron microscopy（SEM）, X-ray diffraction（XRD） and energy dispersive spectroscopy（EDS）. The results show that variations in laser scanning speed significantly influence the forming quality of the alloy. Specifically, higher scanning speeds induce discontinuous fluctuations in the melt pool and irregular surface undulations, whereas lower speeds promote porosity formation at the cross-section. Initially, an increase in laser scanning speed enlarges the size of the martensite structure, followed by a decrease, accompanied by a gradual reduction in martensite hierarchy. Low or high laser scanning speeds cause local cracks on the alloy surface, where elemental depletion and enrichment are observed. These findings demonstrate a direct correlation between laser scanning speed and alloy forming quality. These results provide valuable insights for optimizing the process parameters and strategies of SLM for TA15 alloy, thereby facilitating its further promotion and application.

With the upgrading of information security, target stealth and electromagnetic protection, the urgent development of highly efficient wave-absorbing materials is imperative. This paper briefly describes the working principle of wave-absorbing materials, and comprehends the research progress of coated and structural wave-absorbing materials, and finally focuses on the development of fiber hybrid wave-absorbing composites: the fiber arrangement, component regulation and interface design can synergistically enhance the electromagnetic and mechanical properties. Through multi-fiber synergistic design and multi-scale structural optimization, fiber hybrid wave-absorbing composites can realize the coupling optimization of impedance matching and loss mechanism, and have both broadband absorption and mechanical loading characteristics, which promote the development of wave-absorbing materials in the direction of structural and functional integration. Finally, the technological breakthrough of expanding the wave-absorbing frequency band through multi-fiber blending system is summarized, and the future development of a new generation of dual-use wave-absorbing materials with broadband absorption, lightweight and high-strength characteristics around the deepening of the fiber blending mechanism, multi-scale structural design, improvement of the environmental adaptability, multi-functional integration, synergistic control of the fiber orientation and angle of incidence, and the development of high-temperature ceramic-based wave-absorbing materials are prospected.

This study investigates the performance evolution of T800/polyaryletherketone（PAEK） thermoplastic composites subjected to hygrothermal aging conditions. By meticulously controlling the cooling rate, two distinct types of carbon fiber-reinforced PAEK composites with varying crystallinities are prepared: CF/PAEK-CL（low crystallinity） and CF/PAEK-CH（high crystallinity）. These composites are then systematically examined for their moisture absorption behavior, thermal properties, and mechanical performance in hygrothermal environments. Experimental results reveal that the water absorption of CF/PAEK composites increases progressively over time, with CF/PAEK-CL exhibiting a notably higher moisture uptake rate due to its lower crystallinity. Following hygrothermal aging, the glass transition temperature（T_g） of all samples decreases, with CF/PAEK-CL experiencing a specific reduction of approximately 5%. Thermal analysis further indicates that hygrothermal aging has a negligible impact on the crystallinity of the materials, and notably, the high-crystallinity composite demonstrates superior thermal stability in such environments. Flexural testing results demonstrate that hygrothermal aging has a limited influence on the flexural strength and modulus of CF/PAEK composites, underscoring their robust resistance to the detrimental effects of hygrothermal conditions on flexural mechanical properties. This resilience ensures their long-term stability and reliability in harsh environments. The findings of this study offer pivotal data and theoretical insights, paving the way for the application of CF/PAEK composites in demanding service conditions.

Optimizing the directional solidification process of nickel-based superalloys is pivotal for enhancing the quality of hot-end castings in aero-engines. Traditional process optimization methods have heavily relied on empirical trial-and-error approaches, whereas numerical simulation technology is increasingly emerging as a pivotal tool. This paper presents a comprehensive review of the latest advancements in numerical simulation pertaining to the directional solidification process of nickel-based superalloys. It emphasizes modeling methodologies, simulation outcomes, and their practical applications in process optimization and defect control（such as stray grains and freckles） across various multi-physics fields, encompassing temperature fields, fluid flow and solute transport, stress-strain fields, and microstructural aspects（grains and dendrites）. A synthesis of current research reveals that numerical simulation studies still grapple with several shortcomings: a high degree of dependence on approximate boundary conditions in models; inadequate refinement and limited global optimization capabilities within process windows; incomplete numerical representations of certain crystalline defects and complex defect interactions; and substantial computational resource demands for high-fidelity microstructural simulations. To tackle these challenges, future research trends are anticipated to concentrate on deepening and integrating multi-physics and cross-scale coupling models, leveraging artificial intelligence-driven simulation and optimization, enhancing the precise characterization of solidification mechanisms in multi-component alloys, and strengthening experimental-simulation collaborative validation systems through the integration of in-situ characterization techniques with simulations. By advancing in these areas, numerical simulation technology is poised to play a pivotal role in achieving precise control over the morphology and properties of complex castings, while effectively mitigating defects.

In order to investigate the effect of low-angle grain boundary（LAGB） on the high-temperature creep behavior of a second-generation nickel-based single-crystal（SX） superalloy, the high-temperature creep fracture and interrupted experiments are carried out at 1100 ℃/137 MPa using plate-shaped samples with different grain boundary misorientations. The results show that after standard heat treatment, fine MC carbides are formed at the LAGB with the misorientation of 7° in alloy GB-7, while blocky M₆C carbides are formed at the LAGB with the misorientation of 12° in alloy GB-12. The high temperature creep life of the investigated alloys decreases with increasing the misorientation degree. The creep life of alloy GB-12 is only 40% of that of the single crystal alloy. Further investigation reveals that LAGB migration occurrs in both the GB-7 and GB-12 alloys during high-temperature creep, but the migration distance of the GB-12 alloy is lower than that of the GB-7 alloy. Blocky M₆C carbides in alloy GB-12 hinder the grain boundary migration, leading to strain concentrations at the LAGB region. Cracks tend to initiate at the low-angle grain boundary either inside GB-12 alloy or on its surface, leading to a significant reduction in its creep life. This study can provide guidance and data support for improving the tolerance of LAGBs in high-temperature creep.

Thermal simulation compression tests are conducted on a new type of ultra-high strength and toughness TB17 titanium alloy using Gleeble-3500 thermal simulation testing machine under the conditions of deformation temperature ranging from 795 ℃ to 895 ℃ and strain rate of 0.001 s⁻¹ to 1.0 s⁻¹. The microstructure and plastic flow behavior of the alloy during hot deformation are analyzed, and a constitutive model of flow stress is established. The results show that the flow stress of the alloy increases rapidly with the increase of strain, then decreases slightly, and finally tends to be stable. Partial dynamic recrystallization occurs in the alloy, dominated by dynamic recovery, and the slight decrease in flow stress is related to the partial dynamic recrystallization of the alloy. Dynamic recrystallization volume fraction of the alloy is not higher than 40%, and the dynamic recrystallization mechanism is mainly dominated by the bowing mechanism. A constitutive model based on the Arrhenius equation is constructed, and the deformation activation energy Q value of the alloy at the temperature of 795-895 ℃ is obtained as 205.48 kJ/mol. The model has high prediction accuracy, with average error δ_avg of 3.987% and correlation coefficient R of 0.9972. The construction of this model provides an accurate prediction for the flow stress of TB17 titanium alloy during hot deformation and also offers a reference for the establishment of high-precision constitutive models for other alloys.

The mechanical properties and thermodynamic stability of nickel-based single-crystal superalloys are largely dependent on the charateristics of the precipitated phase interface. In this work, density functional theory（DFT）is utilized to investigate the influence of alloying elements, specially Co, Cr, Mo, W, Re and Ta, on the mechanical properties of γ-Ni/γ′-Ni₃Al interface. Following a convergence analysis to the optimal computational model, our findings reveal that Re and W exhibit the most significant strengthening effects within both the γ and γ′ phases. Notably, Re stands out for its substantial enhancement of Young’s modulus（27 GPa and 11 GPa）and shear modulus（16 GPa and 6 GPa） in the γ and γ′ phases, respectively, while Ta demonstrates a unique proficiency in augmenting the bulk modulus of 21 GPa and 14 GPa in the γ and γ′ phases, respectively. Analysis of interfacial tensile properties indicates that the Re-doped system exhibit the highest ideal tensile strength（approximately 25 GPa）and deformation energy（approximately 1.84 J·m⁻²）. Furthermore, the strengthening impact of alloying elements on interface tensile properties diminishes in the order: Re＞W＞Cr＞Mo＞Ta＞Co＞undoped. Analyses of differential charge density and density of states reveal that the strengthening mechanisms of theses alloying elements are attributable to the augmentation in the chemical bonding strength between doped atoms and their nearest-neighbouring host atoms. Electron orbital characteristics indicate that these alloying elements contribute to retarding interfacial fracture by maintaining local structural stability. A series of results provide ideas for the development of novel nickel-based single-crystal superalloys.

Aerospace equipment materials demand an ultra-high level of safety and reliability, with fatigue performance being one of their core performance metrics. Traditional fatigue prediction methods rely heavily on extensive experimental tests, which are associated with high costs and long development cycles, thus failing to meet the requirements of modern aerospace engineering for efficient and accurate performance evaluation. In recent years, machine learning has exhibited remarkable potential in the fatigue life prediction of aerospace materials. This work presents a systematic review of the research progress in this field, with a focus on mainstream models and modeling workflows. It clarifies the core ideas and key research findings of both pure data-driven methods and physics-integrated approaches, and centers on the role of physical information embedding in enhancing model accuracy, credibility, and interpretability. Moreover, the paper critically discusses the existing limitations, including insufficient information mining in terms of data dimensions and complex failure mechanisms, inadequate model interpretability and low trustworthiness for engineering applications, as well as poor adaptability to complex service conditions. Finally, key research directions for addressing these limitations are highlighted, such as constructing standardized and highly reliable fatigue datasets, establishing a task-oriented automatic fusion mechanism for physical knowledge, and advancing fatigue life prediction at the level of structural components under complex service conditions.

The operating temperatures of hot-section components in advanced aero-engines continue to increase, accompanied by increasingly severe service conditions. Conventional thermal barrier coatings（TBCs）can no longer meet these demanding requirements, necessitating the development of new TBCs with higher temperature resistance and superior overall performance. This paper systematically analyzes the application requirements for new thermal barrier coating materials in advanced aero-engines, focusing on material composition, fabrication processes and microstructure. It elaborates on recent research progress in three types of novel TBCs: rare-earth-doped ZrO₂ coatings applied via atmospheric plasma spraying（APS）, rare-earth zirconate coatings produced by electron beam physical vapor deposition（EB-PVD）, and high-entropy ceramic coatings fabricated through plasma spray-physical vapor deposition （PS-PVD）. Compared to traditional double-layer structured yttria-stabilized zirconia（YSZ） TBCs, these new coating systems—based on rare-earth-doped ZrO₂, rare-earth zirconates, or high-entropy ceramics—exhibit lower thermal conductivity, enhanced thermal shock resistance, and superior resistance to calcium-magnesium-alumino-silicate （CMAS） corrosion. Through in-depth integration with processes such as APS, EB-PVD and PS-PVD, the performance of these coatings has been significantly improved, making them suitable for application in critical hot-section components like floating wall tiles and turbine blades. As breakthroughs continue to emerge in new materials, structures and processes, these advanced thermal barrier coatings are poised to provide crucial support for next-generation aero-engines, enabling them to surpass current temperature limits and achieve greater efficiency and reliability.

Based on the hot-ended casing of K4169 superalloy as the research object, aiming at the defects such as liquid splashing, oscillation and entrained air in the linear filling process of traditional superalloy counter-gravity casting, particularly, considering the complex variable cross-section structure of the casing castings, the work explores the influence of pressurization speed on filling of such structure through hydraulic simulation experiments. The results reveal that for the variable cross-section structure, a lower pressurization speed leads to more stable liquid filling. Orthogonal experiments are conducted to ascertain the optimal filling process parameter of the casing model such as a pouring temperature of 1460 ℃, a shell temperature of 900 ℃ and an average pressurization speed of 4 kPa/s. Based on the casing model’s structure, linear and nonlinear filling pressure curves are designed, and both numerical simulations and experimental studies are performed to compare two filling methods. When comparing two filling processes with the same filling time, the nonlinear filling exhibits a 16.77% decrease in average gate speed compared to the linear filling, resulting in a more stable filling process and production of fewer overall defects in the thin wall areas of the casing. Casings filled using the linear method exhibit numerous crack defects across various regions, leading to a relatively high overall defect rate. In contrast, casings filled using the nonlinear method devoid of crack defects and contain only a few micro-pores. Non-destructive testing results also support the notion that casing castings filled by the nonlinear method have fewer defects, which validates that the nonlinear filling effectively reduces the type and quantity of defects in casing castings.

Grain refinement can effectively enhance mechanical properties of materials at low and medium temperatures, however, it may weaken the stress rupture property above the equicohesive temperature. To study the effect of grain refinement on the stress rupture property of K447A alloy, the microstructure evolutions of alloys with three grain sizes and their corresponding stress rupture mechanisms under the conditions of 760 ℃/724 MPa, 815 ℃/600 MPa, 870 ℃/365 MPa and 980 ℃/210 MPa are investigated using scanning electron microscopy（SEM） and energy dispersive spectroscopy（EDS）. The results show that the equicohesive temperature of K447A alloy lies between 815 ℃ and 870 ℃. Grain refinement shows a temperature-dependent effect on the stress rupture life of K447A alloy. At 760 ℃/724 MPa, as the grain size decreases from 5.0 mm to 1.3 mm and then to 58 μm, the stress rupture life of K447A alloy increases from 83 h to 115 h and further to 194 h, respectively. At 815 ℃/600 MPa, the stress rupture life increases from 31 h to 84 h, as the grain size decreases, and then slightly drops to 76 h. At 870 ℃/365 MPa and 980 ℃/210 MPa, the stress rupture life shows a monotonic decreases with grain refinement. Therefore, grain refinement serves as an effective technology to improve the stress rupture property of K447A alloy below 870 ℃.The stress rupture process is dominated by intragranular deformation below 815 ℃, and grain refinement mainly extends the stress rupture life by shortening the slip band length and increasing the volume fraction of γ′ phase. Above 870 ℃, grain boundary sliding dominates the stress rupture process. The deterioration of the stress rupture property due to grain refinement can be attributed to the severe grain boundary slip at high temperatures, grain boundary oxidation and the formation of brittle AlN and a low-strength precipitation free zone（PFZ）.

Damage detection is a critical link of aviation equipment development, field operation and maintenance, which directly affects the development process and service safety of aircraft structure. In recent years, domestic and foreign scholars and scientific research institutions have carried out a lot of research works in the field of ultrasonic nondestructive testing. Based on this, this paper, guided by the needs of damage detection in the development and operation of aviation equipment, briefly analyzes the characteristics and requirements of typical structural damage of aviation equipment and in-situ detection. This paper focuses on summarizing the latest research progress of ultrasonic theories and methods, advanced detection sensor designs and special detection device research and development. Furthermore, incorporating new issues, ideas and directions emerging from technological research and engineering practice, this paper summarizes and forecasts the main challenges and future development trends in areas such as damage detection technologies for heterogeneous materials, transducer design methods for complex-shaped structures, and the equipment research and development and engineering application of new non-contact testing devices.

High-temperature resistant ceramic matrix composites (HT-CMCs) have demonstrated immense application potential in aerospace, energy, and other extreme service environments, thanks to their outstanding attributes such as exceptional high-temperature resistance, high strength, low density, and excellent chemical stability. Traditional manufacturing processes are constrained in fabricating HT-CMCs with complex shapes and high performance. In contrast, additive manufacturing (AM) technology has paved a new way for the production of HT-CMCs with intricate structures, leveraging its unique capability of layer-by-layer construction. This technology substantially improves the functional properties and structural efficiency of materials by enabling the direct fabrication of complex internal features, like cooling channels. It also supports performance-oriented precise control and customized production according to specific service requirements, while significantly reducing material waste and effectively cutting down manufacturing costs. This paper focuses on the additive manufacturing technology of HT-CMCs. It introduces the technical principles and current application status of this technology, and places particular emphasis on expounding the latest research advancements both domestically and internationally in material system design, forming technologies, and process optimization for additively manufactured HT-CMCs. Furthermore, this paper sets out the future trends of additive manufacturing for HT-CMCs. In terms of material-process synergy, the focus is on overcoming the bottleneck of interface bonding in multi-material printing and developing composite processes to achieve multi-functional integration and gradient structures. Regarding the construction of intelligent systems, the aim is to establish a “digital control-real-time monitoring-parameter optimization” system and reduce trial-and-error costs through AI-based parameter adjustment. In the realm of modularization and circular manufacturing, the emphasis is on developing interchangeable standardized modules and innovating ceramic waste recycling technologies to enhance material utilization rates. All these endeavors are aimed at promoting its engineering application in cutting-edge fields.

2.5D woven composites show great promise for aerospace applications owing to their high specific strength, high specific modulus and good delamination resistance. However, there is a dearth of research on their mechanical properties and failure behaviour at high temperature environment. This paper presents numerical simulation and experimental study on the quasi-static tensile mechanical response and failure behaviour of 2.5D woven C_f/Al composites at high temperature (400 ℃). Representative unit-cell models at the micro- and meso-scale are constructed based on the microstructure and periodic arrangement characteristics of the yarn. Based on the temperature-related material parameters of the matrix and interface, a multiscale finite element model is established to numerically analyse the thermal stress distribution as well as macroscopic and mesoscopic mechanical behaviour of the composites at high-temperature environment. The high temperature induces inhomogeneous thermal stress distribution in the composites, where the matrix and yarns are subjected to compressive and tensile stress, respectively. The experimental results show that the tensile modulus, ultimate strength and elongation of the composites are 63.7 GPa, 238 MPa and 0.72%, respectively. The numerical tensile stress-strain curve is generally consistent with the experimental results. Numerical simulation results show that the matrix and interface damage that induced by the thermal stresses accumulates and expands gradually during the tensile process. This results in the emergence of local interface debonding at the initial tensile stage. As the tensile strain increases, the composites successively experience the local failure of warp yarns and transverse cracking of weft yarns. At the final stage, the severe axial fracture of warp yarns leads to catastrophic fracture of the composite, resulting in a dramatic drop of the tensile stress curve. The fractured warp yarn exhibits a rough fracture surface with the characteristics of fibre pull-out and matrix alloy tearing.

TiAl alloys have attracted much attention due to its excellent specific strength, specific stiffness, and high-temperature performance, which has great potential for application in the aerospace industry. With the development of aerospace technology, the performance requirements for its equipment and service materials have further increased. Thermomechanical treatment plays a very important role in the field of manufacturing technology of aerospace equipment. The mature preparation processes for TiAl alloys are mainly ingot metallurgy and powder metallurgy. TiAl alloys are obtained by both processes require subsequent thermomechanical treatment. Combining the processes of deformation with heat treatment, the microstructure of TiAl alloys can be effectively controlled, thereby improving the room-temperature brittleness and fracture toughness of alloys. On the basis of fully understanding the thermoplastic deformation behavior of TiAl alloys, further research on different hot working methods and processes, process parameter design and control of TiAl alloys are of great significance for reducing the processing cost of TiAl alloy products as well as promoting their production and application. This article mainly reviews the development status of thermomechanical treatment of TiAl alloys.The research progress in the thermoplastic deformation behavior as well as microstructure control of hotworking （hot forging, hot rolling, hot extrusion） and subsequent heat treatment of TiAl alloys is summarized. On the basis, this article proposes the development directions in thermomechanical treatment of TiAl alloys. The first is the research on thermomechanical treatment process of TiAl composite materials. On the basis of high-throughput material design, exploring the hot working and post-treatment process routes suitable for TiAl composites, is expected to develop a new type of TiAl material with excellent high-temperature comprehensive performance. The second is the optimization design of hot working process for large-sized TiAl alloy components. Combining machine learning methods to optimize the hot working parameters of large-sized TiAl alloy components, as well as predict the microstructure evolution during hot working, and developing new mold materials to effectively control the processing temperature, are expected to significantly improve the controllability and stability in the forming process of large-sized TiAl components. The third is the development of low-cost thermomechanical treatment technology of TiAl alloys, such as no package hot working technology and single-step heat treatment process. The fourth is the thermomechanical treatment control of new microstructures for TiAl alloys. On the basis of introducing nanostructures to refine the microstructure of TiAl alloys, a new type of TiAl alloy microstructure design is expected to carry out by thermomechanical treatment to further enhance the performance of TiAl alloys. The fifth is the efficient screening of thermomechanical treatment process parameters for TiAl alloys. Integrating multidisciplinary knowledge, constructing a large database of components, hot working/heat treatment parameters, microstructure, and properties, can reduce the costs and cycles of researches.

The rapid progress in aerospace engineering places an urgent demand for advanced structural materials that exhibit outstanding mechanical properties under ultra-high temperature operating conditions. While recently developed refractory high-entropy alloys (RHEAs) hold promising application prospects, they are still confronted with challenges, including room-temperature brittleness and elemental segregation, which present significant hurdles in manufacturing processes. Additive manufacturing (AM) technology offers distinct advantages in fabricating RHEAs, such as suppressing elemental segregation, refining microstructures, and enabling the production of components with complex geometries, thereby revealing the substantial research potential. This paper firstly introduces the main technical methods for AM-fabricated RHEAs. Subsequently, it systematically summarizes their microstructural features, elemental distribution patterns, and phase composition characteristics, along with an overview of their mechanical performance at both room and elevated temperatures. To address critical process challenges, such as cracking and porosity in AM-produced RHEAs, we not only review recent research achievements but also propose innovative strategies that combine composition optimization and grain boundary engineering to enhance the AM process. Finally, this paper makes prospects for further enhancing the room-temperature plasticity and high-temperature strength by introducing grain boundary strengthening elements or high-entropy ceramic strengthening phases through additive manufacturing technology in the future, as well as for the preparation of large-sized RHEAs complex components by suppressing cracking and residual stress.

The high-temperature mechanical properties of cast nickel-based superalloy K4222 enhance through alloying of Hf. This work investigates the effect of adding mass fraction of 0.72% and 1.5%Hf on the microstructure and high-temperature stress rupture properties of the alloy. The results reveal that the addition of Hf not only increases the MC carbide content in the alloy, but also facilitates the formation of eutectic （Ni₅Hf + γ） phases. After heat treatment, M₂₃C₆ carbides are dissolved at high temperature and MC carbides are degraded, resulting in an overall reduction in the carbide content of each alloy and the elimination of eutectic phases. However, a small amount of Ni₅Hf phase remains in the 1.5%Hf alloy. Meanwhile, the results show that Hf can greatly improve the stress rupture life of the alloy. Compared with 0%Hf alloy, the stress rupture life of the 0.72%Hf and 1.5%Hf alloys increases 101.4% and 211.2% under the condition of 899 ℃/172 MPa, respectively. The improvement of Hf content will reduce the rupture plasticity of K4222 alloy to a certain extent, but 0.72%Hf still maintains good level. Further analysis shows that the addition of Hf can change the morphology of carbides, increase the grain boundary strength, reduce the occurrence of carbide cracking and intergranular cracks, and thus improve the high-temperature creep strength of the alloy.

The creep properties of a corrosion resistant single crystal superalloy at 760 ℃/800 MPa, 980 ℃/250 MPa and 1120 ℃/130 MPa are investigated. The creep fracture microstructure, fracture characteristic and dislocation morphology under different conditions are analyzed using scanning electron microscopy（SEM）and transmission electron microscopy（TEM）. The results indicate that the alloy exhibits good creep performance at 760 ℃/800 MPa, 980 ℃/250 MPa and 1120 ℃/130 MPa, with its creep curves showing similar three-stage creep characteristics. As temperature increases and stress decreases, the creep lives of the initial and acceleration stages becomes shorter, while the creep life of the steady-state stage increases. Compared to 980 ℃/250 MPa and 1120 ℃/130 MPa, the creep rate during the initial stage is faster at 760 ℃/800 MPa. Under 760 ℃/800 MPa conditions, the γ′ phase retains its cuboidal morphology. The dislocation tangles forming in the matrix channels and stacking faults forming from some dislocation cutting γ′ phase have a reinforcing effect. The creep fracture morphology of the alloy involves cleavage-like and ductile dimple mixed fracture. At 980 ℃/250 MPa and 1120 ℃/130 MPa, the alloy exhibits obvious rafting behavior and topological inversion of γ′ phase and γ phase has finished. A high-density dislocation network forming at the γ/γ′ interfaces have a reinforcing effect. No stacking faults are observed to form. Dislocations cut into the γ′ phase during the later stage of creep.The creep fracture morphology is dominated by ductile dimple fracture. At 1120 ℃/130 MPa, a small amount of lamellar σ phases precipitate along specific directions in the alloy, indicating good microstructural stability.

The internal displacement change around shrinkage pores, stress and strain distribution, and microstructural evolution in the defect healing zone of ZTC4 titanium alloy during hot isostatic pressing (HIP) are investigated by numerical simulation combined with experimental methods. The results demonstrate that under the high-temperature and high-pressure conditions of HIP, high stress-strain zones form around the shrinkage pores. The stress magnitude shows an inverse relationship with the distance from pore surfaces, exhibiting higher stress levels in proximity to the pore boundaries. As the shrinkage pore size decreases, the strain concentration intensifies. After HIP, a radial pore-healing zone microstructure develops at the original shrinkage pore sites. Within this healed region, heterogeneous plastic deformation occurs among distinct α/β colonies. Colonies with more readily activated dislocation slip systems experience greater deformation magnitudes, ultimately leading to the formation of equiaxed grain structures.

This study systematically investigates the effects of trace Gd additions of 0.5% (mass fraction, the same hereinafter) and 1.0% on the microstructure and tensile property of ZK60 magnesium alloy. The as-cast and solution-treated microstructures of ZK60, ZVK600, and ZVK610 alloys are characterized by optical microscopy, scanning electron microscopy, energy dispersive spectroscopy, differential scanning calorimetry, and X-ray diffraction. The tensile properties of the alloy specimens are measured and analyzed via room-temperature tensile tests. The results show that the as-cast ZK60 alloy has grain size of 95 μm, with coarse blocky MgZn phases and a small number of Zn₂Zr₃ particles present at grain boundaries. Trace Gd addition increases the fraction of secondary phases and transforms the MgZn phase into the Mg₃GdZn₆ phase, but does not refine the grain size. The room-temperature tensile properties of the three as-cast alloys are relatively close. The as-cast ZVK610 alloy exhibits lower yield strength and ductility, which is associated with its relatively large grain size and increased grain-boundary secondary phases. After T41 step solution treatment, the grain of ZK60 alloy become oarse, the secondary phases are nearly eliminated, and the ductility is significantly improved. However, the yield strength decreases slightly due to grain coarsening. In contrast, a small amount of grain-boundary secondary phases remains in ZVK600 and ZVK610 alloys. T42 and T43 processes, designed with prolonged high-temperature solution time or elevated solution temperature, further reduce the secondary phase fraction in the matrix but lead to additional grain coarsening, resulting in further reduced yield strength and no obvious improvement in ductility. Therefore, T41 solution heat treatment process is recommended.

To meet the lightweigh requirements, the structure of castings is evolving towards thin-walled designs. Therefore, it is necessary to study the evolution characteristics of the microstructures and mechanical properties of thin-walled structures made of nickel-based superalloys. Firstly, a thin-walled casting with wall thicknesses of 1, 1.25 mm and 1.5 mm is designed. Gravity casting experiments are conducted under two different process conditions, and the microstructural analysis and mechanical property tests are carried out for two types of castings, respectively. The values of microstructural characteristics are determined, including secondary dendrite arm spacing（SDAS）, grain morphology and average grain size, as well as the size and volume percentage of the γ′ phase at different wall thicknesses of the castings under different cooling conditions. The corresponding hardness and tensile strength also are measured by experiments. The results show that SDAS increases by more than 29.9% as the wall thickness of the casting increases from 1 mm to 1.25 mm and 1.5 mm. The tensile strength of the casting fluctuates with the increase in wall thickness when the flask temperature is 900 ℃. However, the tensile strength of the casting increases as the wall thickness increases when the flask temperature is 25 ℃. The variation range of the castings cooling rates are determined through numerical simulation. The cooling rate range of castings with a sand mold temperature of 900 ℃ ranges from 16.0 ℃/s to 28.2 ℃/s while those produced with a sand mold temperature of 25 ℃ exhibit a cooling rate range of 26.2 ℃/s to 58.5 ℃/s.

Stress rupture tests are conducted on DD10 alloy specimens with two distinct wall thicknesses at conditions of 1000 ℃/200 MPa and 1100 ℃/100 MPa. The stress damage characteristics of these specimens and the reasons for the thin-wall effect are analysisd. The findings reveal that, under both test conditions, the stress rupture life of thinner specimens is markedly shorter compared to thicker ones, indicating a pronounced thin-wall effect in DD10 alloy. Although the reduction in effective bearing area due to oxidation does expedite the creep process to some extent, the variation in effective stress increase across different wall thicknesses is minimal, within a range of just 6%. This suggests that the augmentation in effective stress stemming from oxidation is not the primary catalyst behind the thin-wall effect. Microstructural observations of the surface and longitudinal sections of the fracture reveal that, under both test conditions, the cavities and cracks in thinner specimens are smaller in size than those in thicker specimens. Furthermore, the relationship between the stress intensity factor（K） and crack length（l） indicates that, for cracks of equivalent size in specimens with varying wall thicknesses, thinner specimens exhibit a higher stress intensity factor at the crack tip, rendering the crack more prone to propagation. Consequently, thinner specimens have a shorter critical size for crack instability expansion. The disparity in this critical size among specimens with different wall thicknesses is pinpointed as a crucial factor contributing to the thin-wall effect.

The directionally solidified superalloy DZ125 is widely used as turbine blades in aero-engines. This work investigates the influence of phosphorus（P）on the microstructure, mechanical properties and crack susceptibility of DZ125 alloy. The results indicate that P primarily segregates at grain boundaries in DZ125 alloy and has little effect on γ′ phases, γ+γ′ eutectic and carbides in the alloy. When P content reaches 0.008% （mass fraction, the same below） P-rich phases form in the interdendritic regions during casting, which subsequently dissolve back into the matrix during heat treatment.When the P content is no more than 0.0039%, P shows no obvious effects on the room-temperature tensile properties or the stress rupture life at 980℃/235 MPa. However, it has a significant impact on the stress rupture life at 760℃/805 MPa: the alloy with 0.0039% P exhibits a 37% decrease in stress rupture life at 760℃/805 MPa compared to the alloy with 0.0013% P, due to the segregation of P at grain boundaries weakens the grain boundaries. When the P content reaches 0.011%, the intergranular cracks appear in the DZ125 alloy hollow turbine blades during directionally solidified process. The main reason for the increase of crack susceptibility is excessive enrichment of P at grain boundaries and precipitation of P-rich phases nearby grain boundaries, which leads to grain boundary weakening and crack initiation.

The K418B superalloy is fabricated utilizing laser powder bed fusion (LPBF) technology, and an analysis is conducted to examine the impact of process parameters on microdefect, density, microstructure, and hardness by OM, SEM and hardness tester. This is achieved by varying the laser power (ranging from 140 W to 220 W) and scanning speed(between 600 mm/s and 1400 mm/s). The findings reveal that both laser power and scanning speed significantly influence the relative density and defect distribution of the samples. Specifically, low energy density leads to the formation of irregular pores, whereas high energy density is associated with the emergence of spherical pores and solidification cracks. Excessive or insufficient volume energy density (VED) results in decreased density and impaired performance. The optimal processing conditions are identified as a laser power of 180 W and a scanning speed of 1400 mm/s, under which the sample density exceeds 99.95%, with minimal surface defects and only a small quantity of solidification cracks. Microstructure reveals distinct melt pool boundaries and cellular structure, accompanied by a Vickers hardness of 366.8 HV_0.2. Notably, the grains at the melt pool boundaries are coarse, with cellular columnar crystals spanning multiple melt pools, indicating rapid solidification. The hardness initially increases and then decreases with VED, aligning with changes in pore content and density. The study attributes cracks primarily to thermal stress and provides a foundational basis for optimizing LPBF processing parameters of K418B alloy, holding potential engineering applications for enhancing the manufacturing quality of critical aero engine components.

Heat treatment is the most critical thermal process determining the properties of powder metallurgy（PM）superalloy components, with FGH96 currently being one of the most prevalent PM Ni-based superalloys. This work investigates the effects of two distinct solution heat treatment cooling methods—full air cooling quenching and combined air-oil cooling quenching—on the microstructure and properties of FGH96 alloy ring parts. The results indicate that both cooling methods yield equivalent grain sizes, ranging from grade 6.5 to 7. Notably, full air-cooled rings exhibit more homogeneous distribution of secondary γʹ phase. In contrast, rings subjected to combined air-oil cooling exhibit coarser secondary γʹ phases, with reduced quantity on the inner side compared to the outer side, attributable to internally diminished cooling rate. During the later stage of quenching, ring parts undergoing full air cooling experience a slower cooling rate than those using combined air-oil cooling. Furthermore, fine γʹ phases, possessing sizes between the secondary and tertiary γʹ phases, precipitate along the grain boundaries using full air cooling method, leading to grain boundary strengthening. This enhances tensile strength but reduces elongation and plastic elongation at 68 h in high-temperature creep tests. Additionally, due to the more uniform cooling rate throughout the ring during full air cooling quenching, the surface residual stress reduces with more uniform distribution, thereby augmenting dimensional stability during subsequent machining processes.