航空发动机钛火特性理论计算研究

梁贤烨; 弭光宝; 李培杰; 黄旭; 曹春晓

doi:10.11868/j.issn.1005-5053.2021.000113

航空发动机钛火特性理论计算研究

doi: 10.11868/j.issn.1005-5053.2021.000113

梁贤烨^{1, 2},
弭光宝^{1, 3, ,},
李培杰²,
黄旭^{1, 3},
曹春晓^{1, 3}

1.
中国航发北京航空材料研究院钛合金研究所, 北京 100095
2.
清华大学新材料国际研发中心, 北京 100084
3.
中国航发先进钛合金重点实验室, 北京100095

基金项目: 国家科技重大专项（J2019-VIII-0003-0165； 2017-VII-0012-0109）

详细信息

通讯作者:
弭光宝（1981—），男，博士，高级工程师，研究方向为航空发动机钛火防控技术与新材料，E-mail：guangbao.mi@biam.ac.cn

中图分类号: TG146.2
计量
- 文章访问数: 43
- HTML全文浏览量: 19
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- 被引次数: 0
出版历程
- 收稿日期: 2021-03-26
- 修回日期: 2021-08-17
- 刊出日期: 2021-12-01

Theoretical calculation of characteristics on titanium fire in aero-engine

LIANG Xianye^{1, 2},
MI Guangbao^{1, 3
, ,},
LI Peijie²,
HUANG Xu^{1, 3},
CAO Chunxiao^{1, 3}

1.
Titanium Alloys Research Institute, AECC Beijing Institute of Aeronautical Materials, Beijing 100095, China
2.
National Center of Novel Materials for International Research, Tsinghua University, Beijing 100084, China
3.
Aviation Key Laboratory of Science and Technology on Advanced Titanium Alloys, Beijing 100095, China

摘要

摘要: 钛火是现代航空发动机的典型灾难性事故，高压压气机机匣等钛合金部件的局部加热是主要的着火源。本研究通过对钛合金等温加热、非等温线性加热以及非等温摩擦加热的着火过程进行模型计算，研究初始加热温度、加热速率、氧浓度和流速等环境因素对着火参数的影响规律，进而给出钛火阻燃设计的建议。结果表明：在等温加热过程中，当加热面温度为1941 K时，临界着火温度约为958 K，着火延迟时间为0.2 s；在非等温线性加热过程中，加热速率为28 K/s、58 K/s及100 K/s的着火延迟时间分别为1.5 s、1.1 s和0.9 s，而临界着火温度基本维持在950 K，微凸体直径为16.5 μm时，临界着火温度约为765 K，与文献报道的实验结果一致；在非等温摩擦加热过程中，接触应力为26.5 kPa，加热速率为130 K/s时，着火延迟时间为1.4 s，流速为300 m/s时，临界着火温度为1040 K，着火延迟时间为2.8 s，当气流中氧浓度为50%，临界着火温度为920 K时，着火延迟时间为1.5 s；设计防钛火结构时应考虑低速环境下的阻燃性能。
- 钛合金 /
- 着火模型 /
- 着火温度 /
- 着火延迟时间 /
- 阻燃
Abstract: Titanium fire is a typical catastrophic failure of modern aero-engine. The local heating of titanium alloy in the high-pressure compressor is the main ignition source. In this study, the ignition process of aero-engine titanium alloy isothermal heating, non-isothermal linear heating and non-isothermal friction heating were modeled to study the influence of factors such as the initial heating temperature, heating rate, oxygen concentration and flow rate on the ignition parameters, and then the recommendations on the flame-retardant design of titanium fire were given. The results show that during the isothermal heating process, the critical ignition temperature is about 958 K. When the heating surface temperature is 1941 K, the ignition delay time is 0.2 s. In the non-isothermal linear heating process, the ignition delay time of the heating rate of 28 K/s, 58 K/s and 100 K/s are 1.5 s, 1.1s and 0.9 s respectively, and the critical ignition temperature is basically maintained at about 950 K; When the microconvex is 16.5 μm, the critical ignition temperature is about 765 K, which is consistent with the experimental results reported in the literature. In the non-isothermal friction heating process, the ignition delay time decreases with the increase of contact stress. When the contact stress is 26.5 kPa, the heating rate is 130 K/s, and the ignition delay time is 1.4 s; When the flow rate is 300 m/s, the critical ignition temperature is 1040 K, and the ignition delay time is 2.8 s; When the oxygen concentration in the airflow is 50%, the critical ignition temperature is 920 K, and the ignition delay time is 1.5 s. The flame retardancy in low- speed environment should be considered when designing anti-titanium fire structures.
- titanium alloy /
- ignition model /
- ignition temperature /
- ignition delay time /
- flame retardant

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图 1 着火模型示意图

Figure 1. Schematic diagram of the ignition model

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图 2 程序流程图

Figure 2. Flow chart of program

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图 3 有限元模型温度场分布

Figure 3. Temperature field distribution of finite element model

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图 4 反应区剖视图

Figure 4. Section view of reaction zone　（a） 0.9 s; （b） 2 s; （c） 2.2 s; （d） 2.3 s

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图 5 反应面俯视图

Figure 5. Top view of reaction surface　（a） 0.9 s; （b） 2 s; （c） 2.2 s; （d） 2.3 s

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图 6 等温加热温度历史

Figure 6. Isothermal heating temperature history

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图 7 线性加热温度历史

Figure 7. Linear heating temperature history

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图 8 不同有效半径线性加热温度历史

Figure 8. Linear heating temperature history with different effective radius

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图 9 不同接触应力摩擦加热温度历史

Figure 9. Friction heating temperature history with different contact stresses

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图 10 不同流速摩擦加热温度历史

Figure 10. Friction heating temperature history with different flow velocities

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图 11 不同氧浓度下摩擦加热温度历史

Figure 11. Friction heating temperature history with different oxygen concentrations

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表 1 材料热物性参数

Table 1. Thermal property parameters of materials

Density，ρ / （kg·m⁻³）	Specific heat，c_p / （J·kg⁻¹·K⁻¹）	Reaction heat， q_r /（MJ·kg⁻¹）	Pre exponential factor， K/（kg·m⁻²·s⁻¹）	Activation energy， E/ （kJ·mol⁻¹）	Thermal conductivity， λ/（W·m⁻¹·K⁻¹）
5300	520.8	24.7	0.15	190	17.8

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表 2 模型初始边界条件

Table 2. Initial boundary conditions of the model

Friction stress， N/MPa	Stator thickness， φ/ m	Particle radius， r/μm	Rotation radius， R₁/μm	Angular velocity， ω/（r·min⁻¹）	Oxygen concentration，c/ %	Flow velocity， v/ （m·s⁻¹）
2.65	0.002	165	4000	5000	21	10

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