Superiority analysis of CCA technology under typical flight mission
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摘要:
基于典型飞行任务,在F⁃119发动机方案的循环参数基础上,对采用冷却冷却空气(CCA)技术的航空发动机性能开展研究,分析CCA技术对发动机总体性能及涡轮叶片温度的影响规律,评估采用CCA技术的涡扇发动机对其所装配飞机的飞行性能的影响。结果表明:针对仅预冷高压涡轮动叶冷却气方案,当保持冷却空气流量不变时,采用CCA技术可将涡轮冷气温度降低16.98%~41.21%,使得高压涡轮动叶表面最高温度降低8.89%~16.80%;当保持叶片表面最高温度不变时,采用CCA技术可减少高压涡轮动叶48.61%的冷却用气,且发动机的推力和耗油率等总体性能基本不变;针对同时预冷高压涡轮导叶和动叶冷却气方案,通过调整循环参数,在保持冷却空气流量和叶片温度不变的前提下,可使涡轮前最高温度提高6.91%,从而提高典型飞行状态下的航发推进性能,进而有效提升所配装飞机的起飞载质量、最大爬升率、最大马赫数、使用升限及航程等飞行性能。
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关键词:
- 典型飞行任务 /
- 涡扇发动机 /
- 冷却品质 /
- 冷却冷却空气(CCA)技术 /
- 叶片表面温度
Abstract:To improve the overall aero⁃engine performance under typical flight mission,superiority analysis of cooled cooling air (CCA) technology was proposed to upgrade the cooling quality of turbine blade cooling air.The effects of introducing CCA technology into the aero⁃engine performance and further the flight performance of the aircraft equipped with the engine with CCA were evaluated based on the reported cycle parameters of F⁃119.The following conclusion can be obtained:in the case of only cooling the cooling air for the turbine rotor blade,when the mass flow rate of the cooling air kept constant,its temperature can be reduced by about 16.98%-41.21%,which lowered the rotor blade temperature by about 8.89%-16.80%.When the turbine blade temperature kept constant,the cooling air for turbine rotor blade can be reduced by about 48.61% and aero⁃engine performance maintained at the same level; in the case of cooling the cooling air for both the turbine stator and rotor blade,when the mass flow rate of the cooling air and turbine blade temperature kept constant,the turbine inlet temperature can be increased by about 6.91%,which can improve the propulsion performance of aero⁃engine,and eventually improve the flight performance of the aircraft,such as takeoff load mass,maximum climb rate,maximum Mach number,service lift limit and range.
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表 1 F⁃22战斗机质量组成
Table 1. Mass composition of F⁃22 fighter
参数 数值 起飞质量/kg 27 216 燃油质量/kg 11 430 机上乘员质量/kg 90 发动机质量/kg 3 537 机体结构质量/kg 7 340 机内装载质量/kg 4 817 起飞燃油系数 0.42 机体结构系数 0.465 发动机推质比 9 表 2 换热器结构参数
Table 2. Structural parameters of the heat exchanger
参数 数值 管外径/mm 5 管壁厚/mm 0.3 纵向管间距/mm 7.3 单排进气管数 4 换热器高度/mm 90 弯头个数 3 横向管排数 240 换热面积/m2 4.79 表 3 冷却性能参数
Table 3. Cooling performance parameters
参数 数值(目前水平) Kcool 0.045 ηint 0.70 εf 0.40 Bimatel 0.15 Bitbc 0.30 参数 飞行状态 H=0,Ma=0 H=11,Ma=1.5 换算空气流量/(kg/s) 126 125.52 涵道比 0.3 0.298 风扇压比 4.5 4.5 风扇效率 0.85 0.854 9 压气机压比 5.8 5.786 压气机效率 0.86 0.861 3 涡轮前温度/K 1 860 2 011 高压涡轮效率 0.87 0.875 低压涡轮效率 0.88 0.884 5 高压导叶引气比例/% 12 12 高压动叶引气比例/% 7.2 7.2 低压导叶引气比例/% 5.5 5.5 飞机系统引气比例/% 1 1 表 5 F⁃119发动机设计点验证(H=0 km、Ma=0)
Table 5. Verification of F⁃119 engine design point (H=0 km,Ma=0)
参数 文献[20] 计算值 GASTURB软件 推力/kN 105.5 105.08 105.9 耗油率/ 0.083 7 0.083 3 0.082 6 高压涡轮膨胀比 2.66 2.72 2.622 低压涡轮膨胀比 2.11 2.13 2.079 喉道面积/m2 0.244 8 0.243 7 0.249 9 表 6 F⁃119发动机非设计点验证(H=11 km、Ma=1.5)
Table 6. Verification of F⁃119 engine off design point(H=11 km,Ma=1.5)
参数 文献[20] 计算值 GASTURB软件 推力/kN 62.5 59.16 60.11 耗油率/ 0.118 3 0.128 0.119 3 换算流量/(kg/s) 126 125.5 1 125.52 风扇增压比 4.5 4.5 4.5 高压压气机增压比 5.8 5.786 5.786 状态 编号 航段 条件 说明 性能极限状态 1 起飞滑跑 H=0 km,Ma=0~0.13,Sto≤400 m,ξ=1.0 最大加力状态 2 最大爬升 H=0 km,Ma=0.8,dh/dt≥160 m/s,ξ=1.0 最大状态 3 作战盘旋 H=9.144 km,Ma=1.6,n=6.5,ξ=0.78 最大加力状态 4 最大飞行马赫数 H=10 km,Ma=2.25,ξ=0.7 最大加力状态 5 使用升限 H=19 km,Ma=1.6,ξ=0.7 最大加力状态 巡航状态 6 亚声速巡航 H=11 km,Ma=0.7,ξ=0.95 评估最大航程 7 超声速巡航 H=11 km,Ma=1.5,ξ=0.95 评估最大超声速巡航航程 表 8 不同航段下飞机载质量及推力需求
Table 8. Mass and thrust of aircraft for each route segment
航段编号 飞机载质量/kg 单发推力需求/kN 1 27 216.0 153.49 2 27 216.0 106.88 3 21 391.7 122.22 4 19 051.2 109.5 5 19 051.2 18.04 6 24 494.4 15.10 7 24 494.4 60.02 表 9 方案二下CCA换热器冷热侧进口参数
Table 9. Inlet parameters of CCA heat exchanger of hot and cold sides for the second schema
位置 参数 工况1 工况2 工况3 工况4 工况5 工况6 工况7 热侧 温度/K 803 841 884 849 796 593 865 压力/MPa 2.62 3.35 2.64 2.23 0.43 0.54 2.10 流量/(kg/s) 6.9 8.7 6.7 6.0 1.2 1.7 5.3 冷侧 温度/K 469 499 527 541 478 352 509 压力/MPa 0.45 0.60 0.47 0.50 0.08 0.10 0.36 流量/(kg/s) 28.8 40.7 31.2 51.9 6.5 10.6 22.0 表 10 方案三冷却空气引气流量
Table 10. Cooling air mass flow for the third schema
工况 流量/(kg/s) 1 3.4 2 4.2 3 3.2 4 2.9 5 0.6 6 0.8 7 2.6 表 11 改进CCA技术换热器冷热侧进口参数
Table 11. Inlet parameters of the modified CCA heat exchanger of cold and hot sides
位置 参数 工况1 工况2 工况3 工况4 工况5 工况6 工况7 热侧(冷却空气引气热力参数) 温度/K 849 875 929 959 869 612 877 压力/MPa 2.86 3.80 3.06 3.17 0.40 0.61 2.15 流量/(kg/s) 19.7 25.6 20.0 20.8 2.5 4.9 14.4 冷侧(外涵空气热力参数) 温度/K 495 517 548 588 513 361 515 压力/MPa 0.49 0.67 0.53 0.61 0.07 0.11 0.37 流量/(kg/s) 22.0 26.8 41.4 31.9 44.5 4.9 10.9 表 12 有无CCA方案时起飞质量组成
Table 12. Takeoff mass composition with or without CCA technology
参数 无CCA方案 有CCA方案 起飞推力/kN 312 335.6 起飞质量/kg 27 216 30 000 燃油质量/kg 11 430 13 650 机上乘员质量/kg 90 90 发动机质量/kg 3 537 3 804 机体结构质量/kg 7 340 7 643 机内装载质量/kg 4 817 4 817 起飞燃油系数 0.42 0.455 机体结构系数 0.465 0.465 发动机推质比 9 9 -
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