涡扇发动机再压缩CCA系统热力循环耦合分析  

Thermodynamic cycle coupling analysis of recompressed CCA systemfor turbofan engine

作　　者：苏杭[1,2] 赵霄 张博[1,3] 杨竹强 SU Hang;ZHAO Xiao;ZHANG Bo;YANG Zhuqiang(Key Laboratory of Complex Energy Conversion and Efficient Utilization of Liaoning Province,School of Energy and Power Engineering,Dalian University of Technology,Dalian 116024,China;Xinxiang Aviation Industry(Group)Co.,LTD,Xinxiang 453049,China;NingBo Institute of Dalian University of Technology,Ningbo 315016,China)

机构地区：[1]大连理工大学能源与动力学院辽宁省复杂能源转换和高效利用重点实验室,辽宁大连116024 [2]新乡航空工业(集团)有限公司,河南新乡453049 [3]大连理工大学宁波研究院,浙江宁波315016

出　　处：《大连理工大学学报》2024年第5期495-506,共12页Journal of Dalian University of Technology

基　　金：国家科技重大专项资助项目(121019111-065);航空发动机及燃气轮机基础科学中心项目(P2022-B-Ⅱ-022-001);中国科协青年人才托举工程资助项目(2022QNRC001).

摘　　要：为了提高发动机的推进性能和热效率,同时改善发动机冷却引气品质,在传统预冷冷却空气(cooled cooling air,CCA)技术基础上,建立基于再压缩CCA系统的典型飞机发动机热力计算耦合分析仿真平台.结合涡轮叶片平均壁温计算模型和飞机/发动机总体匹配模型,分析再压缩CCA系统对涡轮叶片冷却效果、发动机总体性能及相应飞行性能的影响规律.结果表明:采用减小引气比的方式未加力时推力最高提升7.88%,加力时推力最高提升2.03%;加力时耗油率降低、热效率提升,冷却引气总温降低100~120 K、总压提升4%左右,高压涡轮导叶冷却效果提高显著.采用提高燃烧室最高出口温度的方式未加力时推力最高提升22.81%,加力时推力最高提升3.70%;加力时耗油率降低、热效率提升,冷却引气总温降低90 K左右,且在各任务航段高压涡轮叶片温度均低于许用温度.两种方案再压缩CCA系统对发动机性能损失基本无影响,取功比在各状态下均低于0.25%.Based on the traditional cooled cooling air(CCA)technology,a typical aero engine thermodynamic calculation coupling analysis simulation platform with recompressed CCA system is established to improve the propulsion performance and thermal efficiency of the engine and promote the quality of engine cooling bleed air.Combining with the average wall temperature calculation model of the turbine blade and the aircraft/engine overall matching model,the influence law of recompressed CCA system on turbine blade cooling effect,overall engine performance and corresponding flight performance is analyzed.The result shows that by reducing the bleed air flow ratio,the thrust is increased by 7.88%at most without afterburner and 2.03%at most with afterburner.The thrust specific fuel consumption is reduced,and the thermal efficiency is increased with afterburner.The total temperature of cooling bleed air is reduced by 100-120 K,and the total pressure is increased by about 4%with afterburner,which significantly improves the cooling effect of high pressure turbine nuzzle vane.By increasing the maximum outlet temperature of the burner,the thrust increases by 22.81%at most without afterburner and 3.70%at most with afterburner.The thrust specific fuel consumption is reduced,and the thermal efficiency is increased with afterburner.The total temperature of cooling bleed air is reduced by about 90 K,and the high pressure turbine blade temperature is lower than the allowable temperature in each mission phase with afterburner.The recompressed CCA system of the two schemes has no effect on engine performance loss,and the system power takeoff ratio is less than 0.25%in each state.

关 键 词：涡扇发动机 再压缩 冷却空气 性能分析 热力循环 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]