基于部件级模型的涡扇发动机红外特征预测方法  

Prediction method of turbofan engine infrared feature based on component-level model

作　　者：陈铭 张海波[1] CHEN Ming;ZHANG Haibo(College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2024年第6期32-47,共16页Journal of Propulsion Technology

基　　金：国家科技重大专项(J2019-III-0009-0053)。

摘　　要：为了在涡扇发动机总体设计和系统仿真阶段对红外特征快速评估,针对小涵道比涡扇发动机典型的轴对称式排气系统结构,提出了一种红外特征预测方法,并基于部件级模型构建了排气系统红外辐射强度的简化物理模型,以及尾喷流红外辐射强度的支持向量机模型,应用这两种模型分析了热力循环参数对发动机红外特征的影响,在开启加力后发动机红外辐射强度将比巡航状态提升1~2个数量级;讨论了发动机红外特征在飞行包线内的变化规律,在等转速条件下,排气系统红外辐射强度在低空高速状态的峰值约为高空低速状态谷值的1.35倍;尾喷流红外辐射强度在低空低速状态的峰值约为高空高速状态谷值的15倍;对比了外涵道引气和压气机引气冷却中心锥的红外抑制方案,前者对排气系统红外辐射的抑制效果优于后者,且对发动机总体性能的影响较小;最后分析了发动机过渡态时红外特征的变化趋势,其中排气系统红外辐射强度随油门的响应速率显著滞后于尾喷流红外辐射。To quickly evaluate the infrared radiation characteristics of turbofan engine in the stage of overall design and system simulation,a prediction method of infrared characteristics was proposed for the small bypass ratio turbofan engine with typical axisymmetric exhaust system structure.Based on the component-level model,a simplified physical model of infrared radiation intensity of exhaust system,and a support vector machine model of infrared radiation intensity of tail jet were built,and the influence of thermodynamic cycle parameters on engine infrared characteristics was analysed by these two models.After the afterburner is turned on,the infrared radiation intensity of the engine will be 1~2 orders of magnitude higher than that of the cruise state.The variation law of engine infrared characteristics in flight envelope was discussed.Under the condition of constant rotor speed,the peak value of exhaust system infrared radiation intensity at low altitude and high speed is about 1.35 times of the valley value at high altitude and low speed.The peak value of tail jet infrared radiation intensity at low altitude and low speed is about 15 times of the valley value at high altitude and high speed.The infrared suppression schemes of bypass bleed air and compressor bleed air cooling central cone were compared.The former is superior to the latter in suppressing the infrared characteristics of exhaust system,and has less influence on the overall performance of the engine.Finally,the changing trend of the engine infrared characteristics during the transition state was analysed,the response rate of the exhaust system infrared radiation intensity with throttle lags behind the tail jet infrared radiation.

关 键 词：涡扇发动机 部件级模型 排气系统 尾喷流 红外辐射 

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]