进气压力畸变对某涡轴发动机影响分析研究  

Study on Effects of Inlet Temperature Distortion on Turboshaft Engine

作　　者：杨宇飞 王召广 黄兴 屠宝锋[2] YANG Yufei;WANG Zhaoguang;HUANG Xing;TU Baofeng(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou Hunan 412002;School of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing Jiangsu 210016)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《中国科技纵横》2023年第4期63-67,共5页China Science & Technology Overview

摘　　要：以某组合压气机形式的涡轴发动机为对象,开展进气总压畸变对发动机稳定性和性能的影响研究。利用“平行压力机”理论,建立了多子发动机模型,通过一维、时间相关模型方程计算发动机内部的流动参数。通过该发动机的进气压力畸变试验结果校验计算模型,得到该涡轴发动机的压力畸变计算模型。利用该模型对发动机进行评估。计算结果表明,该型涡轴发动机低转速状态时的抗压力畸变能力较弱;当出现进气压力畸变后,第一级轴流压气机和离心压气机的工作裕度不足,此时发动机性能会快速下降,但当综合压力畸变指数超过1%后,性能下降趋势会降低。The combined compressor type of turboshaft engine being object,the stability and performance influence of inlet pressure distortion was studied.Using the theory parallel compressor,the parallel engine model is constructed.The main internal parameters of engine are calculated through one-dimensional and time-dependent model,then the calculation model was verified by the inlet pressure distortion test results of the engine,and the pressure distortion calculation model of the turboshaft engine was obtained.Finally,the model is used to evaluate the engine.The results show that the anti-pressure distortion ability of this turboshaft engine is weak at low speed;When inlet pressure distortion occurs,the first stage axial compressor and centrifugal compressor will have insufficient working margin,at this time,the engine performance will decline rapidly,but when the composite pressure distortion index exceeds 1%,the performance decline trend will be reduced.

关 键 词：涡轴发动机 压力畸变 组合压气机 稳定性 性能 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计]