进气道防冰引气对压气机性能影响的快速评估方法研究  

A rapid evaluation method for effects of anti-icing bleed air of intake on compressor performance

作　　者：杨宇飞 魏佐君 任光明 李成 YANG Yufei;WEI Zuojun;REN Guangming;LI Cheng(Shenzhen Key Laboratory of Wide-Speed-Range and Variable-Density Continuous Wind Tunnel,Southern University of Science and Technology,Shenzhen 518055,China;AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;College of Engineering,Southern University of Science and Technology,Shenzhen 518055,China)

机构地区：[1]南方科技大学深圳市宽速域变密度连续式风洞重点实验室,广东深圳518055 [2]中国航发湖南动力机械研究所,湖南株洲412002 [3]南方科技大学工学院,广东深圳518055

出　　处：《推进技术》2025年第2期57-66,共10页Journal of Propulsion Technology

基　　金：深圳市科技计划基础研究专项项目(JCYJ20200109141403840);深圳市科技计划平台和载体专项项目(ZDSYS20220527171405012);国家自然科学基金(52106045)。

摘　　要：为在不增加整机性能计算复杂度和数据信息要求的前提下,考虑进气道防冰热空气排入所造成的流动掺混和畸变的影响,本文提供了一种快速评估进气道防冰引气对压气机性能影响的计算方法。该方法采用多维度耦合计算方法,对于具有防冰引气排入的进气道采用全三维CFD计算,同时引入平行压气机模型的思想评估畸变进气下的压气机特性,从而实现进气道与压气机的不同维度数据在AIP界面的动态交互,进而通过迭代求得进气道流量与防冰引气流量的匹配。通过该评估方法分析了进气道出口不同周向和径向分区数对压气机性能评估的影响,从而说明了耦合计算的重要性。采用本方法计及防冰引气引起的畸变影响后,防冰引气比为1.6%时压气机失速边界流量增加约2%,失速边界变窄,堵塞流量减小约2%。防冰引气排入流量越大,压气机性能下降越大。To consider the influence of flow mixing and distortion caused by the anti-icing hot air exhaust⁃ed into intake without increasing the computational complexity and data requirement during the modelling of en⁃gine performance,this paper presents a method to quickly evaluate the effect of anti-icing bleed air of intake on compressor performance.The method adopts a multi-dimensional coupling calculation method with different di⁃mensional models,which adopts a fully three-dimensional CFD calculation to solve the intake flow and introduc⁃es the idea of parallel compressor model to evaluate the compressor characteristics.As a result,the dynamic up⁃date of different dimension data of intake and compressor on the air interface plane(AIP)is realized,and the matching of their flow rate is obtained through iteration.By this evaluation method,the influence of different cir⁃cumferential and radial partition numbers on the compressor performance evaluation is analysed,showing the im⁃portance of the fully coupling calculation.After considering the distortion caused by anti-icing bleed air using this method,when the bleeding ratio is 1.6%,the stall point flow rate increases by about 2%,which means the surge margin becomes narrower,and the blocking point flow rate decreases by about 2%.The greater the dis⁃charge rate of anti-icing bleed air,the greater the decline in compressor performance.

关 键 词：防冰引气 进气道 压气机性能 多维度耦合计算 快速评估方法 

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]