三级增压级试验件性能试验研究  

Experimental investigation of the performance in a three stage booster rig

作　　者：向宏辉[1] 夏联[1] 顾杨[1] 任铭林[1] 

机构地区：[1]中国燃气涡轮研究院零部件试验室,四川江油621703

出　　处：《燃气轮机技术》2009年第2期19-22,25,共5页Gas Turbine Technology

基　　金：国家APTD计划资助项目

摘　　要：本文针对大涵道比涡扇发动机增压级部件关键设计技术,对某型三级增压级试验件进行了总性能试验、级间参数测量试验、进气压力畸变试验以及声学测量试验等多项研究,深入分析了其试验数据。试验结果表明:增压级性能在全工况下达到或超过设计要求,级间匹配性能良好;综合畸变指数随着进口马赫数的增加而增加,跟均匀进气时相比,畸变时稳定工作边界向右下方偏移,喘振裕度相应减小;低转速时,增压级噪声的主要成分是叶片通过频率(BPF)及其谐波,但在低频区间上,许多离散的非BPF谐波分量也具有很大幅值,随着转速的提高,噪声频谱中的主要成分更加集中到BPF及其谐波分量上。In order to deal with the key technology of the booster component design in the high bypass ratio engine, a series of experiments of a three stage booster rig were carried out at a single stage and multistage compressor test facility. The experimental items included overall performance, parameters of stages, inlet total pressure distortion and acoustics. Aerodynamic performance and acoustic characteristics were also analyzed in detail. The experimental results show that the performance of the booster successfully reaches the design goal. With the ascent of the inlet Mach number, the multiple distortion index increases. The stability limit of the booster is moved down due to the inlet pressure distortion, and the surge margin reduces accordingly.The main elements of the booster noise are blade passing frequency（ BPF）and harmonic frequencies, but the non - BPF magnitudes of noise are also large in the low frequency segment at low speed. The main elements of noise spectrum more concentrate on the BPF and harmonic frequencies with the increase of the speed.

关 键 词：增压级试验件 性能 进气压力畸变 噪声 试验研究 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]