航空发动机

刘宝杰1，2，3，张帅1，于贤君1，2，3.4 级重复级低速模拟压气机的试验与计算[J].航空发动机,2018,44(5):

4 级重复级低速模拟压气机的试验与计算

Experimental and Numerical Calculation of a 4- stage Repeating Stage Low Speed SimulationCompressor

DOI：

英文关键词:4-stage repeating stage low speed simulation ield measurement numerical simulation high pressure compressor aeroengine

基金项目:国防科技重点试验室基金项目（51476004、51376014）资助

作者	单位	E-mail
刘宝杰1，2，3，张帅1，于贤君1，2，3	1. 北京航空航天大学能源与动力工程学院北京100191；2. 北京航空航天大学航空发动机气动热力国防重点试验室，北京100191；3. 先进航空发动机协同创新中心，北京100191	liubj@buaa.edu.cn

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中文摘要:

低速模拟试验技术为航空发动机高压压气机设计体系的发展完善以及关键技术验证提供了重要手段。为了验证和完善低速模拟试验技术，对1 台模拟某高压压气机后面级的4 级重复级低速大尺寸压气机进行了详细的试验研究，并利用小尺寸高精度5 孔气动探针获得了详细的转静子出口流场数据。试验结果表明：该4 级压气机实现了典型的重复级流动，较好地模拟了高速原型的流动特征，随着流量系数的减小，静子尾迹均匀增厚，未出现角区失速，流场组织合理。基于试验数据对常用的CFD 软件进行校验，表明CFX、Numeca 和Turbo 在叶片落后角、转子叶尖泄漏和静子损失等方面模拟存在不足

英文摘要:

An important mean for the development and improvement of the design system and the verification of the key technology of the aeroengine high pressure compressor was provided by the low speed simulation test technology. In order to verify and improve the low speed simulation test technology,a 4-stage repeating stage low speed and large size compressor of a certain high pressure compressor rear stage was simulated in detail. The detailed flow field data of rotor and stator outlet were obtained by using a high precision 5-hole pneumatic probe with small size. The test results show that the 4-stage compressor realizes the typical repeating stage flow and simulates the flow characteristics of the high-speed prototype commendable. The wake of the stator increases uniformly,no angular stall occurs and the flow field structure is reasonable with the decrease of flow coefficient. The commonly used CFD software is verified based on the test data. It is shown that the simulation of CFX,Numeca and Turbo are insufficient in the aspects ofblade backward angle,rotor tip leakage and stator loss.

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