4 级重复级低速模拟压气机的试验与计算

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。

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

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.