处理机匣结构对某型跨声速轴流压气机畸变响应特性影响  

Making Axial Flow Compressor Tolerant to Severe Circumferential Pressure Distortion with Deliberate Design of Casing Treatment

作　　者：吴虎[1] 黄健[1] 高双林[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《西北工业大学学报》2005年第5期567-571,共5页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(10377013)资助

摘　　要：基于机匣处理下的跨声速轴流压气机叶排实验特性,应用畸变传递的矩阵分析模型,对叶尖处理机匣结构容总压畸变特性进行了详细分析,初步建立了几种处理机匣结构对总压畸变及其沿轴流压气机叶排衰减特性影响规律。计算结果表明,处理机匣虽能有效提高了转子叶排抗总压畸变能力,但不同结构处理机匣下静子叶排抗畸变特性存在明显差异,这对设计合理的扩大轴流压气机稳定裕度处理机匣结构尤为重要。An important component of the gas turbine engine is its axial flow compressor system. With the advent of high maneuvering aircraft with weapons release in the vicinity of the engine inlets, there will always exist inlet total pressure distortions. So, in today＇s military turbine engines, their axial compressors must be capable of stable operation despite severe inlet total pressure distortion. Our aim is to see what can be done about casing treatment to implement this desirable situation. Many experimental and analytical investigations have been conducted in the past four decades to quantify the effects of various casing treatment configurations on axial compression system stability with both uniform and distortion inlet flow conditions. An efficient calculation model for studying what to do about casing treatment is established which allows the rapid computation of the inlet circumferential total pressure distortion development through any combination of rotors, stators and clearances. The predictions of aerodynamic response of an axial flow compressor rotor, stator and axial clearance to steady circumferential pressure distortion are presented with four casing configurations： solid casing, circumferential groove casing, axial skewed slot casing, and blade angle slot casing. With inlet pressure distortions, it is found that the last three easing configurations that all improve the stall margin of axial flow compressors under uniform inlet conditions is still superior to the solid casing. For the rotor with inlet circumferential total pressure distortion, by using the last three casing configurations, we obtain weak incidence angle changes, low total temperature distortion production, and last but most importantly great attenuation of total pressure distortion. It is apparent that effective improvement in stall margin can be achieved with proper casing treatment under inlet circumferential pressure distortions. Deliberate design of appropriate casing treatment configurations must be considered to make axial c

关 键 词：轴流压气机 压力畸变 响应特性 处理机匣 

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]