涡喷发动机压气机失速、喘振及喘振点参数的测量和分析
MEASUREMENTS AND ANALYSIS OF SURGE,STALL AND SURGE POINT PARAMETERS IN TURBOJET COMPRESSORS
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摘要: 本文介绍涡喷发动机在“净”和畸变进气下,涡轮一导面积减小12%或标准一导时,进行旋转失速和喘振试验的试验方法、测量方法及其试验的结果和分析。还介绍两种逼喘方法的试验,一种是静态逼喘,另一种是动态逼喘。试验结果表明,逼喘方式与喘振点参数有关联,动态逼喘的喘振点上的压比值与流量值分别比静态逼喘的低2.8%和1.7%。Abstract: This paper presents the testing and measuring method of three kinds of flow instability test(rotating stall and surge),the test results and analysis of them for a turbojet engine with "clean" or distorted inlet flow. The tests have been carriedout as follows. ( 1 )testing of the"upper"and"lower"stall-point on the stall line of the engine with and without distorted inlet flow; ( 2 )tests of surge in the engine with "clean" or distorted inlet flow at n= 1.0, 0.933, 0.9, 0.87 and with rated Anb (area of first-stage turbine nozzle) or Anb decreased by 12%; (3)tests of static-forced surge(decreasing the area of engine nozzle very very slowly)and dynamic-forced surge for an engine with"clean" or distorted inlet flow. The results from the tests comprise.
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