Design of a Sector Cascade Applied in the Middle Stage of a Compressor Test Rig

作     者：WANG Jiayu HU Jun JIANG Chao LI Jun WANG Jiayu;HU Jun;JIANG Chao;LI Jun

作者机构：College of Energy and Power EngineeringNanjing University of Aeronautics and AstronauticsNanjing 210016China Jiangsu Province Key Laboratory of Aerospace Power SystemNanjing 210016China 

出 版 物：《Journal of Thermal Science》 (热科学学报（英文版）)

年 卷 期：2022年第31卷第2期

页      面：485-494页

核心收录：

学科分类：08[工学] 082503[工学-航空宇航制造工程] 0805[工学-材料科学与工程（可授工学、理学学位）] 0825[工学-航空宇航科学与技术] 0702[理学-物理学] 

基　　金：supported by the National Science and Technology Major Project(2017-Ⅱ-0004-0017)。 

主　　题：sector cascade compressor test platform 3-D printing 

摘      要：A compressor test platform was designed in the purpose of easy assembly and cost-saving tests.New design concepts were firstly used on the test platform and iterative revisions were conducted to verify the effects,which decrease the risk of applying to the full annulus directly.The platform was a sector cascade that can be inserted into an otherwise full stator annulus,with a set of exchangeable endwall casing and blades manufactured by 3-D printing.The platform can create an operating condition which is closer to engine-realistic flow conditions than traditional cascade tests.The flow field of the prototype stator was tested in detail at the operating point and showed some flow defects in the tip region,and then three design plans were conducted to experimentally investigate which design concept could improve the blade tip flow.The concept of casing endwall profiling was the most effective one which markedly depressed the separation of the tip region and decreased the total pressure loss coefficient.The test results show that the design of the test platform was successful and promising,which could be used to conduct more researches on the flow mechanism of the middle stage.