Development and prospect of Controlled Diffusion Airfoils for Multistage Compressor Part Ⅰ:Design and Development of Controlled Diffusion Airfoils
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Development and prospect of Controlled Diffusion Airfoils for Multistage Compressor Part Ⅰ:Design and Development of Controlled Diffusion Airfoils
Vol. 16, Issue 3, (2001)
作者机构:
哈尔滨工业大学241教研室,北京,100083
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Published:2001
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ZHONG Jing-jun, WANG Hui-she, WANG Zhong-qi. Development and prospect of Controlled Diffusion Airfoils for Multistage Compressor Part Ⅰ:Design and Development of Controlled Diffusion Airfoils[J]. 2001, 16(3).
DOI:
ZHONG Jing-jun, WANG Hui-she, WANG Zhong-qi. Development and prospect of Controlled Diffusion Airfoils for Multistage Compressor Part Ⅰ:Design and Development of Controlled Diffusion Airfoils[J]. 2001, 16(3).DOI:
Development and prospect of Controlled Diffusion Airfoils for Multistage Compressor Part Ⅰ:Design and Development of Controlled Diffusion Airfoils
The optimum design of Controlled Diffusion Airfoils (CDA) is one of the main research fields in subsonic and transonic profile design for multistage compressor.This paper reviews the necessity of CDA research
the background of CDA development
the features and design methods of first generation CDA and the second generation CDA with consideration of cascade endwall flow.The CDA is originated from the supercritical airfoil.Controlling the diffusion on the suction surface of an airfoil
can eliminate or decrease the shock wave
reduce the loss and enlarge the range of incidence.Around this criterion of airfoil design
many design methods have been proposed
which can be classified into inverse method and direct method.The CDA research in China started later than many other countries
and concentrated mainly on its principles and design methods.
Development of Controlled Diffusion Airfoils for Multistage Compressor Application Part 2 Test and Numerical Simulation of Controlled Diffusion Airfoils
Design method and its misaligned contact characteristic of aviation crowned spline
Design and verification of engine air particle separator for vehicle gas turbine engine
A design method for high efficiency propeller
Modified axisymmetric basic flowfield for hypersonic inward turning inlet
Related Author
WANG Zhong qi
ZHONG Jing jun
WANG Hui she
Mengru WANG
Changqing SU
Yongquan WANG
Zhifei FENG
Guang ZHAO
Related Institution
Harbin Institute of Technology
Shenyang Engine Research Institute,Aero Engine Corporation of China
Key Laboratory for Power Transmission Technology of Aero⁃Engine,Aero Engine Corporation of China
School of Energy and Power Engineering,Dalian University of Technology