ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Supersonic Compressor Blade Profile Design Method
Received date: 2013-06-17
Revised date: 2013-09-06
Online published: 2013-09-10
In order to make inlet Mach number and flow angle equal to a given value in the design of supersonic compressor blade profile, this paper presents a new blade profile parameterization method. The method is based on solving unique incidence classic method, and gives the relationship between the blade profile shape with unique incidence by analysis and formula derivation. The front part of blade profile is determined by the inlet Mach number and flow angle, and the other part is determined by blade profile characteristic parameters such as the throat area ratio, the small circle radius at the leading edge and trailing edge, the maximum deflection, the maximum thickness, etc. The method is used to design 6 supersonic compressor blade profiles. And Fluent is used to verify the design results. The results show that the design value of inlet Mach number and flow angle are consistent with the Fluent solution result (the maximum error of the Mach number is only 0.01, and the maximum error of the flow angle is only 0.7°); the parameterization method is easy to achieve compression by much oblique shock and a normal shock.
QIU Ming , ZHOU Zhenggui , LIU Longlong , CUI Cui . Supersonic Compressor Blade Profile Design Method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014 , 35(4) : 975 -985 . DOI: 10.7527/S1000-6893.2013.0384
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