导航

Acta Aeronautica et Astronautica Sinica ›› 2024, Vol. 45 ›› Issue (19): 630565.doi: 10.7527/S1000-6893.2024.30565

• Uncertainties in Aerothermodynamics of Aero-engine • Previous Articles    

Influence of geometric variation on aerodynamic performance of controlled diffusion airfoil

Dejun MENG1,2(), Wenbin SHI2, Jiaxin LIU3,4, Pengfei XU2, Dingxi WANG1, Xianjun YU3   

  1. 1.National Elite Institute of Engineering,Northwestern Polytechnical University,Xi’an 710072,China
    2.AECC Shenyang Engine Research Institute,Shenyang 110015,China
    3.Research Institute of Aero-Engine,Beihang University,Beijing 102206,China
    4.CAAC Airworthiness Certification Center,Beijing 100102,China
  • Received:2024-04-22 Revised:2024-05-13 Accepted:2024-06-17 Online:2024-10-15 Published:2024-07-01
  • Contact: Dejun MENG E-mail:762406405@qq.com
  • Supported by:
    National Level Project

Abstract:

This paper conducts research on the law and mechanism of influence of local geometric variations on airfoil performance. The Hicks-Henne function is used to model the contour variation and contour gradient variation of Controlled Diffusion Airfoil (CDA) to perform S1 stream surface numerical calculation. The calculation results indicate that the trend of variation of blade performance with positive and negative airfoil contour variation amplitude is symmetrical, when airfoil contour gradient variation is small. However, when airfoil contour gradient variation is large, both positive and negative airfoil contour variations lead to a decrease in airfoil performance, and influence of positive variations surpasses that of negative variations. Boundary layer separation and even transition in advance caused by geometric variations is the major reason for the decrease in airfoil performance. Based on the research results, the sensitive regions for CDA are established, which are within 5% chord from the leading edge and the suction surface before boundary layer transition. The variation sensitive regions are conducive to improving processing tolerance criteria and reducing the aerodynamic performance risk of compressors.

Key words: controlled diffusion airfoil, airfoil contour, airfoil contour gradient, loss, incidence angle range

CLC Number: