Influence of continuous and individual bumps on aerodynamic performance of transonic compressor rotor

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  • (1. Naval Architecture and Ocean Engineering College, Dalian Maritime University, Dalian 116026, China;2. Merchant Marine College,Shanghai Maritime University,Shanghai 201306,China)

Received date: 2023-07-24

  Revised date: 2023-09-25

  Accepted date: 2023-09-25

  Online published: 2023-09-25

Abstract

In order to study the aerodynamic performance of the bumps in the transonic compressor rotor, NASA Rotor 37 is taken as the research object with the spanwise continuous and individual bumps configured on its suction surface. The flow field structure and aerodynamic performance of the prototype rotor and the bump rotors under variable speed conditions are studied by numerical simulation. The results show that under the design speed and 110 % design speed, the continuous bump has better control effect on the shock wave near the blade tip. The flow can be pre-compressed ahead of the shock wave, which helps decrease the pressure gradient of the shock wave. This results in a reduction of the shock wave strength and minimizes the loss of shock wave correlation. Under peak efficiency condition of the design speed, the total pressure ratio of the rotor with the spanwise individual bump is increased by 0.236 %, and the efficiency is increased by 0.309 %. The total pressure ratio of the rotor with the continuous bump is increased by 0.285 %, and the efficiency is increased by 0.454 %. Under 50 %, 60 % and 90 % of design speed, the bumps has no beneficial effect on the aerodynamic performance of the rotor.

Cite this article

YANG Xudong, HAN Ji’ang, GUO Chongjia, YANG Sihan, HU Yi, ZHONG Jingjun . Influence of continuous and individual bumps on aerodynamic performance of transonic compressor rotor[J]. Journal of Dalian Maritime University, 2024 , 50(1) : 143 -157 . DOI: 10.16411/j.cnki.issn1006-7736.2024.01.016

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