连续性和非连续性鼓包对跨声速压气机转子气动性能的影响

杨旭东, 韩吉昂, 郭重佳, 杨嗣涵, 胡义, 钟兢军

doi:10.16411/j.cnki.issn1006-7736.2024.01.016

大连海事大学学报 >

2024 , Vol. 50 >Issue 1: 143 - 157

DOI: https://doi.org/10.16411/j.cnki.issn1006-7736.2024.01.016

连续性和非连续性鼓包对跨声速压气机转子气动性能的影响

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(1.大连海事大学船舶与海洋工程学院，辽宁大连 116026; 2.上海海事大学商船学院，上海 201306)

杨旭东（1998 — ），男，硕士生，研究方向：发动机气动热力学。韩吉昂*（1979 — ），男，博士，教授，博士生导师，E-mail：hja@dlmu.edu.cn。郭重佳（1996 — ），男，博士生，研究方向：发动机气动热力学。杨嗣涵（1999 — ），男，硕士生，研究方向：发动机气动热力学。胡义（1994 —），男，博士生，研究方向：发动机气动热力学。钟兢军（1963 —），男，博士，教授，博士生导师，研究方向：发动机气动热力学。

收稿日期: 2023-07-24

修回日期: 2023-09-25

录用日期: 2023-09-25

网络出版日期: 2023-09-25

基金资助

国家自然科学基金重点项目（52236005）；航空发动机及燃气轮机基础科学中心重点项目(P2022-B-Ⅱ-007-001)。

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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

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摘要

为研究鼓包对跨声速压气机转子气动性能的影响，以NASA Rotor 37作为研究对象，在其吸力面上布置展向连续性和非连续性的鼓包，并采用数值模拟方法研究了原型转子和鼓包转子变转速工况下的流场结构和气动性能。结果表明：设计转速和110%设计转速下，连续性鼓包对叶顶附近的激波控制效果较好，可以对激波前气体进行预压缩，从而降低激波前后的逆压梯度，减弱激波强度，进而减小激波相关损失。在设计转速最高效率工况下，非连续性鼓包转子总压比提升0.236%，效率提升0.309%；连续性鼓包转子总压比提升0.285%，效率提升0.454%。50%、60%和90%设计转速下，鼓包并没有起到明显的有益效果。

关键词： 跨声速压气机转子; 连续性鼓包; 非连续性鼓包; 气动性能; 变转速工况

本文引用格式

杨旭东, 韩吉昂, 郭重佳, 杨嗣涵, 胡义, 钟兢军 . 连续性和非连续性鼓包对跨声速压气机转子气动性能的影响[J]. 大连海事大学学报, 2024 , 50(1) : 143 -157 . DOI: 10.16411/j.cnki.issn1006-7736.2024.01.016

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.

Key words： transonic compressor rotor; continuous bump; individual bump; aerodynamic performance; variable speed conditions

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