Effect of the distribution of the upstream probe support on performance of compressor cascade

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2022-11-04 DOI:10.1515/tjeng-2022-0027

Kuanxin Hou, H. Xiang, Jie Gao, Binbin Lin, Qiulin Dai, Yao Fu, Yong Yang, Lei Huang

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Abstract

Abstract Aiming at the problem of aerodynamic coupling interference between disturbance of the built-in measurement probe and internal flow of high load compressor, the experiment of axial position and structure dimension of cylindrical probe support effect on the performance of the compressor cascade was carried out on the transonic plane cascade test facility. The effect characteristics of the distribution of probe support on aerodynamic performance of downstream cascade under different inlet Mach numbers were analyzed through the experimental data. The experimental results show that the axial position of probe support has little impact on the total pressure loss coefficient of cascade under the low-speed inlet flow condition. However, the variety of the axial position of probe support has a great impact on the total pressure loss coefficient of cascade under the high-speed inlet flow condition. With the decrease of the axial distance between probe support and cascade, the total pressure loss coefficient of cascade increases. Under different inlet flow conditions, the variety of the structure dimension of probe support has a significant impact on the total pressure loss coefficient of cascade. With the increase of the structure dimension of probe support, the total pressure loss coefficient of cascade increases.

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上游探针支架分布对压气机叶栅性能的影响

摘要针对内置测量探头的扰动与高负荷压气机内部流动之间的气动耦合干扰问题，在跨声速平面叶栅试验装置上进行了圆柱探头支撑的轴向位置和结构尺寸对压气机叶栅性能影响的实验。通过实验数据，分析了不同进口马赫数下探针支撑分布对下游叶栅气动性能的影响特性。实验结果表明，在低速进气条件下，探针支架的轴向位置对叶栅总压损失系数的影响很小。然而，在高速入口流动条件下，探针支架轴向位置的变化对叶栅的总压损失系数有很大影响。随着探针支架与叶栅轴向距离的减小，叶栅总压损失系数增大。在不同的入口流量条件下，探针支架结构尺寸的变化对叶栅总压损失系数有显著影响。随着探针支架结构尺寸的增大，叶栅总压损失系数增大。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

International Journal of Turbo & Jet-Engines 工程技术-工程：宇航

CiteScore

1.90

自引率

11.10%

发文量

审稿时长

6 months

期刊介绍： The Main aim and scope of this Journal is to help improve each separate components R&D and superimpose separated results to get integrated systems by striving to reach the overall advanced design and benefits by integrating: (a) Physics, Aero, and Stealth Thermodynamics in simulations by flying unmanned or manned prototypes supported by integrated Computer Simulations based on: (b) Component R&D of: (i) Turbo and Jet-Engines, (ii) Airframe, (iii) Helmet-Aiming-Systems and Ammunition based on: (c) Anticipated New Programs Missions based on (d) IMPROVED RELIABILITY, DURABILITY, ECONOMICS, TACTICS, STRATEGIES and EDUCATION in both the civil and military domains of Turbo and Jet Engines. The　International Journal of Turbo & Jet Engines　is devoted to cutting edge research in theory and design of propagation of jet aircraft. It serves as an international publication organ for new ideas, insights and results from industry and academic research on thermodynamics, combustion, behavior of related materials at high temperatures, turbine and engine design, thrust vectoring and flight control as well as energy and environmental issues.