Expanding the choke margin of a mixed flow compressor stage for a micro gas turbine engine

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2023-02-22 DOI:10.1515/tjj-2022-0060

Hano van Eck, S. J. van der Spuy, A. Gannon

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Abstract

Abstract In an attempt to reduce engine frontal area, while maintaining a high single stage pressure ratio, mixed flow compressor stages are frequently used in micro gas turbine (MGT) engines. The expansion of the choke margin of such a mixed flow compressor is presented. The use of a crossover diffuser configuration in a mixed flow compressor stage has displayed superior performance results compared to legacy diffuser configurations, especially when geometric restrictions are enforced. A disadvantage of a crossover diffuser configuration is that it typically displays an inferior operating range compared to legacy diffuser configurations. In an attempt to expand the choke margin of a MGT mixed flow compressor, the use of tandem and splitter vane crossover diffuser configurations was evaluated. It was found that a low solidity first vane row configuration provided a 3% increase in choke margin. A splitter vane crossover diffuser configuration provided a 5.9% increase in choke margin. A tandem vaned diffuser with a reduced first row vane number provided a 7.8% increase in choke margin.

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微型燃气涡轮发动机混流压气机级节流裕度的扩大

摘要为了在保持高单级压力比的同时减少发动机的前部面积，混流式压缩机级经常用于微型燃气轮机（MGT）发动机。介绍了这种混流式压缩机节流裕度的扩展。与传统扩散器配置相比，在混流压缩机级中使用交叉扩散器配置显示出优越的性能结果，尤其是在实施几何限制时。交叉扩散器配置的缺点是，与传统扩散器配置相比，它通常显示较差的工作范围。为了扩大MGT混流式压缩机的阻风门裕度，对串联和分流叶片交叉扩压器配置的使用进行了评估。研究发现，低固体度的第一排叶片结构使节流裕度增加了3%。分流叶片交叉扩压器配置使节流裕度增加了5.9%。具有减少的第一排叶片数量的串联叶片扩散器提供了7.8%的节流裕度增加。

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.