Impact investigation of inlet environmental changes on the rated condition performance of a high-pressure compressor

IF 0.7 4区 工程技术 Q4 ENGINEERING, AEROSPACE
Q. Wang, Zhourong Zhang, Shuning Xiao, Qingsong Hong
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引用次数: 0

Abstract

Abstract The variations of inlet environment parameters can make significant effects on the compressor performance. This paper aims to investigate the effects of inlet total pressure and total temperature changes on the rated condition performance of a nine-stage HPC. Different cases of total pressure and total temperature boundary conditions at this compressor inlet are studied by 3-D numerical simulations with experimental validations. The numerical results confirm that the variations of inlet total pressure and total temperature make different effects on the rated condition performance of compressor. The overall performance parameters, such as the corrected mass flow and isentropic efficiency, will increase with inlet total pressure increasing and decrease with inlet total temperature increasing by different change rules. The flow similarity is also investigated by comparing the calculated results of critical quantities in different cases. The results indicate that the rising inlet total pressure can increase the Reynolds number and it is beneficial to reduce the viscous influence so that it is available to improve the performance; the rising inlet total temperature can decrease both the specific heat ratio and Reynolds number so that it will lead to the compressor performance decline inevitably.
进口环境变化对高压压气机额定工况性能的影响研究
进气环境参数的变化会对压缩机的性能产生显著影响。本文旨在研究入口总压力和总温度变化对九级HPC额定工况性能的影响。通过三维数值模拟和实验验证,研究了该压缩机入口总压力和总温度边界条件的不同情况。数值结果表明,入口总压力和总温度的变化对压缩机的额定工况性能有不同的影响。修正后的质量流量和等熵效率等整体性能参数会随着入口总压的增加而增加,而随着入口总温度的增加而减少,其变化规律不同。通过比较不同情况下临界量的计算结果,研究了流量的相似性。结果表明,入口总压的升高可以增加雷诺数,有利于减小粘性影响,从而有利于提高性能;入口总温度的升高会降低压缩机的比热比和雷诺数,从而不可避免地导致压缩机性能的下降。
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
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
36
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.
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