会聚发散喷管超声速气膜冷却性能的详细研究

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2023-03-27 DOI:10.1515/tjj-2022-0080

Lingling Chen, Y. Shi, Haoqi Yang, Yalin Shi, Qingzhen Yang

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引用次数: 0

摘要

摘要本文对会聚发散喷管的超声速气膜冷却性能进行了数值研究，旨在探索和拓展实际工况下排气喷管高效冷却技术的知识。这项工作是用海温湍流模式的稳态RANS方法进行的。边界条件的选择是为了模拟真实的发动机工况。改变狭缝高度和进口压比，考察几何条件和流动条件对狭缝高度和进口压比的影响。对流场进行了详细的分析，研究了超声速二次流注入跨声速流动的现象。除了冷却效果外，还讨论了冷却工况下的推力系数和流量系数以及基准工况，以评估超音速冷却剂喷射对喷管性能的影响。该工作可为航空发动机排气喷嘴冷却方案的设计提供依据。

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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Detailed investigation of supersonic film cooling performance in a convergent divergent nozzle

Abstract This paper numerically studied supersonic film cooling performance in a convergent divergent nozzle, for the purpose of exploring and extending the knowledge of high-efficient cooling techniques for exhaust nozzles in real working conditions. The work was conducted with a steady state RANS approach with the SST turbulence model. The boundary conditions were chosen to mimic a real engine condition. The slot height and the inlet pressure ratio were varied to investigate the effect of the geometrical condition and flow condition. The flow field was analyzed in detail to study the phenomena of the supersonic secondary flow injected into the transonic flow. Besides the cooling effectiveness, the thrust coefficient and the discharge coefficient for the cooling cases were discussed together with the baseline case, to evaluate the influence of the supersonic coolant injection on the nozzle performance. The work can be a basis for the design of cooling schemes in an aero-engine exhaust nozzle.

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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.