Unsteady film cooling characteristics of the high-pressure turbine shroud with blade rotation in an aero-engine

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2022-07-11 DOI:10.1515/tjj-2021-0032

Z. Kou, Zihao Bao, Guang-chao Li, Xunyan Yin

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引用次数: 1

Abstract

Abstract Three-dimensional unsteady numerical simulations were conducted to investigate the detailed film cooling mechanism of the high-pressure turbine shroud with the first-stage turbine blade and guide vane for an aero-engine under the high-speed rotation of blades and rotor-stator interaction. The slip mesh was used to realize the relative motion between the rotating blade and the stationary turbine shroud. It is found that the coolant jet is alternately influenced by the hot mainstream, tip clearance leakage flow and leakage vortex due to the high rotational speed of blades. The film cooling characteristics of the turbine shroud significantly present an unsteady and periodic flow and heat transfer phenomenon. The insufficient cooling margin for film holes at the upstream of the blade leading edge can occur not only under high blowing ratios due to the coolant jet liftoff, but also at low blowing ratios due to the insufficient coolant flow rate as a result of the high exit pressure. A novel shroud cooling structure with coolant supply by the added throttle chamber is put forward, and expected to provide better thermal protection for the high-pressure turbine shroud near the leading edge of blades with no extra increase in the total mass flow rate of coolant.

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航空发动机叶片旋转高压涡轮护罩的非定常膜冷却特性

摘要通过三维非定常数值模拟，研究了航空发动机高压涡轮护罩在叶片高速旋转和转子-定子相互作用下，带一级涡轮叶片和导叶的薄膜冷却机理。滑动网格用于实现旋转叶片和固定涡轮护罩之间的相对运动。研究发现，由于叶片转速较高，冷却剂射流交替受到热主流、叶尖间隙泄漏流和泄漏涡流的影响。涡轮护罩的膜冷却特性显著地呈现出不稳定和周期性的流动和传热现象。叶片前缘上游的膜孔的冷却裕度不足不仅可能发生在由于冷却剂射流升空而导致的高吹风比下，而且可能发生在因为高出口压力而导致的冷却剂流速不足而导致的低吹风比下。提出了一种通过增加节流室提供冷却剂的新型围带冷却结构，并希望在不增加冷却剂总质量流量的情况下，为叶片前缘附近的高压涡轮围带提供更好的热保护。

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.