Control mechanism of secondary flow in a turbine cascade with non-axisymmetric endwall profiling under Co-rotating incoming vortex

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2023-01-02 DOI:10.1515/tjj-2022-0063

Zhiyuan Cao, Chuxuan Wang, Jiantong Zhao, Xinyu Hao, Zhigao Song, Bo Liu

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引用次数: 1

Abstract

Abstract Upstream vortex has a significant effect on the secondary flow structure of the downstream turbine in the stage environment. This study investigates the secondary flow structure with non-axisymmetric endwall profiling (NAEW) under the interaction of co-rotating incoming vortex (Vic). A half-delta wing vortex generator is utilized to model Vic. The turbine cascade case which exhibited maximum reduction of the cascade loss with NAEW under no incoming vortex is studied. The mechanism of loss reduction with NAEW under the interaction of Vic is analysed. Vic could decrease the secondary flow near the endwall region by affecting the horseshoe vortex transport in the cascade. However, its loss reduction was lower than the loss increments of Vic itself. The arrival of Vic at the leading edge of the cascade increased the strength of the horseshoe vortex, resulting in a significant increase in loss. Under the interaction of Vic, NAEW decreased the blade loading near endwall region, which resulted in the reduction of cascade loss.

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共转来涡作用下非轴对称端壁型涡轮叶栅二次流控制机理

在级环境中，上游涡对下游涡轮二次流结构有重要影响。研究了非轴对称端壁型(NAEW)在共旋来涡(Vic)作用下的二次流结构。半三角翼涡发生器被用来模拟维克。研究了在无来流涡条件下，采用NAEW能最大程度降低叶栅损失的涡轮叶栅情况。分析了在Vic相互作用下NAEW减损的机理。Vic可以通过影响叶栅内马蹄涡输运来减少端壁附近的二次流。但其损失减少量低于Vic本身的损失增量。Vic在叶栅前缘的到来使马蹄涡的强度增加，造成损失的显著增加。在Vic的相互作用下，NAEW降低了端壁附近的叶片载荷，从而降低了叶栅损失。

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.