Numerical study on flow control mechanism of endwall fence in a high-lift turbine rotor with open separation

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology Pub Date : 2024-10-04 DOI:10.1016/j.ast.2024.109651

Hang Yuan , Caiyan Chen , Hanliu Deng , Xiaoying Sheng , Xingen Lu , Yanfeng Zhang

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引用次数: 0

Abstract

The enhanced cross pressure gradient and the interference effect between secondary flow and separation bubble on the suction side make the refinement of flow organization in the endwall region a key role in improving the performance of low Reynolds number turbine stages. This influence is further amplified in high-lift turbines with open separation. The flow control method of applying endwall fence on a high-lift rotor of a low-speed turbine stage has been numerically studied. By analyzing the transformation of separation bubble on the suction surface and the development of vortices in the endwall region, the flow control mechanism of the endwall fence at low Reynolds numbers is presented. The influence of different fence design parameters on aerodynamic performance has been summarized. The research results indicate that the induced generation of fence vortex can effectively suppress passage vortex. After installing the fence, the intensification of blockage in the endwall region near the leading edge effectively delays the occurrence of laminar separation. Due to the introduction of additional endwall losses, the flow control effect of the fence mainly comes from the suppression of separation. The flow field in the endwall region and flow control effect are significantly affected by the pitchiwse position and height of the fence, while the width of the fence has a slight impact. The flow control effect can be more effectively achieved by designing the height variation of the fence reasonably. In addition, numerical results indicate that the optimized fence all exhibit good control effectiveness under different operating conditions.

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开放式分离的高扬程涡轮转子端壁栅栏流动控制机制的数值研究

交叉压力梯度的增强以及吸入侧二次流与分离气泡之间的干扰效应，使得端壁区域流动组织的细化成为提高低雷诺数涡轮级性能的关键因素。在采用开放式分离的高扬程涡轮机中，这种影响会进一步扩大。对在低速涡轮级的高扬程转子上应用端壁栅栏的流动控制方法进行了数值研究。通过分析分离气泡在吸气面上的变化和涡流在端壁区的发展，提出了端壁栅栏在低雷诺数下的流动控制机制。总结了不同栅栏设计参数对气动性能的影响。研究结果表明，栅栏涡流的诱导生成可以有效抑制通道涡流。安装栅栏后，前缘附近端壁区域阻塞的加剧有效延迟了层流分离的发生。由于引入了额外的端壁损失，栅栏的流动控制效果主要来自于对分离的抑制。内壁区域的流场和流量控制效果受栅栏的俯仰位置和高度影响较大，而栅栏的宽度影响较小。通过合理设计栅栏的高度变化，可以更有效地达到控流效果。此外，数值结果表明，优化后的栅栏在不同运行条件下均表现出良好的控制效果。

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

Aerospace Science and Technology 工程技术-工程：宇航

CiteScore

10.30

自引率

28.60%

发文量

654

审稿时长

54 days

期刊介绍： Aerospace Science and Technology publishes articles of outstanding scientific quality. Each article is reviewed by two referees. The journal welcomes papers from a wide range of countries. This journal publishes original papers, review articles and short communications related to all fields of aerospace research, fundamental and applied, potential applications of which are clearly related to: • The design and the manufacture of aircraft, helicopters, missiles, launchers and satellites • The control of their environment • The study of various systems they are involved in, as supports or as targets. Authors are invited to submit papers on new advances in the following topics to aerospace applications: • Fluid dynamics • Energetics and propulsion • Materials and structures • Flight mechanics • Navigation, guidance and control • Acoustics • Optics • Electromagnetism and radar • Signal and image processing • Information processing • Data fusion • Decision aid • Human behaviour • Robotics and intelligent systems • Complex system engineering. Etc.