Numerical investigation of flow control in low-pressure turbine cascade using Gurney Flaps

IF 0.7 4区 工程技术 Q4 ENGINEERING, AEROSPACE
Mohan Agrawal, Jai Bhan Verma, G. Joshi, S. Chandel, Ved Prakash, R. K. Mishra
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Abstract

Abstract This paper reports the numerical investigations to analyze the effect of the application of Gurney Flaps on various configurations in a Low-Pressure Turbine (LPT) cascade in mitigating the laminar flow separation during low Reynolds number operations. T106 LPT blade of chord 60 mm has been selected for the present study. Gurney Flaps of flat type and quarter round type of a particular height of the chord length are selected. Flaps are provided near the blades’ trailing edges for numerical analysis. The numerical computations are performed using STARCCM+ software, and the K-ω SST turbulence Model is used for turbulence closure. The studies are performed at various Reynolds numbers ranging from 37,500 to 138,750 to understand the application of various configurations of Gurney Flap vis a vis turbine blade without Gurney Flap. Performance parameters such as lift coefficient, drag coefficient, aerodynamic efficiency, and static pressure distributions over the blade surface are used to analyse the alterations in the performance of aerodynamic characteristics of the LPT Blade. All the Gurney Flap configurations improved the overall blade aerodynamics. Among these configurations, the flat Gurney Flap configuration is found to be superior as it improves the aerodynamic efficiency of the blade.
利用轮尼襟翼控制低压涡轮叶栅流动的数值研究
摘要本文通过数值研究,分析了在低压涡轮(LPT)叶栅中不同构型的轮尼襟翼的应用对减轻低雷诺数运行时层流分离的影响。本研究选用弦型60mm的T106 LPT叶片。选择和弦长度的特定高度的平型和四分之一圆型轮盖。在叶片后缘附近设置了襟翼,以便进行数值分析。数值计算采用STARCCM+软件进行,湍流闭合采用K-ω SST湍流模型。研究在37,500到138,750的不同雷诺数下进行,以了解不同配置的轮尼襟翼对无轮尼襟翼的涡轮叶片的应用。利用升力系数、阻力系数、气动效率、叶片表面静压分布等性能参数分析LPT叶片气动特性性能的变化。所有的轮尼襟翼配置都改善了叶片的整体空气动力学。在这些配置中,平轮尼襟翼配置被发现是优越的,因为它提高了叶片的气动效率。
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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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