Conjugate heat transfer characteristics of a film-cooled turbine blade leading edge with staggered-oblique impinging jets

IF 1.9 3区工程技术 Q3 ENGINEERING, MECHANICAL

Journal of Turbomachinery-Transactions of the Asme Pub Date : 2023-09-07 DOI:10.1115/1.4063367

Hongye Li, Qiang Du, Qingzong Xu, Guangyao Xu, Haoyang Liu, Dawei Chen

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Abstract

To improve the cooling performance, a novel impingement scheme is proposed to be used in a film-cooled turbine blade leading edge. Different from a normal one, the novel scheme consists of two rows of staggered impinging jets at oblique angles of ±35°, and is thus named as the staggered-oblique impingement scheme. A conjugated numerical investigation is carried out to illustrate the underlying mechanisms of the cooling performance. Three typical jet Reynolds numbers, 6000, 12000, and 18000, are studied using the validated SST k-ω turbulence model. Numerical results show a flow separation within the staggered-oblique impinging jets, which causes the discharge coefficient for the novel impingement scheme lower. Results also reveal a phenomenon difference that two symmetric vortices are induced by each normal impinging jet, while only one vortex appears on the acute angle side along with each staggered-oblique impinging jet. The flow fields of the staggered-oblique impingement scheme create a more uniform heat transfer distribution and a maximum of 23.7% higher area-averaged Nusselt number than the normal impingement scheme. The area-averaged overall cooling effectiveness for the novel scheme is higher than the normal one by a maximum of 4.8%. The uniformity and the enhancement of the overall cooling effectiveness arise from the wall jet being fully developed. The adiabatic cooling effectiveness is similar for both impingement schemes. This indicates that the improvement in overall cooling effectiveness for the staggered-oblique impingement scheme mainly arises from internal heat transfer.

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具有交错倾斜撞击射流的膜冷却涡轮叶片前缘的共轭传热特性

为了提高冷却性能，提出了一种新的冲击方案，用于膜冷却涡轮叶片前缘。与常规方案不同，该方案由两排倾斜角度为±35°的交错撞击射流组成，因此被称为交错倾斜撞击方案。进行了共轭数值研究，以说明冷却性能的潜在机制。使用经验证的SST k-ω湍流模型研究了三个典型的射流雷诺数，即6000、12000和18000。数值结果表明，在交错倾斜撞击射流中存在流动分离，这导致新型撞击方案的流量系数较低。结果还揭示了一种现象差异，即每个正常的撞击射流都会产生两个对称的涡流，而随着每个交错的倾斜撞击射流，只有一个涡流出现在锐角侧。交错倾斜冲击方案的流场产生了更均匀的传热分布，并且与正常冲击方案相比，面积平均努塞尔数最多高23.7%。新方案的面积平均整体冷却效率比常规方案高出4.8%。均匀性和整体冷却效率的提高源于壁面射流的充分发展。两种冲击方案的绝热冷却效果相似。这表明，交错斜向冲击方案的整体冷却效率的提高主要来自内部传热。

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

Journal of Turbomachinery-Transactions of the Asme 工程技术-工程：机械

CiteScore

4.70

自引率

11.80%

发文量

168

审稿时长

9 months

期刊介绍： The Journal of Turbomachinery publishes archival-quality, peer-reviewed technical papers that advance the state-of-the-art of turbomachinery technology related to gas turbine engines. The broad scope of the subject matter includes the fluid dynamics, heat transfer, and aeromechanics technology associated with the design, analysis, modeling, testing, and performance of turbomachinery. Emphasis is placed on gas-path technologies associated with axial compressors, centrifugal compressors, and turbines. Topics: Aerodynamic design, analysis, and test of compressor and turbine blading; Compressor stall, surge, and operability issues; Heat transfer phenomena and film cooling design, analysis, and testing in turbines; Aeromechanical instabilities; Computational fluid dynamics (CFD) applied to turbomachinery, boundary layer development, measurement techniques, and cavity and leaking flows.