总体冷却效率与温度比的基本原理

IF 1.9 3区工程技术 Q3 ENGINEERING, MECHANICAL

Journal of Turbomachinery-Transactions of the Asme Pub Date : 2023-10-10 DOI:10.1115/1.4063730

James Cartlidge, Thomas Povey

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引用次数: 0

摘要

摘要本文研究了典型高压喷嘴导叶(HPNGV)冷却系统的整体冷却效率(即所谓的金属效率)与主流与冷却剂总温比(TR)之间的关系。研究的温比范围是典型实验条件(TR = 1.2)与典型发动机条件(TR = 2.0)之间的温比范围。其目的有两个:首先，量化实验工况和发动机工况的总体冷却效率差异;其次，了解差异的物理基础，根据五种局部表面边界条件的变化进行分离。我们使用定制的共轭热模型来实现这一点，该模型包括内部冷却和外部膜冷却层的模型。研究了三种典型的冷却结构。结果允许在不同温度比条件下的情况进行比较和缩放。

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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FUNDAMENTALS OF SCALING OF OVERALL COOLING EFFECTIVENESS WITH TEMPERATURE RATIO

Abstract In this paper we study the relationship between overall cooling effectiveness (or so-called metal effectiveness) and mainstream-to-coolant total temperature ratio (TR), for typical high-pressure nozzle guide vane (HPNGV) cooling systems. The temperature ratio range studied is that between typical experimental conditions (TR ≅ 1.2) and typical engine conditions (TR ≅ 2.0). The purpose is twofold: firstly, to quantify the difference in overall cooling effectiveness between experimental and engine conditions of temperature ratio; and—secondly—to understand the physical bases for the difference, separated in terms of changes in five local surface boundary conditions. We do this using a bespoke conjugate thermal model which includes models of both the internal cooling and the external film cooling layer. Three typical cooling architectures are studied. The results allow comparison and scaling between situations at different conditions of temperature ratio.

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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.