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ISSN Online: 2377-424X

International Heat Transfer Conference 12
August, 18-23, 2002, Grenoble, France

Heat Transfer and Pressure Distributions on A Gas Turbine Vane End-Wall

Get access (open in a dialog) DOI: 10.1615/IHTC12.5360
6 pages

Abstract

Gas turbines are extensively used for aircraft propulsion, land-based power generation and industrial applications. Thermal efficiency and power output of gas turbines increase with increasing turbine inlet temperature. The current turbine inlet temperature level in advanced gas turbines is far above the melting point of the blade material. Therefore, a sophisticated cooling scheme must be developed for continuous safe operation of gas turbines with high performance. To design an effective cooling system, it is necessary to better understand the detailed hot gas flow physics within the turbine stages. This study focuses on the detailed heat transfer coefficient distributions on a gas turbine vane end-wall region. Heat Transfer coefficient and Static pressure distributions are experimentally investigated on a gas turbine vane end-wall in a five-vane linear cascade. The vane is the 2-dimentional model of a GE-E3 first stage gas turbine stator vane. The flow condition in the test cascade corresponds to an exit Reynolds number based on axial chord of 500,000. Both heat transfer and pressure measurements on the vane endwall region are made at two different turbulence intensity levels of 6.8% and 10.8% at the cascade inlet. Detailed heat transfer coefficient distributions on the vane end-wall region are measured using a hue detection based transient liquid crystal technique. Results show various regions of high and low heat transfer coefficient on the vane endwall surface due to several types of endwall secondary flows and vortices. Heat transfer coefficient increases with increasing turbulence intensity level at the cascade inlet. These detailed heat transfer coefficient distributions provide important information in designing an effective film-cooling scheme in order to prevent the vane endwall region from overheating by combustor hot gas stream.