Date of Award

Spring 5-2016

Access Type

Thesis - Open Access

Degree Name

Master of Science in Aerospace Engineering

Department

Aerospace Engineering

Committee Chair

Mark Ricklick

First Committee Member

Sandra K.S. Boetcher

Second Committee Member

Magdy Attia

Abstract

This study attempts to improve the trailing edge protection of a turbine vane by incorporating two concepts from the literature. These two concepts are optimized near wall cooling passages and a triple-impingement configuration in the vane trailing edge. Finally this study explores a CFD conjugate analysis based on the Shear Stress Transport k(l) turbulence model. The overall goal is to produce a more effective cooling configuration by studying the effects of the flow and heat transfer of the dual configuration, while keeping the integrity of the turbine vane. Star-CCM+ was utilized to carry out the computational data on a 3-D model of the NASA C3X turbine vane. The analysis compared the temperature and the overall heat transfer coefficient to several data sets from the literature t the vane mid span with a heavy emphasis on the trailing edge portion of turbine vane. Results are generated to show the nature of the flow induced by the coupled system and the thermomechanical performance and the efficiency of the turbine vane. The triple impingement configuration displayed a cooler average temperature distribution of 18.8% than the original NASA C3X vane and a slightly cooler temperature of 2.2% than the original micro-cooling configuration from the literature. Strictly the back 1/3rd of the vane for the triple impingement configuration produced a 2.8%-3.3% cooler average temperature than the original micro-cooling configuration and a 14.7%-18.95% cooler vane than the original NASA C3X vane. The results have the likely hood to produce a tremendous cost savings for an industry utilizing cooling configurations for turbine application.

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