Cooling of Turbine Stator Blade using Air Cycle Machine

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V. Siva
A. Haritha
S. Akash
L. Haran

Abstract

Gas turbines have been widely used in power generation and aircraft propulsion. The turbine inlet temperature may be elevated than the metal melting point for improving the gas turbine performance. Therefore, cooling of gas turbines becomes very critical for engine operation and safety. Blade cooling is an important parameter in order to increase the turbine blade life for reaching a temperature. To combat and avert failure of turbine blades in gas turbine engines resulting from the excessive operating temperatures, film cooling has been incorporated into blade designs. Normally in film cooling, cool air is bled from the compressor stage. In this work, the cool air will bleed from the air cycle machine’s output and ducted to the internal chambers of the turbine stator blades and discharged through small holes. Air cycle machine output temperature range from 10°C to -20°C. Analysis for the turbine stator blade for this temperature can be done with many cases in the Autodesk CFD.

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