Turbine blade cooling simulation in the gas turbine engine simulation code getran
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A row-by-row turbine simulation model was developed for the dynamic engine simulation code, GETRAN, that incorporates heat transfer effects within the governing equations. The model permits the use of turbine blade cooling flow in the solution of the transient turbine performance characteristics. Several user-defined options are available in the final simulation module. These include heat transfer without blade cooling, heat transfer with blade cooling flow, and heat transfer with blade cooling where the cooling mass flow is injected into the main turbine flow. Mathematical modeling of the heat transfer in the turbine is accomplished in a "bulk flow" one-dimensional fashion. After successful integration of the new turbine solution method into the GETRAN code, several engine transient simulations were run for a small helicopter turboshaft engine to assess the performance of the heat transfer routine and examine the effects of turbine blade cooling (both with and without cooling mass flow injection) on engine performance. © 2003 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
author list (cited authors)
Greendyke, R. B., & Schobeiri, M. T.