Film Cooling Modeling in a Turbine Working under the Unsteady Exhaust Flow of Pulsed Detonation Combustion

Gokkul Raj Varatharajulu Purgunan (), Majid Asli, Teodosio Nacci, Daniela Anna Misul, Simone Salvadori and Panagiotis Stathopoulos
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Gokkul Raj Varatharajulu Purgunan: Institute of Fluid Mechanics and Technical Acoustics, Technische Universität Berlin, 10623 Berlin, Germany
Majid Asli: Chair of Aeroengine Design, Brandenburg University of Technology Cottbus-Senftenberg, 03046 Cottbus, Germany
Teodosio Nacci: Department of Energy (DENERG), Politecnico di Torino, 10129 Turin, Italy
Daniela Anna Misul: Department of Energy (DENERG), Politecnico di Torino, 10129 Turin, Italy
Simone Salvadori: Department of Energy (DENERG), Politecnico di Torino, 10129 Turin, Italy
Panagiotis Stathopoulos: Institute of Low Carbon Industrial Processes, German Aerospace Center (DLR), 51147 Cottbus, Germany

Energies, 2024, vol. 17, issue 6, 1-20

Abstract: Pressure gain combustors (PGCs) have demonstrated significant advantages over conventional combustors in gas turbine engines by increasing the thermal efficiency and reducing the pollution emission level. PGCs use shock waves to transfer energy which contributes to the increase in outlet total pressure. One of the major obstacles in the actual implementation of PGCs in the gas turbine cycle is the exploitation of the highly unsteady flow of the combustor outlet with the downstream turbine. Because of the higher outlet temperature from the PGCs, the turbine blade cooling becomes essential. Due to the highly fluctuating unsteady flow of PGCs, 3D CFD simulation of turbines becomes very expensive. In this work, an alternative approach of using a 1D unsteady Euler model for the turbine is proposed. One of the novel aspects of this paper is to implement the turbine blade cooling in the unsteady 1D Euler model. The main parameters required for the turbine blade cooling are the cooling air mass flow rate, temperature, and pressure. Due to the introduction of coolant flow, the blades are no longer adiabatic and the mass flow rate across the turbine is not constant. Comparing the 1D Euler results against zero-dimensional calculation and 3D CFD approach showed a very good match for both steady and unsteady simulations confirming the applicability of the 1D method.

Keywords: pressure gain combustor; turbomachinery; unsteady interaction; film cooling; Euler equations; computational fluid dynamics (search for similar items in EconPapers)
JEL-codes: Q Q0 Q4 Q40 Q41 Q42 Q43 Q47 Q48 Q49 (search for similar items in EconPapers)
Date: 2024
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