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

  • 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 thePressure 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.show moreshow less

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Author: Gokkul Raj Varatharajulu Purgunan, Majid AsliORCiD, Teodosio Nacci, Daniela Anna Misul, Simone SalvadoriORCiD, Panagiotis Stathopoulos
URL:https://www.mdpi.com/1996-1073/17/6/1312
DOI:https://doi.org/10.3390/en17061312
ISSN:1996-1073
Title of the source (English):Energies
Document Type:Scientific journal article peer-reviewed
Language:English
Year of publication:2024
Tag:Cooling; Pressure gain combustion; Turbomachinery
Volume/Year:17
Issue number:6
First Page:1
Last Page:20
EU-Project number / Contract (GA) number:956803
Article number:1312
Fundername (EU):Marie Skłodowska-Curie
Way of publication:Open Access
Faculty/Chair:Fakultät 3 Maschinenbau, Elektro- und Energiesysteme / FG Flug-Triebwerksdesign
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