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Open AccessArticle

Parameterised Model of 2D Combustor Exit Flow Conditions for High-Pressure Turbine Simulations

1
Institute of Gas Turbines and Aerospace Propulsion, Technische Universität Darmstadt, Otto-Berndt-Straße 2, 64287 Darmstadt, Germany
2
Turbine Aerodynamics and Cooling, Rolls-Royce Deutschland Ltd. & Co. KG, 15827 Blankenfelde-Mahlow, Germany
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Author to whom correspondence should be addressed.
This paper is an extended version of our paper published in European Turbomachinery Conference ETC12, 2017, Paper No. 24.
Academic Editor: Peter Ireland
Int. J. Turbomach. Propuls. Power 2017, 2(4), 20; https://doi.org/10.3390/ijtpp2040020
Received: 8 August 2017 / Revised: 3 November 2017 / Accepted: 4 December 2017 / Published: 8 December 2017
An algorithm is presented generating a complete set of inlet boundary conditions for Reynolds-averaged Navier–Stokes computational fluid dynamics (RANS CFD) of high-pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding the sensitivities of turbine aerothermal performance in a systematic approach. The boundary conditions are based on a set of input parameters controlling velocity, temperature, and turbulence fields. All other quantities are derived from operating conditions and additional modelling assumptions. The algorithm is coupled with a CFD solver by applying the generated profiles as inlet boundary conditions. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD. View Full-Text
Keywords: computational fluid dynamics; combustor turbine interaction; axial turbine; boundary conditions computational fluid dynamics; combustor turbine interaction; axial turbine; boundary conditions
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Schneider, M.; Schiffer, H.-P.; Lehmann, K. Parameterised Model of 2D Combustor Exit Flow Conditions for High-Pressure Turbine Simulations. Int. J. Turbomach. Propuls. Power 2017, 2, 20.

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