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

Schneider, Marius and Schiffer, Heinz-Peter and Lehmann, Knut (2017):
Parameterised Model of 2D Combustor Exit Flow Conditions for High Pressure Turbine Simulations.
In: 12th European Turbomachinery Conference, Stockholm, Sweden, April 3-7, 2017, [Online-Edition: http://www.euroturbo.eu/publications/proceedings-papers/etc2...],
[Conference or Workshop Item]

Abstract

An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.

Item Type: Conference or Workshop Item
Erschienen: 2017
Creators: Schneider, Marius and Schiffer, Heinz-Peter and Lehmann, Knut
Title: Parameterised Model of 2D Combustor Exit Flow Conditions for High Pressure Turbine Simulations
Language: English
Abstract:

An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.An algorithm is presented generating a complete set of inlet boundary conditions for RANS CFD of high pressure turbines to investigate their interaction with lean and rich burn combustors. The method shall contribute to understanding 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 condition. The successive steps to derive consistent flow profiles are described and results are validated against flow fields extracted from combustor CFD.

Divisions: 16 Department of Mechanical Engineering
16 Department of Mechanical Engineering > Institute of Gas Turbines and Aerospace Propulsion (GLR)
Event Title: 12th European Turbomachinery Conference
Event Location: Stockholm, Sweden
Event Dates: April 3-7, 2017
Date Deposited: 16 Apr 2018 13:26
Official URL: http://www.euroturbo.eu/publications/proceedings-papers/etc2...
Identification Number: ETC2017-024
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