Schneider, Marius ; Lehmann, Knut ; Schiffer, Heinz-Peter (2017)
Parameterised Model of 2D Combustor Exit Flow Conditions for High Pressure Turbine Simulations.
12th European Turbomachinery Conference. Stockholm, Sweden (03.04.2017-07.04.2017)
Konferenzveröffentlichung, Bibliographie
Kurzbeschreibung (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.
| Typ des Eintrags: | Konferenzveröffentlichung |
|---|---|
| Erschienen: | 2017 |
| Autor(en): | Schneider, Marius ; Lehmann, Knut ; Schiffer, Heinz-Peter |
| Art des Eintrags: | Bibliographie |
| Titel: | Parameterised Model of 2D Combustor Exit Flow Conditions for High Pressure Turbine Simulations |
| Sprache: | Englisch |
| Publikationsjahr: | 7 April 2017 |
| Veranstaltungstitel: | 12th European Turbomachinery Conference |
| Veranstaltungsort: | Stockholm, Sweden |
| Veranstaltungsdatum: | 03.04.2017-07.04.2017 |
| URL / URN: | http://www.euroturbo.eu/publications/proceedings-papers/etc2... |
| Kurzbeschreibung (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. |
| ID-Nummer: | ETC2017-024 |
| Fachbereich(e)/-gebiet(e): | 16 Fachbereich Maschinenbau 16 Fachbereich Maschinenbau > Fachgebiet für Gasturbinen, Luft- und Raumfahrtantriebe (GLR) |
| Hinterlegungsdatum: | 16 Apr 2018 13:26 |
| Letzte Änderung: | 06 Mär 2020 07:20 |
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