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Investigation of combustor-turbine-interaction in a rotating cooled transonic high-pressure turbine test rig, Part II: Numerical modelling and simulation

Gövert, Simon and Ferraro, Federica and Krumme, Alexander and Buske, Clemens and Tegeler, Marc and Kocian, Frank and di Mare, Francesca (2019) Investigation of combustor-turbine-interaction in a rotating cooled transonic high-pressure turbine test rig, Part II: Numerical modelling and simulation. In: Proceedings of the ASME Turbo Expo. ASME. ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition, 2019-06-17 - 2019-06-21, Phoenix, Arizona, USA.

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Reducing the uncertainties in the prediction of turbine inlet conditions is a crucial aspect to improve aero engine designs and further increase engine efficiencies. To meet constantly stricter emission regulations, lean burn combustion could play a key role for future engine designs. However, these combustion systems are characterized by significant swirl for flame stabilization and reduced cooling air mass flows. As a result, substantial spatial and transient variations of the turbine inlet conditions are encountered. To investigate the effect of the combustor on the high pressure turbine, a rotating cooled transonic high-pressure configuration has been designed and investigated experimentally at the DLR turbine test facility 'NG-Turb' in Göttingen, Germany. It is a rotating full annular 1.5 stage turbine configuration which is coupled to a combustor simulator. The combustor simulator is designed to create turbine inlet conditions which are hydrodynamically representative for a lean-burn aero engine. A detailed description of the test rig and its instrumentation as well as a discussion of the measurement results is presented in part I of this paper. Part II focuses on numerical modeling of the test rig to further extend the understanding of the measurement results. Integrated simulations of the configuration including combustor simulator and nozzle guide vanes are performed for leading edge and passage clocking position and the effect on the hot streak migration is discussed. The simulation and experimental results at the combustor-turbine interface are compared showing a good overall agreement. The relevant flow features are correctly predicted in the simulations, proving the suitability of the numerical model for application to integrated combustor-turbine interaction Analysis.

Item URL in elib:https://elib.dlr.de/128277/
Document Type:Conference or Workshop Item (Speech)
Title:Investigation of combustor-turbine-interaction in a rotating cooled transonic high-pressure turbine test rig, Part II: Numerical modelling and simulation
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Gövert, SimonUNSPECIFIEDhttps://orcid.org/0000-0003-4593-1776UNSPECIFIED
Buske, ClemensUNSPECIFIEDhttps://orcid.org/0000-0003-4157-7415UNSPECIFIED
Date:June 2019
Journal or Publication Title:Proceedings of the ASME Turbo Expo
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:Combustor-Turbine-Interaction, Numerical Modelling, Integrated Simulation, FACTOR test rig
Event Title:ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition
Event Location:Phoenix, Arizona, USA
Event Type:international Conference
Event Start Date:17 June 2019
Event End Date:21 June 2019
Organizer:American Society of Mechanical Engineers
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:propulsion systems
DLR - Research area:Aeronautics
DLR - Program:L ER - Engine Research
DLR - Research theme (Project):L - Combustion Chamber Technologies (old)
Location: Köln-Porz
Institutes and Institutions:Institute of Propulsion Technology > Combustor
Institute of Propulsion Technology > Turbine
Deposited By: Gövert, Simon
Deposited On:28 Aug 2019 10:28
Last Modified:24 Apr 2024 20:31

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