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A Blade Element Theory Based Actuator Disk Methodology for Modeling of Fan Engines in RANS Simulations

Spinner, Sebastian and Keller, Dennis and Schnell, Rainer and Trost, Marco (2020) A Blade Element Theory Based Actuator Disk Methodology for Modeling of Fan Engines in RANS Simulations. In: AIAA Aviation 2020 Forum. AIAA Aviation 2020 Forum, 15-19. Juni 2020, Reno, Nevada, USA. doi: 10.2514/6.2020-2749. ISBN 978-162410598-2.

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A modified actuator disk method based on blade element momentum theory is applied to an UHBR turbofan engine with the DLR TAU Code. The method is compared against RANS simulations with a common thermodynamic engine boundary condition and high-fidelity 360° uRANS simulations as well as RANS mixing-plane data from the design process of the engine conducted with the DLR flow solver TRACE. The input data of the actuator disk model comprise sectional lift and drag coefficients of the rotor and stator blades which are obtained by 2D RANS computations of the blade sections performed with the TAU Code. The boundary conditions for these 2D computations are derived from the aforementioned RANS mixing-plane results obtained during the design process of the investigated engine. Good agreement between the RANS actuator disk method and the uRANS results as well as the RANS mixing-plane data is observed. The actuator disk model is able to predict global engine performance data for different engine operating points. Detailed analysis shows that the actuator disk model is able to reproduce characteristic non-uniform inflow phenomena that could in the past only be modeled with uRANS computations. Additionally the model is capable to accurately predict the thrust distribution between rotor and stator. Therefore it is able to fill the gap between the currently used thermodynamic engine boundary condition and high-fidelity uRANS computations with only a minor increase in required computational resources.

Item URL in elib:https://elib.dlr.de/137639/
Document Type:Conference or Workshop Item (Speech)
Title:A Blade Element Theory Based Actuator Disk Methodology for Modeling of Fan Engines in RANS Simulations
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Spinner, SebastianUNSPECIFIEDhttps://orcid.org/0000-0002-3661-6814UNSPECIFIED
Date:June 2020
Journal or Publication Title:AIAA Aviation 2020 Forum
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:No
Keywords:Engine Modelling, Actuator Disk, UHBR, RANS, CFD
Event Title:AIAA Aviation 2020 Forum
Event Location:Reno, Nevada, USA
Event Type:international Conference
Event Dates:15-19. Juni 2020
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:other
DLR - Research area:Aeronautics
DLR - Program:L - no assignment
DLR - Research theme (Project):L - no assignment
Location: Braunschweig
Institutes and Institutions:Institute for Aerodynamics and Flow Technology
Institute of Propulsion Technology
Deposited By: Spinner, Sebastian
Deposited On:18 Nov 2020 07:55
Last Modified:10 Aug 2023 07:43

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