Comparative Studies of RANS Versus Large Eddy Simulation for Fan–Intake Interaction

Author:

Ma Yunfei1,Vadlamani Nagabhushana Rao2,Cui Jiahuan3,Tucker Paul4

Affiliation:

1. Department of Engineering, University of Cambridge, Cambridge CB2 1PZ, UK e-mail:

2. Department of Aerospace Engineering, Indian Institute of Technology (IIT) Madras, Chennai 600036, India e-mail:

3. School of Aeronautics and Astronautics, ZJU-UIUC Institute, Zhejiang University, Haining 310007, China e-mail:

4. Professor Department of Engineering, University of Cambridge, Cambridge CB2 1PZ, UK e-mail:

Abstract

The present research applied a mixed-fidelity approach to examine the fan–intake interaction. Flow separation induced by a distortion generator (DG) is either resolved using large eddy simulation (LES) or modeled using the standard k–ω model, Spalart–Allmaras (SA) model, etc. The immersed boundary method with smeared geometry (immersed boundary method with smeared geometry (IBMSG)) is employed to represent the effect of the fan and a wide range of test cases is studied by varying the (a) height of the DG and (b) proximity of the fan to the DG. Comparisons are drawn between the LES and the Reynolds-averaged Navier–Stokes (RANS) approaches with/without the fan effect. It is found that in the “absence of fan,” the discrepancies between RANS and LES are significant within the separation and reattachment region due to the well-known limitations of the standard RANS models. “With the fan installed,” the deviation between RANS and LES decreases substantially. It becomes minimal when the fan is closest to the DG. It implies that with an installed fan, the inaccuracies of the turbulence model are mitigated by the strong flow acceleration at the casing due to the fan. More precisely, the mass flow redistribution due to the fan has a dominant primary effect on the final predictions and the effect of turbulence model becomes secondary, thereby suggesting that high fidelity eddy resolving simulations provide marginal improvements to the accuracy for the installed cases, particularly for the short intake–fan strategies with fan getting closer to intake lip.

Funder

China Scholarship Council

Engineering and Physical Sciences Research Council

Publisher

ASME International

Subject

Mechanical Engineering

Reference45 articles.

1. Inlet Distortion Effects in Aircraft Propulsion System Integration,1992

2. Effects of Boundary-Layer Ingestion on the Aero-Acoustics of Transonic Fan Rotors;ASME J. Turbomach.,2013

3. A Study of Fan-Distortion Interaction Within the Nasa Rotor 67 Transonic Stage;ASME J. Turbomach.,2012

4. Unsteady CFD Simulation of Transonic Axial Compressor Stages With Distorted Inflow,2016

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