Effect of Unsteady Fan-Intake Interaction on Short Intake Design

Author:

Boscagli Luca1ORCID,MacManus David2,Christie Robert3,Sheaf Chris4

Affiliation:

1. Centre for Propulsion and Thermal Power Engineering, Cranfield University , Cranfield MK43 0AL, UK

2. Propulsion Aerodynamics, Centre for Propulsion and Thermal Power Engineering, Cranfield University , Cranfield MK43 0AL, UK

3. Aerospace Engineering Design, Centre for Propulsion and Thermal Power Engineering, Cranfield University , Cranfield MK43 0AL, UK

4. Installation Aerodynamics, Rolls-Royce plc , Derby DE24 8BJ, UK

Abstract

Abstract The next generation of ultrahigh bypass ratio civil aero-engines promises notable engine cycle benefits. However, these benefits can be significantly eroded by a possible increase in nacelle weight and drag due to the typical larger fan diameters. More compact nacelles, with shorter intakes, may be required to enable a net reduction in aero-engine fuel burn. The aim of this paper is to assess the influence of the design style of short intakes on the unsteady interaction under crosswind conditions between fan and intake, with a focus on the separation onset and characteristics of the boundary layer within the intake. Three intake designs were assessed, and a hierarchical computational fluid dynamics (CFD) approach was used to determine and quantify primary aerodynamic interactions between the fan and the intake design. Similar to previous findings for a specific intake configuration, both intake flow unsteadiness and the unsteady upstream perturbations from the fan have a detrimental effect on the separation onset for the range of intake designs. The separation of the boundary layer within the intake was shock driven for the three different design styles. The simulations also quantified the unsteady intake flows with an emphasis on the spectral characteristics and engine-order signatures of the flow distortion. Overall, this work showed that is beneficial for the intake boundary layer to delay the diffusion closer to the fan and reduce the preshock Mach number to mitigate the adverse unsteady interaction between the fan and the shock.

Funder

Engineering and Physical Sciences Research Council

Publisher

ASME International

Subject

Mechanical Engineering,Energy Engineering and Power Technology,Aerospace Engineering,Fuel Technology,Nuclear Energy and Engineering

Reference57 articles.

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2. ESDU, 1981, “ Mass Flow and Momentum Functions for One-Dimensional Flow of Gas in Ducts,” Engineering Sciences Data Unit, Data Items, Report No. 81004.https://www.esdu.com/cgi-bin/ps.pl?t=doc&p=esdu_81004

3. Tradeoffs in Jet Inlet Design: A Historical Perspective;J. Aircr.,2007

4. Crosswind Effects on Engine Inlets: The Inlet Vortex;J. Aircr.,2010

5. Ultrashort Nacelles for Low Fan Pressure Ratio Propulsors;ASME J. Turbomach.,2015

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