Analysis of Fan Stage Conceptual Design Attributes for Boundary Layer Ingestion

Author:

Hall D. K.1,Greitzer E. M.2,Tan C. S.2

Affiliation:

1. Gas Turbine Laboratory, Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA 02139 e-mail:

2. Gas Turbine Laboratory, Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA 02139

Abstract

This paper describes a new conceptual framework for three-dimensional turbomachinery flow analysis and its use to assess fan stage attributes for mitigating adverse effects of inlet distortion due to boundary layer ingestion (BLI). A nonaxisymmetric throughflow analysis has been developed to define fan flow with inlet distortion. The turbomachinery is modeled using momentum and energy source distributions that are determined as a function of local flow conditions and specified blade camber surface geometry. Comparison with higher-fidelity computational and experimental results shows the analysis captures the principal flow redistribution and distortion transfer effects associated with BLI. Distortion response is assessed for a range of (i) design flow and stagnation enthalpy rise coefficients, (ii) rotor spanwise work profiles, (iii) rotor–stator spacings, and (iv) nonaxisymmetric stator geometries. Of the approaches examined, nonaxisymmetric stator geometry and increased stage flow and stagnation enthalpy rise coefficients provide the greatest reductions in rotor flow nonuniformity, and may offer the most potential for mitigating performance loss due to BLI inlet distortion.

Funder

National Aeronautics and Space Administration

Publisher

ASME International

Subject

Mechanical Engineering

Reference27 articles.

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2. Sato, S., 2012, “The Power Balance Method for Aerodynamic Performance Assessment,” Ph.D. dissertation, Massachusetts Institute of Technology, Cambridge, MA.http://hdl.handle.net/1721.1/75837

3. Hall, D. K., 2015, “Analysis of Civil Aircraft Propulsors With Boundary Layer Ingestion,” Ph.D. dissertation, Massachusetts Institute of Technology, Cambridge, MA.http://hdl.handle.net/1721.1/97353

4. Assessment of Technologies for the Silent Aircraft Initiative;AIAA J. Propul. Power,2009

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