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 in-let distortion due to boundary layer ingestion (BLI). A non-axisymmetric 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) rotor spanwise work profiles, (ii) rotor-stator spacings, and (iii) non-axisymmetric stator geometries. Of the approaches examined, non-axisymmetric stator geometry and increased stage flow and stagnation enthalpy rise coefficients provide the greatest reductions in rotor flow non-uniformity, and may offer the most poentential for mitigating performance loss due to BLI inlet distortion.
Analysis of Fan Stage Conceptual Design Attributes for Boundary Layer Ingestion
2017
Article (Journal)
English
Analysis of Fan Stage Conceptual Design Attributes for Boundary Layer Ingestion
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