Analysis of Fan Stage Conceptual Design Attributes for Boundary Layer Ingestion
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...
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| Format: | Article |
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ASME International
2018
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| Online Access: | http://hdl.handle.net/1721.1/114790 https://orcid.org/0000-0002-2343-910X https://orcid.org/0000-0001-9625-1020 https://orcid.org/0000-0002-8805-5289 |
| _version_ | 1826208043789975552 |
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| author | Hall, David Kenneth Greitzer, Edward M Tan, Choon S |
| author2 | Massachusetts Institute of Technology. Department of Aeronautics and Astronautics |
| author_facet | Massachusetts Institute of Technology. Department of Aeronautics and Astronautics Hall, David Kenneth Greitzer, Edward M Tan, Choon S |
| author_sort | Hall, David Kenneth |
| collection | MIT |
| description | 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. |
| first_indexed | 2024-09-23T13:59:37Z |
| format | Article |
| id | mit-1721.1/114790 |
| institution | Massachusetts Institute of Technology |
| last_indexed | 2024-09-23T13:59:37Z |
| publishDate | 2018 |
| publisher | ASME International |
| record_format | dspace |
| spelling | mit-1721.1/1147902024-06-26T15:03:01Z Analysis of Fan Stage Conceptual Design Attributes for Boundary Layer Ingestion Hall, David Kenneth Greitzer, Edward M Tan, Choon S Massachusetts Institute of Technology. Department of Aeronautics and Astronautics Massachusetts Institute of Technology. Gas Turbine Laboratory Hall, David Kenneth Greitzer, Edward M Tan, Choon S 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. 2018-04-19T13:30:48Z 2018-04-19T13:30:48Z 2017-03 2016-12 2018-03-20T16:59:57Z Article http://purl.org/eprint/type/JournalArticle 0889-504X http://hdl.handle.net/1721.1/114790 Hall, D. K. et al. “Analysis of Fan Stage Conceptual Design Attributes for Boundary Layer Ingestion.” Journal of Turbomachinery 139, 7 (March 2017): 071012 © 2017 ASME https://orcid.org/0000-0002-2343-910X https://orcid.org/0000-0001-9625-1020 https://orcid.org/0000-0002-8805-5289 http://dx.doi.org/10.1115/1.4035631 Journal of Turbomachinery Article is made available in accordance with the publisher's policy and may be subject to US copyright law. Please refer to the publisher's site for terms of use. application/pdf ASME International ASME |
| spellingShingle | Hall, David Kenneth Greitzer, Edward M Tan, Choon S Analysis of Fan Stage Conceptual Design Attributes for Boundary Layer Ingestion |
| title | Analysis of Fan Stage Conceptual Design Attributes for Boundary Layer Ingestion |
| title_full | Analysis of Fan Stage Conceptual Design Attributes for Boundary Layer Ingestion |
| title_fullStr | Analysis of Fan Stage Conceptual Design Attributes for Boundary Layer Ingestion |
| title_full_unstemmed | Analysis of Fan Stage Conceptual Design Attributes for Boundary Layer Ingestion |
| title_short | Analysis of Fan Stage Conceptual Design Attributes for Boundary Layer Ingestion |
| title_sort | analysis of fan stage conceptual design attributes for boundary layer ingestion |
| url | http://hdl.handle.net/1721.1/114790 https://orcid.org/0000-0002-2343-910X https://orcid.org/0000-0001-9625-1020 https://orcid.org/0000-0002-8805-5289 |
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