An improved blade passage model for estimating off-design axial compressor performance
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2013.
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| Other Authors: | |
| Format: | Thesis |
| Language: | eng |
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Massachusetts Institute of Technology
2014
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| Online Access: | http://hdl.handle.net/1721.1/85765 |
| _version_ | 1811088049636900864 |
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| author | Brand, Maximilian Lewis |
| author2 | Zoltán S. Spakovszky. |
| author_facet | Zoltán S. Spakovszky. Brand, Maximilian Lewis |
| author_sort | Brand, Maximilian Lewis |
| collection | MIT |
| description | Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2013. |
| first_indexed | 2024-09-23T13:55:10Z |
| format | Thesis |
| id | mit-1721.1/85765 |
| institution | Massachusetts Institute of Technology |
| language | eng |
| last_indexed | 2024-09-23T13:55:10Z |
| publishDate | 2014 |
| publisher | Massachusetts Institute of Technology |
| record_format | dspace |
| spelling | mit-1721.1/857652019-04-12T21:41:10Z An improved blade passage model for estimating off-design axial compressor performance Brand, Maximilian Lewis Zoltán S. Spakovszky. Massachusetts Institute of Technology. Department of Aeronautics and Astronautics. Massachusetts Institute of Technology. Department of Aeronautics and Astronautics. Aeronautics and Astronautics. Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2013. Cataloged from PDF version of thesis. Includes bibliographical references (pages 127-129). Accurate estimates of multistage axial compressor performance at off-design operating conditions are essential to the determination of key performance metrics of aircraft gas turbine engines, such as fuel burn, thrust output, and stable operating range. However, conventional RANS based CFD calculations of multistage axial compressors diverge at off-design operating conditions where large separation occurs and the stages are mismatched. This thesis demonstrates the feasibility of a body force based approach to capturing the three-dimensional flow field through a turbomachinery blade row at off-design conditions. A first principles based blade passage model is introduced which addresses the limitations of previous approaches. The inputs to the improved blade passage model are determined from three-dimensional, steady, single-passage RANS CFD calculations. In a first step towards modeling multistage configurations, the improved blade passage model is validated using a fan rotor test case. At the design operating conditions, the stagnation pressure rise coefficient and the work coefficient are both estimated within 5%, and the adiabatic efficiency is estimated within 1 percentage point over most of the span relative to single-passage RANS CFD simulations. At low mass flow operating conditions, where the single-passage RANS CFD diverges, the blade passage model and related body force representation are capable of computing the three-dimensional throughflow with separation and reversed flow. These results pave the way for future unsteady calculations to assess compressor stability and for multistage compressor simulations at off-design conditions. by Maximilian Lewis Brand. S.M. 2014-03-19T15:43:50Z 2014-03-19T15:43:50Z 2013 2013 Thesis http://hdl.handle.net/1721.1/85765 871256923 eng M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission. http://dspace.mit.edu/handle/1721.1/7582 129 pages application/pdf Massachusetts Institute of Technology |
| spellingShingle | Aeronautics and Astronautics. Brand, Maximilian Lewis An improved blade passage model for estimating off-design axial compressor performance |
| title | An improved blade passage model for estimating off-design axial compressor performance |
| title_full | An improved blade passage model for estimating off-design axial compressor performance |
| title_fullStr | An improved blade passage model for estimating off-design axial compressor performance |
| title_full_unstemmed | An improved blade passage model for estimating off-design axial compressor performance |
| title_short | An improved blade passage model for estimating off-design axial compressor performance |
| title_sort | improved blade passage model for estimating off design axial compressor performance |
| topic | Aeronautics and Astronautics. |
| url | http://hdl.handle.net/1721.1/85765 |
| work_keys_str_mv | AT brandmaximilianlewis animprovedbladepassagemodelforestimatingoffdesignaxialcompressorperformance AT brandmaximilianlewis improvedbladepassagemodelforestimatingoffdesignaxialcompressorperformance |