A two-dimensional design method for highly-loaded blades in turbomachines
Includes bibliographical references
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| Format: | Technical report |
| Published: |
c1983
2016
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| Online Access: | http://hdl.handle.net/1721.1/104697 |
| _version_ | 1826197900044009472 |
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| author | Dang, Thong Quoc |
| author2 | Massachusetts Institute of Technology. Department of Aeronautics and Astronautics |
| author_facet | Massachusetts Institute of Technology. Department of Aeronautics and Astronautics Dang, Thong Quoc |
| author_sort | Dang, Thong Quoc |
| collection | MIT |
| description | Includes bibliographical references |
| first_indexed | 2024-09-23T10:55:21Z |
| format | Technical report |
| id | mit-1721.1/104697 |
| institution | Massachusetts Institute of Technology |
| last_indexed | 2024-09-23T10:55:21Z |
| publishDate | 2016 |
| publisher | c1983 |
| record_format | dspace |
| spelling | mit-1721.1/1046972019-04-10T15:46:17Z A two-dimensional design method for highly-loaded blades in turbomachines Highly-loaded blades in turbomachines, A two-dimensional design method for Dang, Thong Quoc Massachusetts Institute of Technology. Department of Aeronautics and Astronautics Turbomachines -- Blades. TJ267.5.B5.D36 1983 Includes bibliographical references Also issued as: Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1983. A practical design method for highly-loaded blades in an isolated cascade is presented in this thesis. The flow is assumed to be incompressible and inviscid. The upstream inlet flow condition is taken to be uniform. The present goals of this research are to provide a practical numerical code for the design problem, and a non-linear theory which can be easily expanded to three-dimensions. The theory is based in part on the Clebsh formulation. The blade profile is determined iteratively through the blade boundary conditions using a "smoothing" technique. A practical numerical code is presented for the design problem using "partial smoothing". The program gives very fast convergence solutions with satisfactory accuracy for practical solidity range. A practical design method for highly-loaded blades in an isolated cascade is presented in this thesis. The flow is assumed to be incompressible and inviscid. The upstream inlet flow condition is taken to be uniform. The present goals of this research are to provide a practical numerical code for the design problem, and a non-linear theory which can be easily expanded to three-dimensions. The theory is based in part on the Clebsh formulation. The blade profile is determined iteratively through the blade boundary conditions using a "smoothing" technique. A practical numerical code is presented for the design problem using "partial smoothing". The program gives very fast convergence solutions with satisfactory accuracy for practical solidity range. This research was supported by the U.S. Air Force Office of Scientific Research, Dr. J. D. Wilson, Program Manager, contract Number: F49620-82-K-0002 2016-10-06T21:22:02Z 2016-10-06T21:22:02Z c1983 Technical report http://hdl.handle.net/1721.1/104697 68927451 GT & PDL report ; no. 173. 125 leaves application/pdf c1983 |
| spellingShingle | Turbomachines -- Blades. TJ267.5.B5.D36 1983 Dang, Thong Quoc A two-dimensional design method for highly-loaded blades in turbomachines |
| title | A two-dimensional design method for highly-loaded blades in turbomachines |
| title_full | A two-dimensional design method for highly-loaded blades in turbomachines |
| title_fullStr | A two-dimensional design method for highly-loaded blades in turbomachines |
| title_full_unstemmed | A two-dimensional design method for highly-loaded blades in turbomachines |
| title_short | A two-dimensional design method for highly-loaded blades in turbomachines |
| title_sort | two dimensional design method for highly loaded blades in turbomachines |
| topic | Turbomachines -- Blades. TJ267.5.B5.D36 1983 |
| url | http://hdl.handle.net/1721.1/104697 |
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