Centrifugal effect on the boundary layer on a blade of an axial turbo-machine
April 1962
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| Format: | Technical Report |
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Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1962]
2016
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| Online Access: | http://hdl.handle.net/1721.1/104675 |
| _version_ | 1826205941227323392 |
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| author | Olsson, Erik K. A. |
| author2 | General Electric Company |
| author_facet | General Electric Company Olsson, Erik K. A. |
| author_sort | Olsson, Erik K. A. |
| collection | MIT |
| description | April 1962 |
| first_indexed | 2024-09-23T13:21:29Z |
| format | Technical Report |
| id | mit-1721.1/104675 |
| institution | Massachusetts Institute of Technology |
| last_indexed | 2024-09-23T13:21:29Z |
| publishDate | 2016 |
| publisher | Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1962] |
| record_format | dspace |
| spelling | mit-1721.1/1046752019-04-12T16:17:55Z Centrifugal effect on the boundary layer on a blade of an axial turbo-machine Olsson, Erik K. A. General Electric Company General Motors Corporation. Allison Division Westinghouse Electric Corporation Massachusetts Institute of Technology. Gas Turbine Laboratory TJ267.A1 M37 no.66 TL574.B6 O47 1962 Boundary layer Turbomachines -- Aerodynamics Turbulence April 1962 Issued also as: Thesis (Sc. D.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 1962 Includes bibliographical references A study of the effect of centrifugal force acting on the turbulent boundary layer of a blade in a turbo-machine is presented. The study includes experimental work conducted in an apparatus featuring an annular cascade of compressor blades, designed to simulate the flow in a compressor. This is a case of three-dimensional turbulent boundary layer flow end the objects of the study were to find the magnitude of the cross-flow and gain a better understanding of the skewed boundary layers. It is found that the cross-flow which develops in the boundary layer is small with velocities of the order of 1/10 of the through-flow velocities. The study further resulted in the development of a model of skewed, turbulent velocity-profiles, involving two "universal" analytical functions and four parameters. This model has been used with success to describe the measured velocity-profiles. The use of the model and the general result that the cross-flow is small has made it possible to find solutions to the boundary layer integral equations written in a "streamline" coordinate system. Application of the calculation method for the experimental data has been made successfully. A loss parameter is defined and an extension to include the crossflow losses is suggested. Under the sponsorship of General Electric Company, Allison Division of General Motors Corporation, Westinghouse Electric Corporation 2016-10-06T21:21:53Z 2016-10-06T21:21:53Z 1962 Technical Report http://hdl.handle.net/1721.1/104675 09162596 GTL report #66 1 volume ([120] pages in various pagings) application/pdf Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1962] |
| spellingShingle | TJ267.A1 M37 no.66 TL574.B6 O47 1962 Boundary layer Turbomachines -- Aerodynamics Turbulence Olsson, Erik K. A. Centrifugal effect on the boundary layer on a blade of an axial turbo-machine |
| title | Centrifugal effect on the boundary layer on a blade of an axial turbo-machine |
| title_full | Centrifugal effect on the boundary layer on a blade of an axial turbo-machine |
| title_fullStr | Centrifugal effect on the boundary layer on a blade of an axial turbo-machine |
| title_full_unstemmed | Centrifugal effect on the boundary layer on a blade of an axial turbo-machine |
| title_short | Centrifugal effect on the boundary layer on a blade of an axial turbo-machine |
| title_sort | centrifugal effect on the boundary layer on a blade of an axial turbo machine |
| topic | TJ267.A1 M37 no.66 TL574.B6 O47 1962 Boundary layer Turbomachines -- Aerodynamics Turbulence |
| url | http://hdl.handle.net/1721.1/104675 |
| work_keys_str_mv | AT olssonerikka centrifugaleffectontheboundarylayeronabladeofanaxialturbomachine |