A numerical investigation of a flutter in a transonic fan
October 1996
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| Format: | Technical Report |
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Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1996]
2016
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| Online Access: | http://hdl.handle.net/1721.1/104759 |
| _version_ | 1826209931263475712 |
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| author | Isomura, Kousuke |
| author2 | Massachusetts Institute of Technology. Gas Turbine Laboratory |
| author_facet | Massachusetts Institute of Technology. Gas Turbine Laboratory Isomura, Kousuke |
| author_sort | Isomura, Kousuke |
| collection | MIT |
| description | October 1996 |
| first_indexed | 2024-09-23T14:36:04Z |
| format | Technical Report |
| id | mit-1721.1/104759 |
| institution | Massachusetts Institute of Technology |
| last_indexed | 2024-09-23T14:36:04Z |
| publishDate | 2016 |
| publisher | Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1996] |
| record_format | dspace |
| spelling | mit-1721.1/1047592019-04-12T16:15:32Z A numerical investigation of a flutter in a transonic fan Isomura, Kousuke Massachusetts Institute of Technology. Gas Turbine Laboratory TJ778.M41 G24 no.223 Aerodynamics, Transonic Flutter (Aerodynamics) October 1996 Includes bibliographical references (pages 155-158) The mechanism of the bending mode flutter of a modern transonic fan has been studied using a quasi-3D viscous unsteady code. The type of flutter in the scope of this research is that for a highly loaded blade with a tip relative Mach number just above unity, commonly referred to as transonic stall flutter. This type of flutter is often encountered in modern wide chord fans without a part span shroud. The code written as a part of this research uses an upwinding scheme with Roe's 3rd-order flux differencing, and Johnson and King's turbulence model with later modification by Johnson and Coakley. An extensive series of code validation calculations were performed and the reliability of the code has been verified against data and other calculational procedures. The calculations of the flow in this fan revealed that the source of the flutter is an oscillation of the passage shock, rather than a stall. As blade loading increases, the passage shock moves forward. Just before the passage shock unstarts, the stability of the passage shock decreases, and the shock oscillates at a large amplitude between unstarted position and started position with small blade vibration. The shock foot of the oscillating passage shock on the blade pressure surface exerts the dominant blade exciting force. Supported by Ishikawajima-Harima Heavy Industries Co., Ltd 2016-10-06T21:22:29Z 2016-10-06T21:22:29Z 1996 Technical Report http://hdl.handle.net/1721.1/104759 38078795 GTL report #223 158 pages application/pdf Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1996] |
| spellingShingle | TJ778.M41 G24 no.223 Aerodynamics, Transonic Flutter (Aerodynamics) Isomura, Kousuke A numerical investigation of a flutter in a transonic fan |
| title | A numerical investigation of a flutter in a transonic fan |
| title_full | A numerical investigation of a flutter in a transonic fan |
| title_fullStr | A numerical investigation of a flutter in a transonic fan |
| title_full_unstemmed | A numerical investigation of a flutter in a transonic fan |
| title_short | A numerical investigation of a flutter in a transonic fan |
| title_sort | numerical investigation of a flutter in a transonic fan |
| topic | TJ778.M41 G24 no.223 Aerodynamics, Transonic Flutter (Aerodynamics) |
| url | http://hdl.handle.net/1721.1/104759 |
| work_keys_str_mv | AT isomurakousuke anumericalinvestigationofaflutterinatransonicfan AT isomurakousuke numericalinvestigationofaflutterinatransonicfan |