Effects of compressor endwall suction and blowing on stability enhancement
January 1988
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| Format: | Technical Report |
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Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1988]
2016
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| Online Access: | http://hdl.handle.net/1721.1/104733 |
| _version_ | 1826212808481570816 |
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| author | Lee, Norman Kai Wing |
| author2 | Massachusetts Institute of Technology. Gas Turbine and Plasma Dynamics Laboratory |
| author_facet | Massachusetts Institute of Technology. Gas Turbine and Plasma Dynamics Laboratory Lee, Norman Kai Wing |
| author_sort | Lee, Norman Kai Wing |
| collection | MIT |
| description | January 1988 |
| first_indexed | 2024-09-23T15:38:33Z |
| format | Technical Report |
| id | mit-1721.1/104733 |
| institution | Massachusetts Institute of Technology |
| last_indexed | 2024-09-23T15:38:33Z |
| publishDate | 2016 |
| publisher | Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1988] |
| record_format | dspace |
| spelling | mit-1721.1/1047332019-04-11T09:01:14Z Effects of compressor endwall suction and blowing on stability enhancement Compressor endwall suction and blowing on stability enhancement, Effects of Lee, Norman Kai Wing Massachusetts Institute of Technology. Gas Turbine and Plasma Dynamics Laboratory TJ778.M41 G24 no.192 Turbomachines -- Blades Stalling (Aerodynamics) January 1988 Includes bibliographical references An experimental investigation was carried out to examine the effects on stall margin of flow injection into, and removal out of, the endwall region of an axial compressor blade row. A main goal was to identify the mechanism by which wall treatment suppresses stall in turbomachines. To simulate the relative motion between blade and treatment, the injection and removal took place through a slotted hub rotating beneath a cantilevered stator row. Overall performance data and detailed (time-averaged) flow-field measurements were obtained. Both injection and removal increased the stalling pressure rise, but neither was as effective as the complete treatment. This implies that removal of high blockage flow is not the only reason behind the observed stall margin improvement in a casing or hub treatment, and that injection also contributes to stall suppression. The results also indicated that, for a given variation of injection, the increase in stall pressure rise is linked to the streamwise momentum of the injected flow. Supported by Allison Gas Turbine Division of General Motors Supported by the Air Force Office of Scientific Research F49-620-85-C-0018 2016-10-06T21:22:16Z 2016-10-06T21:22:16Z 1988 Technical Report http://hdl.handle.net/1721.1/104733 19764347 GTL report #192 123 leaves application/pdf Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1988] |
| spellingShingle | TJ778.M41 G24 no.192 Turbomachines -- Blades Stalling (Aerodynamics) Lee, Norman Kai Wing Effects of compressor endwall suction and blowing on stability enhancement |
| title | Effects of compressor endwall suction and blowing on stability enhancement |
| title_full | Effects of compressor endwall suction and blowing on stability enhancement |
| title_fullStr | Effects of compressor endwall suction and blowing on stability enhancement |
| title_full_unstemmed | Effects of compressor endwall suction and blowing on stability enhancement |
| title_short | Effects of compressor endwall suction and blowing on stability enhancement |
| title_sort | effects of compressor endwall suction and blowing on stability enhancement |
| topic | TJ778.M41 G24 no.192 Turbomachines -- Blades Stalling (Aerodynamics) |
| url | http://hdl.handle.net/1721.1/104733 |
| work_keys_str_mv | AT leenormankaiwing effectsofcompressorendwallsuctionandblowingonstabilityenhancement AT leenormankaiwing compressorendwallsuctionandblowingonstabilityenhancementeffectsof |