THE ROLE OF TIP LEAKAGE FLOW IN SPIKE-TYPE ROTATING STALL INCEPTION
© 2019 by ASME. This paper describes the role of tip leakage flow in creating the leading edge separation necessary for the onset of spike-type compressor rotating stall. A series of unsteady multipassage simulations, supported by experimental data, are used to define and illustrate the two competin...
| Main Authors: | , , , , |
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| Other Authors: | |
| Format: | Article |
| Language: | English |
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ASME International
2021
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| Online Access: | https://hdl.handle.net/1721.1/135872 |
| _version_ | 1826203295299928064 |
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| author | Hewkin-Smith, M Pullan, G Grimshaw, SD Greitzer, EM Spakovszky, ZS |
| author2 | Massachusetts Institute of Technology. Gas Turbine Laboratory |
| author_facet | Massachusetts Institute of Technology. Gas Turbine Laboratory Hewkin-Smith, M Pullan, G Grimshaw, SD Greitzer, EM Spakovszky, ZS |
| author_sort | Hewkin-Smith, M |
| collection | MIT |
| description | © 2019 by ASME. This paper describes the role of tip leakage flow in creating the leading edge separation necessary for the onset of spike-type compressor rotating stall. A series of unsteady multipassage simulations, supported by experimental data, are used to define and illustrate the two competing mechanisms that cause the high incidence responsible for this separation: blockage from a casing-suction-surface corner separation and forward spillage of the tip leakage jet. The axial momentum flux in the tip leakage flow determines which mechanism dominates. At zero tip clearance, corner separation blockage dominates. As clearance is increased, the leakage flow reduces blockage, moving the stall flow coefficient to lower flow, i.e., giving a larger unstalled flow range. Increased clearance, however, means increased leakage jet momentum and contribution to leakage jet spillage. There is thus a clearance above which jet spillage dominates in creating incidence, so the stall flow coefficient increases and flow range decreases with clearance. As a consequence, there is a clearance for maximum flow range; for the two rotors in this study, the value was approximately 0.5% chord. The chordwise distribution of the leakage axial momentum is also important in determining stall onset. Shifting the distribution toward the trailing edge increases flow range for a leakage jet dominated geometry and reduces flow range for a corner separation dominated geometry. Guidelines are developed for flow range enhancement through control of tip leakage flow axial momentum magnitude and distribution. An example is given of how this might be achieved. |
| first_indexed | 2024-09-23T12:34:42Z |
| format | Article |
| id | mit-1721.1/135872 |
| institution | Massachusetts Institute of Technology |
| language | English |
| last_indexed | 2024-09-23T12:34:42Z |
| publishDate | 2021 |
| publisher | ASME International |
| record_format | dspace |
| spelling | mit-1721.1/1358722023-02-23T16:24:07Z THE ROLE OF TIP LEAKAGE FLOW IN SPIKE-TYPE ROTATING STALL INCEPTION Hewkin-Smith, M Pullan, G Grimshaw, SD Greitzer, EM Spakovszky, ZS Massachusetts Institute of Technology. Gas Turbine Laboratory © 2019 by ASME. This paper describes the role of tip leakage flow in creating the leading edge separation necessary for the onset of spike-type compressor rotating stall. A series of unsteady multipassage simulations, supported by experimental data, are used to define and illustrate the two competing mechanisms that cause the high incidence responsible for this separation: blockage from a casing-suction-surface corner separation and forward spillage of the tip leakage jet. The axial momentum flux in the tip leakage flow determines which mechanism dominates. At zero tip clearance, corner separation blockage dominates. As clearance is increased, the leakage flow reduces blockage, moving the stall flow coefficient to lower flow, i.e., giving a larger unstalled flow range. Increased clearance, however, means increased leakage jet momentum and contribution to leakage jet spillage. There is thus a clearance above which jet spillage dominates in creating incidence, so the stall flow coefficient increases and flow range decreases with clearance. As a consequence, there is a clearance for maximum flow range; for the two rotors in this study, the value was approximately 0.5% chord. The chordwise distribution of the leakage axial momentum is also important in determining stall onset. Shifting the distribution toward the trailing edge increases flow range for a leakage jet dominated geometry and reduces flow range for a corner separation dominated geometry. Guidelines are developed for flow range enhancement through control of tip leakage flow axial momentum magnitude and distribution. An example is given of how this might be achieved. 2021-10-27T20:29:44Z 2021-10-27T20:29:44Z 2019 2019-10-25T15:05:38Z Article http://purl.org/eprint/type/JournalArticle https://hdl.handle.net/1721.1/135872 en 10.1115/1.4042250 Journal of Turbomachinery Article is made available in accordance with the publisher's policy and may be subject to US copyright law. Please refer to the publisher's site for terms of use. application/pdf ASME International ASME |
| spellingShingle | Hewkin-Smith, M Pullan, G Grimshaw, SD Greitzer, EM Spakovszky, ZS THE ROLE OF TIP LEAKAGE FLOW IN SPIKE-TYPE ROTATING STALL INCEPTION |
| title | THE ROLE OF TIP LEAKAGE FLOW IN SPIKE-TYPE ROTATING STALL INCEPTION |
| title_full | THE ROLE OF TIP LEAKAGE FLOW IN SPIKE-TYPE ROTATING STALL INCEPTION |
| title_fullStr | THE ROLE OF TIP LEAKAGE FLOW IN SPIKE-TYPE ROTATING STALL INCEPTION |
| title_full_unstemmed | THE ROLE OF TIP LEAKAGE FLOW IN SPIKE-TYPE ROTATING STALL INCEPTION |
| title_short | THE ROLE OF TIP LEAKAGE FLOW IN SPIKE-TYPE ROTATING STALL INCEPTION |
| title_sort | role of tip leakage flow in spike type rotating stall inception |
| url | https://hdl.handle.net/1721.1/135872 |
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