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dc.contributor.author | Mahmood, Gazi I.![]() |
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dc.contributor.author | Arnachellan, Keenesh![]() |
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dc.date.accessioned | 2018-03-05T10:41:38Z | |
dc.date.available | 2018-03-05T10:41:38Z | |
dc.date.issued | 2018-03 | |
dc.description.abstract | The effects of film cooling on the endwall region flow and aerodynamic losses are investigated experimentally as the film flow is delivered from the slots in the endwall upstream of a linear vane cascade. Four slots inclined at 30 deg deliver the film jet parallel to the main flow at four blowing ratios between 1.1 and 2.3 and at a temperature ratio of 1.0. The slots are employed in two configurations pitchwise: all four slots open (case 1) and two middle slots open (case 2). The inlet Reynolds number to the cascade is 2.0E+05. Measurements of the blade surface pressure, axial vorticities, yaw angles, and total pressure loss distributions along the cascade are reported with and without (baseline) the film-cooling flow. The results show that the film flow changes the orientations, distributions, and strength of the endwall secondary flows and boundary layer. Case 1 of film cooling provides more mass flux and momentum than case 2 affecting the passage vortex legs. The overall total pressure losses at the cascade exit are always lower for the film-cooling cases than for the baseline. The overall losses are also lower at the low blowing ratios but higher at the high blowing ratios for the film-cooling case 1 than for case 2. | en_ZA |
dc.description.department | Mechanical and Aeronautical Engineering | en_ZA |
dc.description.librarian | hj2018 | en_ZA |
dc.description.sponsorship | The AMRSCOR program of the South African government | en_ZA |
dc.description.uri | https://arc.aiaa.org/loi/jpp | en_ZA |
dc.identifier.citation | Gazi I. Mahmood and Keenesh Arnachellan. "Effects of Upstream Endwall Film Cooling on a Vane Cascade Flowfield", Journal of Propulsion and Power, Vol. 34, No. 2 (2018), pp. 460-468. https://doi.org/10.2514/1.B3664. | en_ZA |
dc.identifier.issn | 0748-4658 (print) | |
dc.identifier.issn | 1533-3876 (online) | |
dc.identifier.other | 10.2514/1.B3664 | |
dc.identifier.uri | http://hdl.handle.net/2263/64146 | |
dc.language.iso | en | en_ZA |
dc.publisher | American Institute of Aeronautics and Astronautics Inc. | en_ZA |
dc.rights | © 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. | en_ZA |
dc.subject | Passage vortex | en_ZA |
dc.subject | Endwall region | en_ZA |
dc.subject | Pressure side | en_ZA |
dc.subject | Suction side | en_ZA |
dc.subject | Secondary losses | en_ZA |
dc.subject | Wheelspace coolant injection | en_ZA |
dc.subject | Slot | en_ZA |
dc.subject | Aerodynamics | en_ZA |
dc.subject | Performance | en_ZA |
dc.subject | Purge flow | en_ZA |
dc.subject | Gap geometry | en_ZA |
dc.subject | Blade passage | en_ZA |
dc.subject | Flow structure | en_ZA |
dc.subject | Turbine cascade | en_ZA |
dc.subject | Leading-edge fillets | en_ZA |
dc.title | Effects of upstream endwall film cooling on a vane cascade flowfield | en_ZA |
dc.type | Postprint Article | en_ZA |