Abstract
The first stage vane section of a modern gas turbine engine is assembled with a gap between the combustor and the vane platform and a second gap on the platform. To prevent ingression, leakage flow is provided through each gap. In this paper, the effectiveness of the leakage flow as an endwall film coolant is measured. The cascade geometry includes axial contouring of the cooled endwall and several step configurations for each gap. The steps reflect assembly or differential thermal growth misalignment. Various blowing rates are applied through each gap to allow assessment of the changes in effectiveness with changes in leakage rate. Thus, the results presented herein show how the gaps, steps, and leakage rates alter the cooling effectiveness of the leakage flow. Shown are some cases where steps improve the film cooling effectiveness. In other cases, enhanced mixing due to gaps, steps, or increased leakage reduces effectiveness.
Original language | English (US) |
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Title of host publication | Proceedings of the ASME Turbo Expo 2006 - Power for Land, Sea, and Air |
Pages | 535-546 |
Number of pages | 12 |
Volume | 3 PART A |
DOIs | |
State | Published - Nov 15 2006 |
Event | 2006 ASME 51st Turbo Expo - Barcelona, Spain Duration: May 6 2006 → May 11 2006 |
Other
Other | 2006 ASME 51st Turbo Expo |
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Country | Spain |
City | Barcelona |
Period | 5/6/06 → 5/11/06 |