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contributor authorZhihong Gao
contributor authorDiganta Narzary
contributor authorShantanu Mhetras
contributor authorJe-Chin Han
date accessioned2017-05-09T00:35:47Z
date available2017-05-09T00:35:47Z
date copyrightJuly, 2009
date issued2009
identifier issn0889-504X
identifier otherJOTUEI-28755#031005_1.pdf
identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/142159
description abstractThe influence of incidence angle on film-cooling effectiveness is studied for a cutback squealer blade tip. Three incidence angles are investigated −0 deg at design condition and ±5 deg at off-design conditions. Based on mass transfer analogy, the film-cooling effectiveness is measured with pressure sensitive paint techniques. The film-cooling effectiveness distribution on the pressure side near tip region, squealer cavity floor, and squealer rim tip is presented for the three incidence angles at varying blowing ratios. The average blowing ratio is controlled to be 0.5, 1.0, 1.5, and 2.0. One row of shaped holes is provided along the pressure side just below the tip; two rows of cylindrical film-cooling holes are arranged on the blade tip in such a way that one row is offset to the suction side profile and the other row is along the camber line. The pressure side squealer rim wall is cut near the trailing edge to allow the accumulated coolant in the cavity to escape and cool the tip trailing edge. The internal coolant-supply passages of the squealer tipped blade are modeled similar to those in the GE-E3 rotor blade. Test is done in a five-blade linear cascade in a blow-down facility with a tip gap clearance of 1.5% of the blade span. The Mach number and turbulence intensity level at the cascade inlet were 0.23 and 9.7%, respectively. It is observed that the incidence angle affects the coolant jet direction on the pressure side near tip region and the blade tip. The film-cooling effectiveness distribution is also altered. The peak of laterally averaged effectiveness is shifted upstream or downstream depending on the off-design incidence angle. The film cooling effectiveness inside the tip cavity can increase by 25% with the positive incidence angle. However, in general, the overall area-averaged film-cooling effectiveness is not significantly changed by the incidence angles in the range of study.
publisherThe American Society of Mechanical Engineers (ASME)
titleEffect of Inlet Flow Angle on Gas Turbine Blade Tip Film Cooling
typeJournal Paper
journal volume131
journal issue3
journal titleJournal of Turbomachinery
identifier doi10.1115/1.2987235
journal fristpage31005
identifier eissn1528-8900
keywordsPressure
keywordsFlow (Dynamics)
keywordsCooling
keywordsCoolants
keywordsBlades
keywordsCavities
keywordsDesign
keywordsSuction AND Gas turbines
treeJournal of Turbomachinery:;2009:;volume( 131 ):;issue: 003
contenttypeFulltext


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