contributor author | Zhihong Gao | |
contributor author | Diganta Narzary | |
contributor author | Shantanu Mhetras | |
contributor author | Je-Chin Han | |
date accessioned | 2017-05-09T00:35:47Z | |
date available | 2017-05-09T00:35:47Z | |
date copyright | July, 2009 | |
date issued | 2009 | |
identifier issn | 0889-504X | |
identifier other | JOTUEI-28755#031005_1.pdf | |
identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/142159 | |
description abstract | The 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. | |
publisher | The American Society of Mechanical Engineers (ASME) | |
title | Effect of Inlet Flow Angle on Gas Turbine Blade Tip Film Cooling | |
type | Journal Paper | |
journal volume | 131 | |
journal issue | 3 | |
journal title | Journal of Turbomachinery | |
identifier doi | 10.1115/1.2987235 | |
journal fristpage | 31005 | |
identifier eissn | 1528-8900 | |
keywords | Pressure | |
keywords | Flow (Dynamics) | |
keywords | Cooling | |
keywords | Coolants | |
keywords | Blades | |
keywords | Cavities | |
keywords | Design | |
keywords | Suction AND Gas turbines | |
tree | Journal of Turbomachinery:;2009:;volume( 131 ):;issue: 003 | |
contenttype | Fulltext | |