contributor author | N. Hay | |
contributor author | S. E. Henshall | |
contributor author | A. Manning | |
date accessioned | 2017-05-08T23:45:54Z | |
date available | 2017-05-08T23:45:54Z | |
date copyright | January, 1994 | |
date issued | 1994 | |
identifier issn | 0889-504X | |
identifier other | JOTUEI-28634#92_1.pdf | |
identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/114591 | |
description abstract | In the cooling passages of gas turbine blades, branches are often angled to the direction of the internal flow. This is particularly the case with film cooling holes. Accurate knowledge of the discharge coefficient of such holes at the design stage is vital so that the holes are correctly sized, thus avoiding wastage of coolant and the formation of hot spots on the blade. This paper describes an experimental investigation to determine the discharge coefficient of 30 deg inclined holes with various degrees of inlet radiusing and with the axis of the hole at various orientation angles to the direction of the flow. Results are given for nominal main flow Mach numbers of 0, 0.15, and 0.3. The effects of radiusing, orientation, and crossflow Mach number are quantified in the paper, the general trends are described, and the criteria for optimum performance are identified. | |
publisher | The American Society of Mechanical Engineers (ASME) | |
title | Discharge Coefficients of Holes Angled to the Flow Direction | |
type | Journal Paper | |
journal volume | 116 | |
journal issue | 1 | |
journal title | Journal of Turbomachinery | |
identifier doi | 10.1115/1.2928282 | |
journal fristpage | 92 | |
journal lastpage | 96 | |
identifier eissn | 1528-8900 | |
keywords | Flow (Dynamics) | |
keywords | Discharge coefficient | |
keywords | Blades | |
keywords | Mach number | |
keywords | Cooling | |
keywords | Coolants | |
keywords | Internal flow | |
keywords | Design | |
keywords | Gas turbines AND Bifurcation | |
tree | Journal of Turbomachinery:;1994:;volume( 116 ):;issue: 001 | |
contenttype | Fulltext | |