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contributor authorM. E. Taslim
contributor authorS. D. Spring
contributor authorT. Li
date accessioned2017-05-08T23:55:07Z
date available2017-05-08T23:55:07Z
date copyrightJuly, 1997
date issued1997
identifier issn0889-504X
identifier otherJOTUEI-28661#601_1.pdf
identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/119613
description abstractLeading edge cooling cavities in modern gas turbine blades play an important role in maintaining the leading edge temperature at levels consistent with airfoil design life. These cavities often have a complex cross-sectional shape to be compatible with the external contour of the blade at the leading edge. A survey of many existing geometries shows that, for analytical as well as experimental analyses, such cavities can be simplified in shape by a four-sided polygon with one curved side similar to the leading edge curvature, a rectangle with one semicircular side (often the smaller side) or a trapezoid, the smaller base of which is replaced by a semicircle. Furthermore, to enhance the heat transfer coefficient in these cavities, they are mostly roughened on three sides with ribs of different geometries. Experimental data on friction factors and heat transfer coefficients in such cavities are rare if not nonexistent. A liquid crystal technique was used in this experimental investigation to measure heat transfer coefficients in six test sections representing the leading-edge cooling cavities. Both straight and tapered ribs were configured on the two opposite sidewalls in a staggered arrangement with angles of attack to the mainstream flow, α of 60 and 90 deg. The ribs on the curved surface were of constant cross section with an angle of attack 90 deg to the flow. Heat transfer measurements were performed on the straight sidewalls, as well as on the round surface adjacent to the blade leading edge. Effects such as rib angle of attack to the mainstream flow and constant versus tapered rib cross-sectional areas were also investigated. Nusselt numbers, friction factors, and thermal performances are reported for nine rib geometries in six test sections.
publisherThe American Society of Mechanical Engineers (ASME)
titleMeasurements of Heat Transfer Coefficients and Friction Factors in Rib-Roughened Channels Simulating Leading-Edge Cavities of a Modern Turbine Blade
typeJournal Paper
journal volume119
journal issue3
journal titleJournal of Turbomachinery
identifier doi10.1115/1.2841164
journal fristpage601
journal lastpage609
identifier eissn1528-8900
keywordsFriction
keywordsChannels (Hydraulic engineering)
keywordsMeasurement
keywordsTurbine blades
keywordsCavities
keywordsHeat transfer coefficients
keywordsFlow (Dynamics)
keywordsBlades
keywordsShapes
keywordsCooling
keywordsLiquid crystals
keywordsTemperature
keywordsHeat transfer
keywordsDesign
keywordsGas turbines
keywordsAirfoils AND Experimental analysis
treeJournal of Turbomachinery:;1997:;volume( 119 ):;issue: 003
contenttypeFulltext


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