Prediction of Heat Transfer Characteristics for Discrete Hole Film Cooling on Flat Plate and Turbine Blades PDF Download
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Author: Daneshmund Kaikushroo Tafti
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 250
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Author: Daneshmund Kaikushroo Tafti
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 250
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Author: Daneshmund K. Tafti
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 0
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Author: Ernst Rudolf Georg Eckert
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 44
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Book Description
Summary: Transpiration and film cooling promise to be effective methods of cooling gas-turbine blades; consequently, analytical and experimental investigations are being conducted to obtain a better understanding of these processes. This report serves as an introduction to these cooling methods, explains the physical processes, and surveys the information available for predicting blade temperatures and heat-transfer rates. In addition, the difficulties encountered in obtaining a uniform blade temperature are discussed, and the possibilities of correcting these difficulties are indicated. Air is the only coolant considered in the application of these cooling methods.
Author:
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 438
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781793995360
Category : Science
Languages : en
Pages : 32
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Book Description
Heat transfer correlations of data on flat plates are used to explore the parameters in the Coolit program used for calculating the quantity of cooling air for controlling turbine blade temperature. Correlations for both convection and film cooling are explored for their relevance to predicting blade temperature as a function of a total cooling flow which is split between external film and internal convection flows. Similar trends to those in Coolit are predicted as a function of the percent of the total cooling flow that is in the film. The exceptions are that no film or 100 percent convection is predicted to not be able to control blade temperature, while leaving less than 25 percent of the cooling flow in the convection path results in nearing a limit on convection cooling as predicted by a thermal effectiveness parameter not presently used in Coolit. Schneider, Steven J. Glenn Research Center WBS 475122.02.03.02.02
Author: Vijay K. Garg
Publisher:
ISBN:
Category :
Languages : en
Pages : 26
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Presented at the International Gas Turbine and Aeroengine Congress and Exposition, Houston, Texas - June 5-8, 1995.
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 730
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Author: Louis M. Russell
Publisher:
ISBN:
Category : Flow visualization
Languages : en
Pages : 30
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Book Description
An experimental study was made to obtain quantitative information on heat transfer, flow, and pressure distribution in a branched duct test section that had several significant features of an internal cooling passage of a turbine blade. The objective of this study was to generate a set of experimental data that could be used for validation of computer codes that would be used to model internal cooling. Surface heat transfer coefficients and entrance flow conditions were measured at nominal entrance Reynolds numbers of 45 000, 335 000, and 726 000. Heat transfer data were obtained by using a steady-state technique in which an Inconel heater sheet is attached to the surface and coated with liquid crystals. Visual and quantitative flow-field data from particle image velocimetry measurements for a plane at midchannel height for a Reynolds number of 45 000 were also obtained. The flow was seeded with polystyrene particles and illuminated by a laser light sheet. Pressure distribution measurements were made both on the surface with discrete holes and in the flow field with a total pressure probe. The flow-field measurements yielded flow-field velocities at selected locations. A relatively new method, pressure sensitive paint, was also used to measure surface pressure distribution. The pressure paint data obtained at Reynolds numbers of 335 000 and 726 000 compared well with the more standard method of measuring pressures by using discrete holes.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 34
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 944
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