Radial Turbine Cooling PDF Download
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 48
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 48
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Book Description
Author: Lizet Tirres
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
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Book Description
Author: Richard Kent Davis
Publisher:
ISBN:
Category :
Languages : en
Pages : 112
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Author: W. U. ROSSLER
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
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Book Description
ARE DESCRIBED. The study is concerned with the effect of introducing a thin film of cool gas between the main hot gas flow and the rotating turbine disk. The program was conducted in two parts. The first part, carried out by S, Test equipment, Infrared equipment, Heaters, Gas turbine nozzles, Rotating structures. Open-ended Terms: Radial-flow turbines. Results of an investigation into the behavior of veil (or film) cooling of a radial-inflow turbineARE DESCRIBED. The study is concerned with the effect of introducing a thin film of cool gas between the main hot gas flow and the rotating turbine disk. The program was conducted in two parts. The first part, carried out by AiResearch Manufacturing Company, comprised an experimental study of the cooling phenomenon on an actual, hot, high-speed turbine. The second part, being conducted at Stanford University, comprises an analytical study and a model experimental study designed to measure basic heat transfer coefficients. The effectiveness of veil cooling was measured by means of thermocouples imbedded in the rotor, with readings brought out through a precision slip-ring unit. Tests were made with several film thicknesses and under various operating conditions. Correlations of the data are presented and discussed. The results of the Stanford work are reviewed. Analytical predictions of heat transfer to a rotating disk are given. The model experimental apparatus is described and plans for the concluding test work are discussed. (Author).
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723141973
Category :
Languages : en
Pages : 120
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Book Description
An experimental study was conducted (1) to experimentally measure, assess and analyze the heat transfer within the internal cooling configuration of a radial turbine rotor blade and (2) to obtain heat transfer data to evaluate and improve computational fluid dynamics (CFD) procedures and turbulent transport models of internal coolant flows. A 1.15 times scale model of the coolant passages within the NASA LERC High Temperature Radial Turbine was designed, fabricated of Lucite and instrumented for transient beat transfer tests using thin film surface thermocouples and liquid crystals to indicate temperatures. Transient heat transfer tests were conducted for Reynolds numbers of one-fourth, one-half, and equal to the operating Reynolds number for the NASA Turbine. Tests were conducted for stationary and rotating conditions with rotation numbers in the range occurring in the NASA Turbine. Results from the experiments showed the heat transfer characteristics within the coolant passage were affected by rotation. In general, the heat transfer increased and decreased on the sides of the straight radial passages with rotation as previously reported from NASA-HOST-sponsored experiments. The heat transfer in the tri-passage axial flow region adjacent to the blade exit was relatively unaffected by rotation. However, the heat transfer on one surface, in the transitional region between the radial inflow passage and axial, constant radius passages, decreased to approximately 20 percent of the values without rotation. Comparisons with previous 3-D numerical studies indicated regions where the heat transfer characteristics agreed and disagreed with the present experiment. Johnson, B. V. and Wagner, J. H. Unspecified Center TURBINE BLADES; INTERNAL FLOW; RADIAL FLOW; THERMOCOUPLES; THIN FILMS; COOLING; TRANSIENT HEATING; TEMPERATURE MEASUREMENT; TURBULENT FLOW; REYNOLDS NUMBER; SCALE MODELS; LIQUID CRYSTALS; POLYMETHYL METHACRYLATE; VORTICES; COMPUTATIONAL FLUID DYNAMICS...
Author: Hany Moustapha
Publisher: Concepts Eti
ISBN: 9780933283121
Category : Technology & Engineering
Languages : en
Pages : 358
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Book Description
Mechanical Engineering Design and Analysis of Axlal and Radial Turbines.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 68
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Book Description
Author: P.H. Snyder
Publisher:
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Category :
Languages : en
Pages : 8
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Author: J. M. Lane
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
Paper presents the results of several Army-sponsored programs, the first of which addresses the performance potential for high-temperature radial turbine.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 12
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Book Description
A procedure for computing the rotor temperature and stress distributions in a cooled radial turbine is considered. Existing codes for modeling the external mainstream flow and the internal cooling flow are used to compete boundary conditions for the heat transfer and stress analyses. An inviscid, quasi three dimensional code computes the external free stream velocity. The external velocity is then used in a boundary layer analysis to compute the external heat transfer coefficient. Coolant temperatures are computed by a viscous one dimensional internal flow code for the momentum and energy equation. These boundary conditions are input to a three dimensional heat conduction code for calculation of rotor temperatures. The rotor stress distribution may be determined for the given thermal, pressure and centrifugal loading. The procedure is applied to a cooled radial turbine which will be tested at the NASA Lewis Research Center. Representative results from this case are included.
