An Experimental Study of Turbine Vane Heat Transfer with Leading Edge and Downstream Film Cooling PDF Download
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Author: V. Nirmalan
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 0
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Book Description
Author: V. Nirmalan
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 0
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723439759
Category :
Languages : en
Pages : 178
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Book Description
The progress under contract NAS3-24619 toward the goal of establishing a relevant data base for use in improving the predictive design capabilities for external heat transfer to turbine vanes, including the effect of downstream film cooling with and without leading edge showerhead film cooling. Experimental measurements were made in a two-dimensional cascade previously used to obtain vane surface heat transfer distributions on nonfilm cooled airfoils under contract NAS3-22761 and leading edge showerhead film cooled airfoils under contract NAS3-23695. The principal independent parameters (Mach number, Reynolds number, turbulence, wall-to-gas temperature ratio, coolant-to-gas temperature ratio, and coolant-to-gas pressure ratio) were maintained over ranges consistent with actual engine conditions and the test matrix was structured to provide an assessment of the independent influence of parameters of interest, namely, exit Mach number, exit Reynolds number, coolant-to-gas temperature ratio, and coolant-to-gas pressure ratio. Data provide a data base for downstream film cooled turbine vanes and extends the data bases generated in the two previous studies. The vane external heat transfer obtained indicate that considerable cooling benefits can be achieved by utilizing downstream film cooling. The data obtained and presented illustrate the interaction of the variables and should provide the airfoil designer and computational analyst the information required to improve heat transfer design capabilities for film cooled turbine airfoils. Hylton, L. D. and Nirmalan, V. and Sultanian, B. K. and Kaufman, R. M. Unspecified Center EQUIPMENT SPECIFICATIONS; FILM COOLING; HEAT TRANSFER; LEADING EDGES; STRUCTURAL DESIGN; VANES; AIRCRAFT ENGINES; CASCADE FLOW; DATA PROCESSING; GAS TURBINES; HIGH TEMPERATURE; PARAMETERIZATION; TWO DIMENSIONAL FLOW...
Author: Tarek Elnady
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Je-Chin Han
Publisher: Taylor & Francis
ISBN: 1466564903
Category : Science
Languages : en
Pages : 865
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Book Description
A comprehensive reference for engineers and researchers, this second edition focuses on gas turbine heat transfer issues and their associated cooling technologies for aircraft and land-based gas turbines. It provides information on state-of-the-art cooling technologies such as advanced turbine blade film cooling and internal cooling schemes. The book also offers updated experimental methods for gas turbine heat transfer and cooling research, as well as advanced computational models for gas turbine heat transfer and cooling performance predictions. The authors provide suggestions for future research within this technology and includes 800 illustrations to help clarify concepts and instruction.
Author: Forrest E. Ames
Publisher:
ISBN:
Category :
Languages : en
Pages : 234
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Author:
Publisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 28
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Book Description
Author: Bengt Sundén
Publisher: Witpress
ISBN:
Category : Medical
Languages : en
Pages : 544
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Book Description
This title presents and reflects current active research on various heat transfer topics and related phenomena in gas turbine systems. It begins with a general introduction to gas turbine heat transfer, before moving on to specific areas.
Author: Christian Liess
Publisher:
ISBN:
Category : Cooling
Languages : en
Pages : 116
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Book Description
Author: Herbert J. Gladden
Publisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 28
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Book Description
Author: James D. Heidmann
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Book Description
