Streakline flow visualization of discrete-hole film cooling with normal, slanted and compound angle injection PDF Download
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Author: Raymond S. Colladay
Publisher:
ISBN:
Category : Flow visualization
Languages : en
Pages : 28
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Author: Raymond S. Colladay
Publisher:
ISBN:
Category : Flow visualization
Languages : en
Pages : 28
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Author: Louis M. Russell
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 772
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Author: Louis M. Russell
Publisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 20
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Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 492
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Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1228
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Book Description
February issue includes Appendix entitled Directory of United States Government periodicals and subscription publications; September issue includes List of depository libraries; June and December issues include semiannual index
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 978
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Author:
Publisher:
ISBN:
Category : Public administration
Languages : en
Pages : 1228
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Author: Chaitanya D Ghodke
Publisher: SAE International
ISBN: 0768095026
Category : Technology & Engineering
Languages : en
Pages : 238
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Book Description
Gas turbines play an extremely important role in fulfilling a variety of power needs and are mainly used for power generation and propulsion applications. The performance and efficiency of gas turbine engines are to a large extent dependent on turbine rotor inlet temperatures: typically, the hotter the better. In gas turbines, the combustion temperature and the fuel efficiency are limited by the heat transfer properties of the turbine blades. However, in pushing the limits of hot gas temperatures while preventing the melting of blade components in high-pressure turbines, the use of effective cooling technologies is critical. Increasing the turbine inlet temperature also increases heat transferred to the turbine blade, and it is possible that the operating temperature could reach far above permissible metal temperature. In such cases, insufficient cooling of turbine blades results in excessive thermal stress on the blades causing premature blade failure. This may bring hazards to the engine's safe operation. Gas Turbine Blade Cooling, edited by Dr. Chaitanya D. Ghodke, offers 10 handpicked SAE International's technical papers, which identify key aspects of turbine blade cooling and help readers understand how this process can improve the performance of turbine hardware.
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
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