Cooling Of Gas Turbines Ii Effectiveness Of Rim Cooling Of Blades
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Cooling Of Gas Turbines Ii Effectiveness Of Rim Cooling Of Blades
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Author : Lincoln Wolfenstein
language : en
Publisher:
Release Date : 1947
Cooling Of Gas Turbines Ii Effectiveness Of Rim Cooling Of Blades written by Lincoln Wolfenstein and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1947 with categories.
Cooling Of Gas Turbines
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Author : Lincoln Wolfenstein
language : en
Publisher:
Release Date : 1947
Cooling Of Gas Turbines written by Lincoln Wolfenstein and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1947 with Aeronautics categories.
Cooling Of Gas Turbines 2
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Author : Lincoln Wolfenstein
language : en
Publisher: BiblioGov
Release Date : 2013-07
Cooling Of Gas Turbines 2 written by Lincoln Wolfenstein and has been published by BiblioGov this book supported file pdf, txt, epub, kindle and other format this book has been release on 2013-07 with categories.
An analysis of rim cooling, which cools the blade by condition alone, was conducted. Gas temperatures ranged from 1300 degrees to 1900 degrees F and rim temperatures from 0 degrees to 1000 degrees F below gas temperatures. Results show that gas temperature increases up to 200 degrees F are permissible provided that the blades are cooled by 400 degrees to 500 degrees F below the gas temperature. Relatively small amounts of blade cooling, at constant gas temperature, give large increases in blade life. Dependence of rim cooling on heat-transfer coefficient, blade dimensions, and thermal conductivity is determined by a single parameter.
Cooling Of Gas Turbines
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Author : W. Byron Brown
language : en
Publisher:
Release Date : 1948
Cooling Of Gas Turbines written by W. Byron Brown and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1948 with Aeronautics categories.
Cooling Of Gas Turbines
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Author : W. Byron Brown
language : en
Publisher:
Release Date : 1947
Cooling Of Gas Turbines written by W. Byron Brown and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1947 with Aeronautics categories.
Gas Turbine Blade Cooling
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Author : Chaitanya D Ghodke
language : en
Publisher: SAE International
Release Date : 2018-12-10
Gas Turbine Blade Cooling written by Chaitanya D Ghodke and has been published by SAE International this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-12-10 with Technology & Engineering categories.
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.
Survey Of Advantages And Problems Associated With Transpiration Cooling And Film Cooling Of Gas Turbine Blades
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Author : Ernst Rudolf Georg Eckert
language : en
Publisher:
Release Date : 1951
Survey Of Advantages And Problems Associated With Transpiration Cooling And Film Cooling Of Gas Turbine Blades written by Ernst Rudolf Georg Eckert and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with Aerodynamics categories.
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.
Cooling Of Gas Turbines
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Author : W. Byron Brown
language : en
Publisher:
Release Date : 1947
Cooling Of Gas Turbines written by W. Byron Brown and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1947 with Aeronautics categories.
Cooling Of Gas Turbines 1 Effects Of Admission Of Fins To Blade Tips And Rotor Admission Of Cooling Air Through Part Of Nozzles And Change In Thermal Conductivity Of Turbine Components
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Author :
language : en
Publisher:
Release Date : 1947
Cooling Of Gas Turbines 1 Effects Of Admission Of Fins To Blade Tips And Rotor Admission Of Cooling Air Through Part Of Nozzles And Change In Thermal Conductivity Of Turbine Components written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1947 with categories.
Analysis was made for calculating the approximate radial temperature distribution in components of a turbosupercharger bucket wheel. Gas temperatures at nozzle box are used in calculations ranging from 1600 degree to 2000 deg F. Only temperatures of the gas, cooling air, and surface heat-transfer coefficients were known. Results show that indirect cooling of turbine blades will not permit large increases in effective gas temperature. With low conductivity materials, some method of direct cooling other than partial admission of cooling air is essential.
Effect Of Blade Tip Crossover Passages On Natural Convection Water Cooling Of Gas Turbine Blades
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Author : Charles F. Zalabak
language : en
Publisher:
Release Date : 1956
Effect Of Blade Tip Crossover Passages On Natural Convection Water Cooling Of Gas Turbine Blades written by Charles F. Zalabak and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1956 with Aircraft gas-turbines categories.
A water-cooled turbine was fabricated and tested to determine the effect of a connecting passage at the turbine rotor blade tip between a radial coolant passage 0.10 inch in diameter (length-diameter ratio = 25.5) and radial coolant passages in the legnth-diameter range of 5.1 to 20.4. Coolant flow through the connecting passage is induced by free-convection forces in the radial passages.