Thermomechanical Stress Analysis of Advanced Turbine Blade Cooling Configuration PDF Download
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Author: University of Kentucky. College of Engineering
Publisher:
ISBN:
Category : Turbines
Languages : en
Pages : 63
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Book Description
Author: University of Kentucky. College of Engineering
Publisher:
ISBN:
Category : Turbines
Languages : en
Pages : 63
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Book Description
Author: Frank J. Rizzo
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 49
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Book Description
Program improvement features in a Boundary Integral Equation Analysis Capability for thermomechanical problems are described. A number of solved problems are presented along with a progress report on the research directed toward a thermomechanical stress analysis in the vicinity of a cooling hole in a film-cooled turbine blade. (Author).
Author: F. J. Rizzo
Publisher:
ISBN:
Category :
Languages : en
Pages : 67
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Book Description
A thermo-mechanical stress analysis capability, based on the Boundary Integral Equation Method (BIE) is developed and described. The capability is used to provide a thermoelastic analysis of stress in the vicinity of cooling holes in turbojet blades with transpiration or film cooling. Details involved in the formulation, numerical procedures, mathematical modelling, and data from solved problems are presented. (Author).
Author: Frank J. Rizzo
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 72
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Book Description
Author: Albert Kaufman
Publisher:
ISBN:
Category : Turbines
Languages : en
Pages : 52
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 300
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Book Description
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: A. Kaufman
Publisher:
ISBN:
Category : Gliders (Aeronautics)
Languages : en
Pages : 38
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Author: Erich Pollman
Publisher:
ISBN:
Category : Blades
Languages : en
Pages : 600
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Book Description
The present treatise reports on theoretical investigations and test-stand measurements which were carried out in the BMW Flugmotoren GMbH in developing the hollow blade for exhaust gas turbines. As an introduction the temperature variation and the stress on a turbine blade for a gas temperature of 900 degrees and circumferential velocities of 600 meters per second are discussed. The assumptions onthe heat transfer coefficients at the blade profile are supported by tests on an electrically heated blade model. The temperature distribution in the cross section of a blade Is thoroughly investigated and the temperature field determined for a special case. A method for calculation of the thermal stresses in turbine blades for a given temperature distribution is indicated. The effect of the heat radiation on the blade temperature also is dealt with. Test-stand experiments on turbine blades are evaluated, particularly with respect to temperature distribution in the cross section; maximum and minimum temperature in the cross section are ascertained. Finally, the application of the hollow blade for a stationary gas turbine is investigated. Starting from a setup for 550 C gas temperature the improvement of the thermal efficiency and the fuel consumption are considered as well as the increase of the useful power by use of high temperatures. The power required for blade cooling is taken into account.
Author:
Publisher:
ISBN:
Category : Engines
Languages : en
Pages : 232
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Book Description
