Crossflow Effects On Impingement Cooling Of A Turbine Vane
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Crossflow Effects On Impingement Cooling Of A Turbine Vane
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Author :
language : en
Publisher:
Release Date : 1974
Crossflow Effects On Impingement Cooling Of A Turbine Vane written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1974 with Cascades (Fluid dynamics) categories.
Crossflow Effects On Impingement Cooling Of A Turbine Vane
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Author :
language : en
Publisher:
Release Date : 1974
Crossflow Effects On Impingement Cooling Of A Turbine Vane written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1974 with categories.
An air-cooled turbine vane was tested in a four-vane cascade. Heat transfer characteristics of the impingement cooled midchord region are reported. Experimental Nusselt numbers of six midchord locations are examined for the effect of crossflow and compared to those predicted by impingement correlations found in the literature.
Crossflow Effects On Impingement Cooling Of A Turbine Vane
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Author :
language : en
Publisher:
Release Date : 1974
Crossflow Effects On Impingement Cooling Of A Turbine Vane written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1974 with Cascades (Fluid dynamics) categories.
Characterization Of An Inline Row Impingement Channel For Turbine Blade Cooling Applications
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Author : Mark A. Ricklick
language : en
Publisher:
Release Date : 2009
Characterization Of An Inline Row Impingement Channel For Turbine Blade Cooling Applications written by Mark A. Ricklick and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2009 with Heat categories.
Gas turbines have become an intricate part of today's society. Besides powering practically all 200,000+ passenger aircraft in use today, they are also a predominate form of power generation when coupled with a generator. The fact that they are highly efficient, and capable of large power to weight ratios, makes gas turbines an ideal solution for many power requirement issues faced today. Designers have even been able to develop small, 'micro' turbines capable of producing efficient portable power. Part of the turbine's success is the fact that their efficiency levels have continuously risen since their introduction in the early 1800's. Along with improvements in our understanding and designs of the aerodynamic components of the turbine, as well as improvements in the areas of material design and combustion control, advances in component cooling techniques have predominantly contributed to this success. This is the result of a simple thermodynamic concept; as the turbine inlet temperature is increased, the overall efficiency of the machine increases as well. Designers have exploited this fact to the extent that modern gas turbines produce rotor inlet temperatures beyond the melting point of the sophisticated materials used within them. This has only been possible through the use of sophisticated cooling techniques, particularly in the 1st stage vanes and blades. Some of the cooling techniques employed today have been internal cooling channels enhanced with various features, film and showerhead cooling, as well as internal impingement cooling scenarios. Impingement cooling has proven to be one of the most capable heat removal processes, and the combination of this cooling feature with that of channel flow, as is done in impingement channel cooling, creates a scenario that has understandably received a great deal of attention in recent years. This study has investigated several of the unpublished characteristics of these impingement channels, including the channel height effects on the performance of the channel side walls, effects of bulk temperature increase on heat transfer coefficients, circumferential heat variation effects, and effects on the uniformity of the heat transfer distribution. The main objectives of this dissertation are to explore the various previously unstudied characteristics of impingement channels, in order to sufficiently predict their performance in a wide range of applications. The potential exists, therefore, for a designer to develop a blade with cooling characteristics specifically tailored to the expected component thermal loads. Temperature sensitive paint (TSP) is one of several non-intrusive optical temperature measurements techniques that have gained a significant amount of popularity in the last decade. By employing the use of TSP, we have the ability to provide very accurate (less than 1 degree Celsius uncertainty), high resolution full-field temperature measurements. This has allowed us to investigate the local heat transfer characteristics of the various channel surfaces under a variety of steady state testing conditions. The comparison of thermal performance and uniformity for each impingement channel configuration then highlights the benefits and disadvantages of various configurations. Through these investigations, it has been shown that the channel side walls provide heat transfer coefficients comparable to those found on the target surface, especially at small impingement heights. Although the side walls suffer from highly non-uniform performance near the start of the channel, the profiles become very uniform as the cross flow develops and becomes a dominating contributor to the heat transfer coefficient. Increases in channel height result in increased non-uniformity in the streamwise direction and decreased heat transfer levels. Bulk temperature increases have also been shown to be an important consideration when investigating surfaces dominated by cross flow heat transfer effects, as enhancements up to 80% in some areas may be computed. Considerations of these bulk temperature changes also allow the determination of the point at which the flow transitions from an impingement dominated regime to one that is dominated by cross flow effects. Finally, circumferential heat variations have proven to have negligible effects on the calculated heat transfer coefficient, with the observed differences in heat transfer coefficient being contributed to the unaccounted variations in channel bulk temperature.
Nasa Technical Memorandum
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Author :
language : en
Publisher:
Release Date : 1991
Nasa Technical Memorandum written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1991 with Aeronautics categories.
Effects Of Different Cross Flow Schemes For Array Jet Impingement Cooling With Bidirectional Exits
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Author : Ganesh Subbarama Iyer
language : en
Publisher:
Release Date : 2023
Effects Of Different Cross Flow Schemes For Array Jet Impingement Cooling With Bidirectional Exits written by Ganesh Subbarama Iyer and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2023 with 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.
Gas Turbine Heat Transfer And Cooling Technology Second Edition
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Author : Je-Chin Han
language : en
Publisher: CRC Press
Release Date : 2012-11-27
Gas Turbine Heat Transfer And Cooling Technology Second Edition written by Je-Chin Han and has been published by CRC Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 2012-11-27 with Science categories.
A comprehensive reference for engineers and researchers, Gas Turbine Heat Transfer and Cooling Technology, Second Edition has been completely revised and updated to reflect advances in the field made during the past ten years. The second edition retains the format that made the first edition so popular and adds new information mainly based on selected published papers in the open literature. See What’s New in the Second Edition: State-of-the-art cooling technologies such as advanced turbine blade film cooling and internal cooling Modern experimental methods for gas turbine heat transfer and cooling research Advanced computational models for gas turbine heat transfer and cooling performance predictions Suggestions for future research in this critical technology The book discusses the need for turbine cooling, gas turbine heat-transfer problems, and cooling methodology and covers turbine rotor and stator heat-transfer issues, including endwall and blade tip regions under engine conditions, as well as under simulated engine conditions. It then examines turbine rotor and stator blade film cooling and discusses the unsteady high free-stream turbulence effect on simulated cascade airfoils. From here, the book explores impingement cooling, rib-turbulent cooling, pin-fin cooling, and compound and new cooling techniques. It also highlights the effect of rotation on rotor coolant passage heat transfer. Coverage of experimental methods includes heat-transfer and mass-transfer techniques, liquid crystal thermography, optical techniques, as well as flow and thermal measurement techniques. The book concludes with discussions of governing equations and turbulence models and their applications for predicting turbine blade heat transfer and film cooling, and turbine blade internal cooling.
Nasa Technical Paper
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Author :
language : en
Publisher:
Release Date : 1984
Nasa Technical Paper written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1984 with Science categories.
Monthly Catalog Of United States Government Publications
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Author :
language : en
Publisher:
Release Date : 1974
Monthly Catalog Of United States Government Publications written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1974 with Government publications categories.