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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.
Book Synopsis Gas Turbine Blade Cooling by : Chaitanya D Ghodke
Download or read book Gas Turbine Blade Cooling written by Chaitanya D Ghodke and published by SAE International. This book was released on 2018-12-10 with total page 238 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 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.
Book Synopsis Gas Turbine Blade Cooling by :
Download or read book Gas Turbine Blade Cooling written by and published by . This book was released on 2018 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 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.
Book Synopsis Gas Turbine Blade Cooling by : Chaitanya D Ghodke
Download or read book Gas Turbine Blade Cooling written by Chaitanya D Ghodke and published by SAE International. This book was released on 2018-12-10 with total page 238 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
This 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.
Book Synopsis Gas Turbine Blade Cooling by : Chaitanya D. Ghodke
Download or read book Gas Turbine Blade Cooling written by Chaitanya D. Ghodke and published by . This book was released on 2018 with total page 236 pages. Available in PDF, EPUB and Kindle. Book excerpt: This 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.
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.
Book Synopsis Gas Turbine Heat Transfer and Cooling Technology, Second Edition by : Je-Chin Han
Download or read book Gas Turbine Heat Transfer and Cooling Technology, Second Edition written by Je-Chin Han and published by CRC Press. This book was released on 2012-11-27 with total page 892 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
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.
Book Synopsis Survey of Advantages and Problems Associated with Transpiration Cooling and Film Cooling of Gas-turbine Blades by : Ernst Rudolf Georg Eckert
Download or read book Survey of Advantages and Problems Associated with Transpiration Cooling and Film Cooling of Gas-turbine Blades written by Ernst Rudolf Georg Eckert and published by . This book was released on 1951 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Everything you wanted to know about industrial gas turbines for electric power generation in one source with hard-to-find, hands-on technical information.
Book Synopsis Gas Turbines for Electric Power Generation by : S. Can Gülen
Download or read book Gas Turbines for Electric Power Generation written by S. Can Gülen and published by Cambridge University Press. This book was released on 2019-02-14 with total page 735 pages. Available in PDF, EPUB and Kindle. Book excerpt: Everything you wanted to know about industrial gas turbines for electric power generation in one source with hard-to-find, hands-on technical information.
Due to the requirement for enhanced cooling technologies on modern gas turbine engines, advanced research and development has had to take place in field of thermal engineering. Among the gas turbine cooling technologies, impingement jet cooling is one of the most effective in terms of cooling effectiveness, manufacturability and cost. The chapters contained in this book describe research on state-of-the-art and advanced cooling technologies that have been developed, or that are being researched, with a variety of approaches from theoretical, experimental, and CFD studies. The authors of the chapters have been selected from some of the most active researchers and scientists on the subject. This is the first to book published on the topics of gas turbines and heat transfer to focus on impingement cooling alone.
Book Synopsis Impingement Jet Cooling in Gas Turbines by : R.S. Amano
Download or read book Impingement Jet Cooling in Gas Turbines written by R.S. Amano and published by WIT Press. This book was released on 2014-05-28 with total page 253 pages. Available in PDF, EPUB and Kindle. Book excerpt: Due to the requirement for enhanced cooling technologies on modern gas turbine engines, advanced research and development has had to take place in field of thermal engineering. Among the gas turbine cooling technologies, impingement jet cooling is one of the most effective in terms of cooling effectiveness, manufacturability and cost. The chapters contained in this book describe research on state-of-the-art and advanced cooling technologies that have been developed, or that are being researched, with a variety of approaches from theoretical, experimental, and CFD studies. The authors of the chapters have been selected from some of the most active researchers and scientists on the subject. This is the first to book published on the topics of gas turbines and heat transfer to focus on impingement cooling alone.
Book Synopsis Cooling of Gas Turbines by : W. Byron Brown
Download or read book Cooling of Gas Turbines written by W. Byron Brown and published by . This book was released on 1948 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Gas turbine inlet temperatures continue to increase in an effort to improve efficiency. Therefore, effective cooling of hot section components is necessary to reduce deterioration and maintain part life. Despite the best efforts of engine designers, coolant flow blockages or degradation of thermal barrier coatings will nevertheless occur during operation and lead to increased surface temperatures that reduce blade life. This phenomenon is especially prevalent in environments where sand or other small particles are ingested into engines. Part-to-part manufacturing variations also lead to significant changes in geometry relative to design intent that impact the flow and cooling effectiveness of turbine components, even when the deviations are within defined tolerances. This thesis examines part-to-part variations in geometry, flow, and cooling effectiveness for true scale turbine blades. A set of engine-run blades with varying levels of environmental deterioration was operated at engine-relevant conditions and surface temperature was measured using infrared thermography. These measurements were used to calculate cooling effectiveness and expected blade life. Blade flow parameter and cooling effectiveness were both high for blades operated in a benign environment, even though the benign run time blades had the highest run time of the blades measured. Blades operated in a harsh environment not only had lower cooling effectiveness, but also more variation in cooling effectiveness between blades. Film cooling trajectories were calculated for each set of blades tested, and showed that all engine-run blades had a significant reduction in maximum cooling effectiveness behind cooling holes with respect to a set of baseline blades. Cooling effectiveness values were then used to scale surface temperatures up to actual engine operating conditions extracted from the NASA E3 program. While lifing curves from previous literature were able to predict blade temperatures for benign environment blades, surface temperature increased much more than expected for harsh operator blades. A second study analyzed the flow performance and geometry of additively manufactured turbine blades with drilled film cooling holes. A benchtop flow rig was used to characterize flow through the full blade as well as isolated regions of the blade. While partial flow through specific regions of the blade did not match design intent, the total flow through the blade varied by less than 10% between the minimum and maximum flow blades at the design pressure ratio. Computed tomography scans were used to analyze the geometry of cooling features such as film cooling holes, crossover holes, turbulators, and pin fins. Shaped film cooling holes manufactured with a conventional electrical discharge machining (EDM) method were undersized throughout the entire cooling hole. A high-speed EDM method created holes that met design specifications in the metering section, but were also undersized at the hole exit. Additively manufactured features such as turbulators and pin fins were close to design intent shape and size, with the largest variations occurring on downskin surfaces that were unsupported during the build. Roughness was high on both internal and external blade surfaces, particularly for regions with the thinnest walls. This study demonstrated the viability of applying additively manufacturing and advanced hole drill methods to study new turbine cooling technologies at an accelerated timeline and reduced cost.
Book Synopsis Impacts of Part-to-Part Variability on Gas Turbine Blade Cooling by : Kelsey Mc Cormack
Download or read book Impacts of Part-to-Part Variability on Gas Turbine Blade Cooling written by Kelsey Mc Cormack and published by . This book was released on 2023 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Gas turbine inlet temperatures continue to increase in an effort to improve efficiency. Therefore, effective cooling of hot section components is necessary to reduce deterioration and maintain part life. Despite the best efforts of engine designers, coolant flow blockages or degradation of thermal barrier coatings will nevertheless occur during operation and lead to increased surface temperatures that reduce blade life. This phenomenon is especially prevalent in environments where sand or other small particles are ingested into engines. Part-to-part manufacturing variations also lead to significant changes in geometry relative to design intent that impact the flow and cooling effectiveness of turbine components, even when the deviations are within defined tolerances. This thesis examines part-to-part variations in geometry, flow, and cooling effectiveness for true scale turbine blades. A set of engine-run blades with varying levels of environmental deterioration was operated at engine-relevant conditions and surface temperature was measured using infrared thermography. These measurements were used to calculate cooling effectiveness and expected blade life. Blade flow parameter and cooling effectiveness were both high for blades operated in a benign environment, even though the benign run time blades had the highest run time of the blades measured. Blades operated in a harsh environment not only had lower cooling effectiveness, but also more variation in cooling effectiveness between blades. Film cooling trajectories were calculated for each set of blades tested, and showed that all engine-run blades had a significant reduction in maximum cooling effectiveness behind cooling holes with respect to a set of baseline blades. Cooling effectiveness values were then used to scale surface temperatures up to actual engine operating conditions extracted from the NASA E3 program. While lifing curves from previous literature were able to predict blade temperatures for benign environment blades, surface temperature increased much more than expected for harsh operator blades. A second study analyzed the flow performance and geometry of additively manufactured turbine blades with drilled film cooling holes. A benchtop flow rig was used to characterize flow through the full blade as well as isolated regions of the blade. While partial flow through specific regions of the blade did not match design intent, the total flow through the blade varied by less than 10% between the minimum and maximum flow blades at the design pressure ratio. Computed tomography scans were used to analyze the geometry of cooling features such as film cooling holes, crossover holes, turbulators, and pin fins. Shaped film cooling holes manufactured with a conventional electrical discharge machining (EDM) method were undersized throughout the entire cooling hole. A high-speed EDM method created holes that met design specifications in the metering section, but were also undersized at the hole exit. Additively manufactured features such as turbulators and pin fins were close to design intent shape and size, with the largest variations occurring on downskin surfaces that were unsupported during the build. Roughness was high on both internal and external blade surfaces, particularly for regions with the thinnest walls. This study demonstrated the viability of applying additively manufacturing and advanced hole drill methods to study new turbine cooling technologies at an accelerated timeline and reduced cost.
