Download or read book An Experimental Study of Heat Transfer in the Rectangular Coolant Passages of a Gas Turbine Rotor Blade written by Mohammed Jalal Uddin and published by . This book was released on 2000 with total page 138 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental and Analytical Investigation of Heat transfer Characteristics of a Return flow Air cooled Turbine Rotor Blade written by Francis S. Stepka and published by . This book was released on 1959 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of Diameter of Closed end Coolant Passages on Natural convection Water Cooling of Gas turbine Blades written by Arthur N. Curren and published by . This book was released on 1956 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation on a water-cooled gas turbine with blade coolant-passage diameters ranging from 0.100 to 0.500 inch, corresponding to length-to-diameter ratios of 25.5 to 5.1, in various quadrants of the turbine. The investigation was conducted to determine (1) whether coolant-passage length-to-ratio has a significant effect on natural-convection heat-transfer correlation, and (2) whether turbine blade temperatures could be calculated with reasonable accuracy from a theoretical natural-convection heat-transfer correlation.
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.
Download or read book Effect of Blade tip Crossover Passages on Natural convection Water cooling of Gas turbine Blades written by Charles F. Zalabak and published by . This book was released on 1956 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book An Experimental Study of Heat Transfer in the Cooling Passages of Gas Turbine Rotor Blades written by Shyy Woei Chang and published by . This book was released on 1995 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Blade to coolant Heat transfer Results and Operating Data from a Natural convection Water cooled Single stage Turbine written by Anthony J. Diaguila and published by . This book was released on 1951 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Determination of Blade to coolant Heat transfer Coefficients on a Forced convection Water cooled Single stage Turbine written by John C. Freche and published by . This book was released on 1951 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of the Heat transfer Characteristics of an Air cooled Sintered Porous Turbine Blade written by Louis J. Schafer (Jr.) and published by . This book was released on 1952 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of Air cooled Turbine Blades in Turbojet Engine written by Robert O. Hickel and published by . This book was released on 1950 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Cooling of Gas Turbines written by W. Byron Brown and published by . This book was released on 1947 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Study of Gas Turbine Blade Film Cooling and Heat Transfer written by Diganta P. Narzary and published by . This book was released on 2010 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Modern gas turbine engines require higher turbine-entry gas temperature to improve their thermal efficiency and thereby their performance. A major accompanying concern is the heat-up of the turbine components which are already subject to high thermal and mechanical stresses. This heat-up can be reduced by: (i) applying thermal barrier coating (TBC) on the surface, and (ii) providing coolant to the surface by injecting secondary air discharged from the compressor. However, as the bleeding off of compressor discharge air exacts a penalty on engine performance, the cooling functions must be accomplished with the smallest possible secondary air injection. This necessitates a detailed and systematic study of the various flow and geometrical parameters that may have a bearing on the cooling pattern. In the present study, experiments were performed in three regions of a non-rotating gas turbine blade cascade: blade platform, blade span, and blade tip. The blade platform and blade span studies were carried out on a high pressure turbine rotor blade cascade in medium flow conditions. Film-cooling effectiveness or degree of cooling was assessed in terms of cooling hole geometry, blowing ratio, freestream turbulence, coolant-to-mainstream density ratio, purge flow rate, upstream vortex for blade platform cooling and blowing ratio, and upstream vortex for blade span cooling. The blade tip study was performed in a blow-down flow loop in a transonic flow environment. The degree of cooling was assessed in terms of blowing ratio and tip clearance. Limited heat transfer coefficient measurements were also carried out. Mainstream pressure loss was also measured for blade platform and blade tip film-cooling with the help of pitot-static probes. The pressure sensitive paint (PSP) and temperature sensitive paint (TSP) techniques were used for measuring film-cooling effectiveness whereas for heat transfer coefficient measurement, temperature sensitive paint (TSP) technique was employed. Results indicated that the blade platform cooling requires a combination of upstream purge flow and downstream discrete film-cooling holes to cool the entire platform. The shaped cooling holes provided wider film coverage and higher film-cooling effectiveness than the cylindrical holes while also creating lesser mainstream pressure losses. Higher coolant-to-mainstream density ratio resulted in higher effectiveness levels from the cooling holes. On the blade span, at any given blowing ratio, the suction side showed better coolant coverage than the pressure side even though the former had two fewer rows of holes. Film-cooling effectiveness increased with blowing ratio on both sides of the blade. Whereas the pressure side effectiveness continued to increase with blowing ratio, the increase in suction side effectiveness slowed down at higher blowing ratios (M=0.9 and 1.2). Upstream wake had a detrimental effect on film coverage. 0% and 25% wake phase positions significantly decreased film-cooling effectiveness magnitude. Comparison between the compound shaped hole and the compound cylindrical hole design showed higher effectiveness values for shaped holes on the suction side. The cylindrical holes performed marginally better in the curved portion of the pressure side. Finally, the concept tip proved to be better than the baseline tip in terms of reducing mainstream flow leakage and mainstream pressure loss. The film-cooling effectiveness on the concept blade increased with increasing blowing ratio and tip gap. However, the film-coverage on the leading tip portion was almost negligible.
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.
Download or read book Cooling of Gas Turbines written by W. Byron Brown and published by . This book was released on 1947 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Download or read book NASA Technical Paper written by and published by . This book was released on 1984 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of Air cooled Turbine Blades in Turbojet Engine written by Vernon L. Arne and published by . This book was released on 1951 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
