An Experimental Investigation Of Turbine Blade Heat Transfer And Turbine Blade Trailing Edge Cooling
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An Experimental Investigation Of Turbine Blade Heat Transfer And Turbine Blade Trailing Edge Cooling
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Author : Jungho Choi
language : en
Publisher:
Release Date : 2005
An Experimental Investigation Of Turbine Blade Heat Transfer And Turbine Blade Trailing Edge Cooling written by Jungho Choi and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2005 with categories.
This experimental study contains two points; part 1 - turbine blade heat transfer under low Reynolds number flow conditions, and part 2 - trailing edge cooling and heat transfer. The effect of unsteady wake and free stream turbulence on heat transfer and pressure coefficients of a turbine blade was investigated in low Reynolds number flows. The experiments were performed on a five blade linear cascade in a low speed wind tunnel. A spoked wheel type wake generator and two different turbulence grids were employed to generate different levels of the Strouhal number and turbulence intensity, respectively. The cascade inlet Reynolds number based on blade chord length was varied from 15,700 to 105,000, and the Strouhal number was varied from 0 to 2.96 by changing the rotating wake passing frequency (rod speed) and cascade inlet velocity. A thin foil thermocouple instrumented blade was used to determine the surface heat transfer coefficient. A Liquid crystal technique based on hue value detection was used to measure the heat transfer coefficient on a trailing edge film cooling model and internal model of a gas turbine blade. It was also used to determine the film effectiveness on the trailing edge. For the internal model, Reynolds numbers based on the hydraulic diameter of the exit slot and exit velocity were 5,000, 10,000, 20,000, and 30,000 and corresponding coolant-to-mainstream velocity ratios were 0.3, 0.6, 1.2, and 1.8 for the external models, respectively. The experiments were performed at two different designs and each design has several different models such as staggered / inline exit, straight / tapered entrance, and smooth / rib entrance. The compressed air was used in coolant air. A circular turbulence grid was employed to upstream in the wind tunnel and square ribs were employed in the inlet chamber to generate turbulence intensity externally and internally, respectively.
Experimental Investigation Of Turbine Blade Platform Film Cooling And Rotational Effect On Trailing Edge Internal Cooling
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Author : Lesley Mae Wright
language : en
Publisher:
Release Date : 2010
Experimental Investigation Of Turbine Blade Platform Film Cooling And Rotational Effect On Trailing Edge Internal Cooling written by Lesley Mae Wright and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2010 with categories.
The present work has been an experimental investigation to evaluate the applicability of gas turbine cooling technology. With the temperature of the mainstream gas entering the turbine elevated above the melting temperature of the metal components, these components must be cooled, so they can withstand prolonged exposure to the mainstream gas. Both external and internal cooling techniques have been studied as a means to increase the life of turbine components. Detailed film cooling effectiveness distributions have been obtained on the turbine blade platform with a variety of cooling configurations. Because the newly developed pressure sensitive paint (PSP) technique has proven to be the most suitable technique for measuring the film effectiveness, it was applied to a variety of platform seal configurations and discrete film flows. From the measurements it was shown advanced seals provide more uniform protection through the passage with less potential for ingestion of the hot mainstream gases into the engine cavity. In addition to protecting the outer surface of the turbine components, via film cooling, heat can also be removed from the components internally. Because the turbine blades are rotating within the engine, it is important to consider the effect of rotation on the heat transfer enhancement within the airfoil cooling channels. Through this experimental investigation, the heat transfer enhancement has been measured in narrow, rectangular channels with various turbulators. The present experimental investigation has shown the turbulators, coupled with the rotation induced Coriolis and buoyancy forces, result in non-uniform levels of heat transfer enhancement in the cooling channels. Advanced turbulator configurations can be used to provide increased heat transfer enhancement. Although these designs result in increased frictional losses, the benefit of the heat transfer enhancement outweighs the frictional losses.
Experimental Investigation Of The Heat Transfer Characteristics Of An Air Cooled Sintered Porous Turbine Blade
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Author : Louis J. Schafer (Jr.)
language : en
Publisher:
Release Date : 1952
Experimental Investigation Of The Heat Transfer Characteristics Of An Air Cooled Sintered Porous Turbine Blade written by Louis J. Schafer (Jr.) and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1952 with Aeronautics categories.
Experimental Investigation Of Air Cooled Turbine Blades In Turbojet Engine
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Author : Robert O. Hickel
language : en
Publisher:
Release Date : 1950
Experimental Investigation Of Air Cooled Turbine Blades In Turbojet Engine written by Robert O. Hickel and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1950 with Aeronautics categories.
Experimental Investigation Of Cross Over Jets In A Rib Roughened Trailing Edge Cooling Channel
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Author : Fei Xue
language : en
Publisher:
Release Date : 2015
Experimental Investigation Of Cross Over Jets In A Rib Roughened Trailing Edge Cooling Channel written by Fei Xue and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2015 with Aerofoils categories.
Increasing the rotor inlet temperature can dramatically increase the efficiency and power output of the gas turbine engine. However, the melting point of turbine blade material limits the realistic upper bound of the rotor inlet temperature. As a result, the development of high temperature turbine blade material and advanced turbine blade cooling technology determines the future of turbine blade engine. Adding impingement jet holes and rib turbulators in the inner cooling channel of the gas turbine blades are two effective ways to enhance the cooling effects. The purpose of this study is to figure out the influence of different combinations of jet holes and rib turbulators on the heat transfer efficiency. A tabletop scale test model is used in the study to simulate the cooling cavity of trailing edge and its feed channel in a real gas turbine blade. The Dimensional Analysis Theory is used in the study to eliminate the influence of scaling. Two different crossover slots are tested with 5 different rib arrangements, and each of the test geometries is tested for 6 jet Reynolds numbers ranging from 10,000 to 36,000. The two different crossover slots are the crossover slots with 0 and 5 degree tilt angles. The four different rib arrangements are ribs with 0 degree, 45 degree, 90 degree and 135 degree angles of attack with respect to the flow direction. Furthermore, a smooth test section (no ribs) was also tested. The steady state liquid crystal thermography is used to quantify the heat transfer performance of the target areas. The variation of Nusselt number versus Reynolds number is plotted for each of the 10 geometries. Also, the variation of Nusselt number versus Reynolds number are compared for different rib angles of attack with the same crossover slot tilt angle, and between different crossover slots tilt angles with the same rib angle. The results show that, the area-weighted average Nusselt number increases monotonically with the Reynolds number; the target areas near the open end have a larger Nusselt number comparing with the ones near the close end; the 90 degree rib angle has the highest Nusselt number among the 4 rib angles of attack and the smooth wall channel; the crossover slots with 0 degree tilt angle produce higher convective heat transfer coefficients than the crossover slots with 5 degree tilt angle. Possible physical explanations for the result are offered by the author.
Experimental Investigation Of Air Cooled Turbine Blades In Turbojet Engine
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Author : Vernon L. Arne
language : en
Publisher:
Release Date : 1951
Experimental Investigation Of Air Cooled Turbine Blades In Turbojet Engine written by Vernon L. Arne and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with Aeronautics categories.
Experimental Investigation Of The Aerodynamics Of Turbine Blade Trailing Edge Cooling At Transonic Speeds
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Author : Veera P. Rajendran
language : en
Publisher:
Release Date : 2000
Experimental Investigation Of The Aerodynamics Of Turbine Blade Trailing Edge Cooling At Transonic Speeds written by Veera P. Rajendran and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2000 with categories.
Experimental Investigation Of Air Cooled Turbine Blades In Turbojet Engine
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Author : Herman H. Ellerbrock (Jr.)
language : en
Publisher:
Release Date : 1951
Experimental Investigation Of Air Cooled Turbine Blades In Turbojet Engine written by Herman H. Ellerbrock (Jr.) and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with Aeronautics categories.
Analytical And Experimental Investigation Of A Forced Convection Air Cooled Internal Strut Supported Turbine Blade
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Author : Eugene F. Schum
language : en
Publisher:
Release Date : 1954
Analytical And Experimental Investigation Of A Forced Convection Air Cooled Internal Strut Supported Turbine Blade written by Eugene F. Schum and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1954 with Air-cooled engines categories.
Experimental Investigation Of Air Cooled Turbine Blades In Turbojet Engine
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Author : Jack B. Esgar
language : en
Publisher:
Release Date : 1952
Experimental Investigation Of Air Cooled Turbine Blades In Turbojet Engine written by Jack B. Esgar and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1952 with Aeronautics categories.