Experimental Study Of Impingement Cooling In Rotating Turbine Blades
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Experimental Study Of Impingement Cooling In Rotating Turbine Blades
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Author : Massachusetts Institute of Technology. Gas Turbine & Plasma Dynamics Laboratory
language : en
Publisher:
Release Date : 1983
Experimental Study Of Impingement Cooling In Rotating Turbine Blades written by Massachusetts Institute of Technology. Gas Turbine & Plasma Dynamics Laboratory and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1983 with categories.
Experimental Data Correlations For The Effects Of Rotation On Impingement Cooling Of Turbine Blades
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Author : J.C. Kreatsoulas
language : en
Publisher:
Release Date : 1987
Experimental Data Correlations For The Effects Of Rotation On Impingement Cooling Of Turbine Blades written by J.C. Kreatsoulas and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1987 with categories.
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.
Channel Flow Modeling Of Impingement Cooling Of A Rotating Turbine Blade
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Author : JaHye Jenny Koo
language : en
Publisher:
Release Date : 1984
Channel Flow Modeling Of Impingement Cooling Of A Rotating Turbine Blade written by JaHye Jenny Koo and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1984 with Cooling categories.
Numerical And Experimental Study On Turbine Blade Cooling Turbulent Flow And Surface Heat Transfer
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Author : Liang Guo
language : en
Publisher:
Release Date : 2011
Numerical And Experimental Study On Turbine Blade Cooling Turbulent Flow And Surface Heat Transfer written by Liang Guo and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2011 with Gas-turbines categories.
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 Study Of Gas Turbine Blade Film Cooling And Heat Transfer
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Author : Diganta P. Narzary
language : en
Publisher:
Release Date : 2010
Experimental Study Of Gas Turbine Blade Film Cooling And Heat Transfer written by Diganta P. Narzary 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.
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.
An Experimental Study Of The Effect Of Wake Passing On Turbine Blade Film Cooling
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-08-16
An Experimental Study Of The Effect Of Wake Passing On Turbine Blade Film Cooling written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-08-16 with categories.
The effect of wake passing on the showerhead film cooling performance of a turbine blade has been investigated experimentally. The experiments were performed in an annular turbine cascade with an upstream rotating row of cylindrical rods. Nickel thin-film gauges were used to determine local film effectiveness and Nusselt number values for various injectants, blowing ratios, and Strouhal numbers. Results indicated a reduction in film effectiveness with increasing Strouhal number, as well as the expected increase in film effectiveness with blowing ratio. An equation was developed to correlate the span-average film effectiveness data. The primary effect of wake unsteadiness was found to be correlated by a streamwise-constant decrement of 0.094.St. Steady computations were found to be in excellent agreement with experimental Nusselt numbers, but to overpredict experimental film effectiveness values. This is likely due to the inability to match actual hole exit velocity profiles and the absence of a credible turbulence model for film cooling. Heidmann, James D. and Lucci, Barbara L. and Reshotko, Eli Glenn Research Center NASA-TM-107425, NAS 1.15:107425, E-10671 RTOP 505-62-10...
Jet Impingement Cooling In Rotating Coolant Passages Of Gas Turbine Blades
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Author : Kumar Vyaghreswara Akella
language : en
Publisher:
Release Date : 1998
Jet Impingement Cooling In Rotating Coolant Passages Of Gas Turbine Blades written by Kumar Vyaghreswara Akella and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1998 with categories.
Measurements Of Heat Transfer Flow And Pressures In A Simulated Turbine Blade Internal Cooling Passage
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Author : Louis M. Russell
language : en
Publisher:
Release Date : 1997
Measurements Of Heat Transfer Flow And Pressures In A Simulated Turbine Blade Internal Cooling Passage written by Louis M. Russell and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1997 with Flow visualization categories.
An experimental study was made to obtain quantitative information on heat transfer, flow, and pressure distribution in a branched duct test section that had several significant features of an internal cooling passage of a turbine blade. The objective of this study was to generate a set of experimental data that could be used for validation of computer codes that would be used to model internal cooling. Surface heat transfer coefficients and entrance flow conditions were measured at nominal entrance Reynolds numbers of 45 000, 335 000, and 726 000. Heat transfer data were obtained by using a steady-state technique in which an Inconel heater sheet is attached to the surface and coated with liquid crystals. Visual and quantitative flow-field data from particle image velocimetry measurements for a plane at midchannel height for a Reynolds number of 45 000 were also obtained. The flow was seeded with polystyrene particles and illuminated by a laser light sheet. Pressure distribution measurements were made both on the surface with discrete holes and in the flow field with a total pressure probe. The flow-field measurements yielded flow-field velocities at selected locations. A relatively new method, pressure sensitive paint, was also used to measure surface pressure distribution. The pressure paint data obtained at Reynolds numbers of 335 000 and 726 000 compared well with the more standard method of measuring pressures by using discrete holes.