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Studies On Transonic Turbine With Film Cooled Blades
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Book Synopsis Studies on Transonic Turbines with Film Cooled Blades by : H. O. Demuren
Download or read book Studies on Transonic Turbines with Film Cooled Blades written by H. O. Demuren and published by . This book was released on 1974 with total page 139 pages. Available in PDF, EPUB and Kindle. Book excerpt: The goal of these studies has been to gather the necessary heat transfer data and develop the design procedure for high performance, film cooled, highly loaded transonic turbine stages. In the pursuit of this goal, three key tasks were accomplished: the measurement of heat transfer rates and film effectiveness in the low supersonic range, a study of the flow at the trailing edge of transonic turbine blades and the heat transfer at this critical part of the blade, and a determination of an optimum profile for a turbine stage providing high work per unit of cooled blade surface.
Book Synopsis Studies on Transonic Turbine with Film-Cooled Blades by :
Download or read book Studies on Transonic Turbine with Film-Cooled Blades written by and published by . This book was released on 1977 with total page 123 pages. Available in PDF, EPUB and Kindle. Book excerpt: During the fourth year of the contract, further advances were made towards the goal of gathering the heat transfer and aerodynamics flow data necessary for a good understanding of the performance of film-cooled, highly- loaded, transonic turbine blading. Surface Mach number and heat transfer rate distributions were determined for a reference transonic airfoil over a range of exit Mach numbers, for inlet incidence angle variation of + or - 15 deg. An evaluation and comparison of all cascade data collected so far was then conducted. Progress was also made in the investigation of the effects of unsteadiness on transonic airfoil aerodynamics and heat transfer.
Book Synopsis Transonic Turbine Blade Film Cooling with Shaped Holes by : Fariborz Forghan
Download or read book Transonic Turbine Blade Film Cooling with Shaped Holes written by Fariborz Forghan and published by . This book was released on 1996 with total page 746 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Film Cooling Visualization and Heat Transfer on Transonic Turbine Blades by :
Download or read book Film Cooling Visualization and Heat Transfer on Transonic Turbine Blades written by and published by . This book was released on 2001 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study is an investigation of the film cooling effectiveness and heat transfer coefficient of a two-dimensional turbine rotor blade in a linear transonic cascade. Experiments were performed in Virginia Tech's Cascade Wind Tunnel with an exit Mach number of 1.2 and an exit Reynolds number of 5 x 10 (exp 6) to simulate real engine flow conditions. The freestream and coolant flows were maintained at a total temperature ratio of 2 +0.4 and a total pressure ration of 1.04. The freestream turbulence was approximately 1%. There are six rows of staggered, discrete cooling holes on and near the leading edge of the blade in a showerhead configuration. Cooled air was used as the coolant. Experiments were performed with and without film cooling on the surface of the blade. The heat transfer coefficient was found to increase with the addition of film cooling an average of 14% overall and to a maximum of 26% at the first gauge location. The average film cooling effectiveness that suggest either a transition from a laminar to a turbulent film regime or the regime or the existence of three-dimensionality in the flow-field over the gauges.
Book Synopsis An Experimental Study of the Effect of Wake Passing on Turbine Blade Film Cooling by : James D. Heidmann
Download or read book An Experimental Study of the Effect of Wake Passing on Turbine Blade Film Cooling written by James D. Heidmann and published by . This book was released on 1997 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Orlando, FL, Jun 2 - Jun 5, 1997.
Book Synopsis The Effects of Film Cooling Upon the Aerodynamic Performance of Transonic Turbine Blades by : B. R. Haller
Download or read book The Effects of Film Cooling Upon the Aerodynamic Performance of Transonic Turbine Blades written by B. R. Haller and published by . This book was released on 1981 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aero-thermal Characteristics and Film Cooling of Transonic Turbine Blade Tips by : Andrew Saul
Download or read book Aero-thermal Characteristics and Film Cooling of Transonic Turbine Blade Tips written by Andrew Saul and published by . This book was released on 2019 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Leading Edge Film-Cooling and Surface Roughness on the Downstream Film-Cooling Along a Transonic Turbine Blade for Low and High Free-Stream Turbulence by :
Download or read book Effects of Leading Edge Film-Cooling and Surface Roughness on the Downstream Film-Cooling Along a Transonic Turbine Blade for Low and High Free-Stream Turbulence written by and published by . This book was released on 2008 with total page 63 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report is the culmination of a two year effort to demonstrate the capability for performing near wall high resolution Time Resolved Particle Image Velocimetry (TRDPIV) measurements in a transonic turbine. Performing TRDPIV in high speed wall bounded flows with high resolution/magnification often posses significant difficulties. For this reason, two preliminary studies where conducted in order to further understand the challenges that would be present in this type of environment. Hardware and algorithm advancements and developments ultimately enabled performing TRDPIV in the transonic cascade facility. However, high pressure, high speed and the turbine blade complex geometries (high curvature and acceleration) significantly inhibit our ability to deliver homogeneous distribution of flow tracers, especially in the near wall region resulting in low quality measurements and regions with randomly missing data. In addition to our experimental results this effort delivers a novel advanced data reconstruction methodology based on proper orthogonal decomposition that was developed to overcome the aforementioned limitation. The following report documents in detail the methods and results generated throughout this effort.
Book Synopsis Effects of Shocks on the Unsteady Heat Transfer in a Film-Cooled Transonic Turbine Cascade by :
Download or read book Effects of Shocks on the Unsteady Heat Transfer in a Film-Cooled Transonic Turbine Cascade written by and published by . This book was released on 2001 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental program was performed to study the effects of high strength shocks on the film cooling heat transfer in a transonic turbine blade. Shocks stronger than seen in actual engines were generated by a shock tube and directed to pass into the cascade upstream of a linear set of blades. The results indicate that the increased strength of the shocks do not disrupt the boundary layer on the blade. Therefore, the heat transfer is still predictable by the methods determined for lower strength shocks, as reported in the attached two papers (presented in Munich during this research program). As a transition to work on high free-stream turbulence effects, initial results for a blown grid were obtained in low speed flow. The corresponding report is attached, but has not yet been published.
Book Synopsis Effects of Wake and Shock Passing on the Heat Transfer to a Film Cooled Transonic Turbine Blade by : M. J. Rigby
Download or read book Effects of Wake and Shock Passing on the Heat Transfer to a Film Cooled Transonic Turbine Blade written by M. J. Rigby and published by . This book was released on 1990 with total page 252 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analytical Study of Cooled Turbine Blades Considering Combined Steady-state and Transient Conditions by : A. Kaufman
Download or read book Analytical Study of Cooled Turbine Blades Considering Combined Steady-state and Transient Conditions written by A. Kaufman and published by . This book was released on 1970 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Film Cooled Small Turbine Blade Research by : Bryan E. Richards
Download or read book Film Cooled Small Turbine Blade Research written by Bryan E. Richards and published by . This book was released on 1976 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Book Synopsis Experimental Study of Gas Turbine Blade Film Cooling and Heat Transfer by : Diganta P. Narzary
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.
Book Synopsis Effect of Incidence on Wall Heating Rates and Aerodynamics on a Film Cooled Transonic Turbine Blade by : Cengiz Camci
Download or read book Effect of Incidence on Wall Heating Rates and Aerodynamics on a Film Cooled Transonic Turbine Blade written by Cengiz Camci and published by . This book was released on 1990 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study investigates the influence of incidence on convective heat transfer to highly curved surfaces of a film-cooled turbine rotor blade. A computational study of free-stream inviscid aerodynamics without cooling at various incidences is followed by well-documented measured heat transfer data sets. The heat transfer experiments are discussed for cases with and without film cooling, performed under realistic gas turbine flow conditions in the short-duration heat transfer facility of the von Karman Institute for Fluid Dynamics. The precise location of the stagnation point and the iso-Mach number contours in the passage for each incidence (−10, 0, 10, +15 deg) are presented for a nominal exit Mach number of 0.94. The free-stream mass flow rate was kept constant for each experiment at different incidence levels. Three rows of compound angled discrete cooling holes are located near the leading edge in a showerhead configuration. Two rows of staggered discrete cooling holes are located on the suction side and a single row of cooling holes is located on the pressure side. The short-duration measurements of quantitative wall heat fluxes on nearly isothermal blade surfaces both in the presence and absence of coolant ejection are presented. The study indicated that the change of the position of the stagnation point strongly altered the aerodynamic behavior and convective heat transfer to the blade in approximately the first 30 percent of both the pressure side and the suction side in the presence and absence of film cooling. The immediate vicinity of the stagnation point was not significantly affected by changing incidence without cooling. Transitional behavior both on the suction surface and on the pressure surface was significantly influenced by the changes in approaching flow direction. Flow separation associated with incidence variations was also observed. Extremely low levels of the convective heat transfer coefficients were experienced near the regions where small separation bubbles are located.
Book Synopsis Transonic Film Cooling from Shaped Holes on the Suction Surface of a Turbine Blade by : Tetsuji Furukawa
Download or read book Transonic Film Cooling from Shaped Holes on the Suction Surface of a Turbine Blade written by Tetsuji Furukawa and published by . This book was released on 2001 with total page 250 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Losses and Discharge Coefficients for a Transonic Turbine Blade with Film Cooling by : Kyle Leon Lee
Download or read book Aerodynamic Losses and Discharge Coefficients for a Transonic Turbine Blade with Film Cooling written by Kyle Leon Lee and published by . This book was released on 1998 with total page 190 pages. Available in PDF, EPUB and Kindle. Book excerpt:
