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Author : B. R. Haller
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (535 download)
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:
Author : Martin F. Urban
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (137 download)
Download or read book Experimental and numerical investigations of film-cooling effects on the aerodynamic performance of transonic turbine blades, ASME 98-GT-546 written by Martin F. Urban and published by . This book was released on 1998 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Stockholm, Sweden, Jun 2-Jun 5, 1998.
Author : B. R. Haller
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (137 download)
Download or read book Aerodynamic Loss Penalty Produced by Film Cooling Transonic Turbine Blades written by B. R. Haller and published by . This book was released on 1983 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 123 pages
Book Rating : 4.:/5 (227 download)
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.
Author : Ernst Rudolf Georg Eckert
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.3/5 (126 download)
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.
Author : Kyle Leon Lee
Publisher :
ISBN 13 :
Total Pages : 190 pages
Book Rating : 4.:/5 (397 download)
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:
Author :
Publisher :
ISBN 13 :
Total Pages : 109 pages
Book Rating : 4.:/5 (227 download)
Download or read book Studies on Transonic Turbines with Film-Cooled Blades written by and published by . This book was released on 1976 with total page 109 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the third 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. The MIT cascade blowdown facility now fully operational was used in evaluating the heat transfer performance of the four blade profiles designed in the first year of the program. The results show that the level of turbulence is an important parameter in determining heat transfer in transonic cascades. It also shows that the heat transfer to the trailing edge of the blades is very high being about 75% of the heat transfer to the leading edge. A comparison of the Nusselt number calculated from heat transfer measurements with the Nusselt number obtained by a prediction method using the pressure distribution shows good correspondence. The variation of average Stanton number over a range of Mach numbers shows that the reference blade has the most superior heat transfer performance. Preliminary data has been obtained on the off-design performance of the blades and full scale tests are underway. Comparative studies show that about 21% less heat needs to be taken out by internal cooling if one stage of a transonic turbine is used to replace two moderately loaded subsonic stages which produce the same output, have the same inlet stagnation conditions, have the same mass flow and the same tip speed. This demonstrates one of the potential advantages of transonic turbines.
Author : Eric Ralph McFarland
Publisher :
ISBN 13 :
Total Pages : 234 pages
Book Rating : 4.:/5 (36 download)
Download or read book An Investigation of the Aerodynamic Performance of Film Cooled Turbine Blades written by Eric Ralph McFarland and published by . This book was released on 1976 with total page 234 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Cengiz Camci
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (139 download)
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.
Author : Reinaldo Araújo Gomes
Publisher :
ISBN 13 : 9783868536003
Total Pages : 174 pages
Book Rating : 4.5/5 (36 download)
Download or read book On Aerothermal Effects of Film Cooling on Turbine Blades with Flow Separation written by Reinaldo Araújo Gomes and published by . This book was released on 2010 with total page 174 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : James D. Heidmann
Publisher :
ISBN 13 :
Total Pages : 14 pages
Book Rating : 4.:/5 (317 download)
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.
Author :
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (946 download)
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.
Author :
Publisher :
ISBN 13 :
Total Pages : 63 pages
Book Rating : 4.:/5 (318 download)
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.
Author :
Publisher :
ISBN 13 :
Total Pages : 484 pages
Book Rating : 4.0/5 ( download)
Download or read book ASME Technical Papers written by and published by . This book was released on 2001 with total page 484 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781720482284
Total Pages : 64 pages
Book Rating : 4.4/5 (822 download)
Download or read book Effect of Film-Hole Shape on Turbine Blade Film Cooling Performance written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-30 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: The detailed heat transfer coefficient and film cooling effectiveness distributions as well as tile detailed coolant jet temperature profiles on the suction side of a gas turbine blade A,ere measured using a transient liquid crystal image method and a traversing cold wire and a traversing thermocouple probe, respectively. The blade has only one row of film holes near the gill hole portion on the suction side of the blade. The hole geometries studied include standard cylindrical holes and holes with diffuser shaped exit portion (i.e. fanshaped holes and laidback fanshaped holes). Tests were performed on a five-blade linear cascade in a low-speed wind tunnel. The mainstream Reynolds number based on cascade exit velocity was 5.3 x 10(exp 5). Upstream unsteady wakes were simulated using a spoke-wheel type wake generator. The wake Strouhal number was kept at 0 or 0.1. Coolant blowing ratio was varied from 0.4 to 1.2. Results show that both expanded holes have significantly improved thermal protection over the surface downstream of the ejection location, particularly at high blowing ratios. However, the expanded hole injections induce earlier boundary layer transition to turbulence and enhance heat transfer coefficients at the latter part of the blade suction surface. In general, the unsteady wake tends to reduce film cooling effectiveness.Han, J. C. and Teng, S.Glenn Research CenterHEAT TRANSFER COEFFICIENTS; COOLANTS; TEMPERATURE PROFILES; SUCTION; TURBINE BLADES; HEAT MEASUREMENT; FILM COOLING; BOUNDARY LAYER TRANSITION; CASCADE WIND TUNNELS; CYLINDRICAL BODIES; EJECTION; GAS TURBINES; HOLE DISTRIBUTION (MECHANICS); LIQUID CRYSTALS; LOW SPEED; THERMAL PROTECTION; THERMOCOUPLES; WIND TUNNELS
Author :
Publisher :
ISBN 13 :
Total Pages : 1064 pages
Book Rating : 4.X/5 (4 download)
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1973 with total page 1064 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : E. R. G. Eckert
Publisher :
ISBN 13 :
Total Pages : 65 pages
Book Rating : 4.:/5 (227 download)
Download or read book Curvature Effects on the Heat Transfer Performance of Three-Dimensional Film Cooling of Gas Turbine Blades written by E. R. G. Eckert and published by . This book was released on 1982 with total page 65 pages. Available in PDF, EPUB and Kindle. Book excerpt: Film cooling is used extensively for the blades of high-performance, high-temperature gas turbines, especially for aircraft turbines. In this method, a film of coolant is injected into the boundary layer covering the skin of the blades and creating a cool layer which separates the blade surface from the hot gas stream and, in this way, reduces the blade temperature. For best performance the coolant should be injected through a slot or a strip of porous material. This, however, is not possible for turbine blades because of strength considerations, and the coolant is injected through one or several rows of holes. For aircraft gas turbines, air is used as a coolant. The present investigation, therefore, is concerned with the cooling performance of film cooling when cooling air is injected into the boundary through one or two rows of holes. A standard configuration of the coolant holes is used because it has been used in previous investigations and because configurations in actual turbine blades are close to it. The cooling holes are arranged at a distance apart equal to three times the hole diameter. For injection through two rows of holes, the two rows are staggered and the centers of the holes are on the corners of equilateral triangles. The channels which end at the blade skin in the cooling holes are inclined by an angle of 35 deg against the skin surface in the downstream direction.
