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Download Heat Transfer And Flow On The Blade Tip Of A Gas Turbine Equipped With A Mean Camberline Strip Final Report Nasa Cr 2001 210764 Aug full books in PDF, epub, and Kindle. Read online Heat Transfer And Flow On The Blade Tip Of A Gas Turbine Equipped With A Mean Camberline Strip Final Report Nasa Cr 2001 210764 Aug ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Author :
Publisher :
ISBN 13 :
Total Pages : 14 pages
Book Rating : 4.:/5 (317 download)
Download or read book Heat Transfer and Flow on the Blade Tip of a Gas Turbine Equipped with a Mean-Camberline Strip written by and published by . This book was released on 2001 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781721262274
Total Pages : 26 pages
Book Rating : 4.2/5 (622 download)
Download or read book Heat Transfer and Flow on the Blade Tip of a Gas Turbine Equipped with a Mean-Camberline Strip written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-16 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental and computational studies have been performed to investigate the detailed distribution of convective heat transfer coefficients on the first-stage blade tip surface for a geometry typical of large power generation turbines (greater than 100 MW) In a previous work the numerical heat transfer results for a sharp edge blade tip and a radiused blade tip were presented. More recently several other tip treatments have been considered for which the tip heat transfer has been measured and documented. This paper is concerned with the numerical prediction of the tip surface heat transfer for radiused blade tip equipped with mean-camberline strip (or "squealer" as it is often called). The heat transfer results are compared with the experimental results and discussed. The effectiveness of the mean-camberline strip in reducing the tip leakage and the tip heat transfer as compared to a radiused edge tip and sharp edge tip was studied. The calculations show that the sharp edge tip works best (among the cases considered) in reducing the tip leakage flow and the tip heat transfer. Ameri, A.A. Glenn Research Center NASA/CR-2001-210764, NAS 1.26:210764, E-12693, Rept-2001-GT-0156
Author :
Publisher :
ISBN 13 :
Total Pages : 836 pages
Book Rating : 4.:/5 (89 download)
Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on 2002 with total page 836 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781721183678
Total Pages : 26 pages
Book Rating : 4.1/5 (836 download)
Download or read book Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine. Part 2; Simulation Results written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: A combined experimental and computational study has been performed to investigate the detailed distribution of convective heat transfer coefficients on the first stage blade tip surface for a geometry typical of large power generation turbines (>1OOMW). This paper is concerned with the numerical prediction of the tip surface heat transfer. Good comparison with the experimental measured distribution was achieved through accurate modeling of the most important features of the blade passage and heating arrangement as well as the details of experimental rig likely to affect the tip heat transfer. A sharp edge and a radiused edge tip were considered. The results using the radiused edge tip agreed better with the experimental data. This improved agreement was attributed to the absence of edge separation on the tip of the radiused edge blade. Ameri, A. A. and Bunker, R. S. Glenn Research Center NASA/CR-1999-209151/PT2, NAS 1.26:209151/PT2, E-11656/PT2, ASME 99-GT-283/PT2
Author : National Aeronautics and Space Adm Nasa
Publisher : Independently Published
ISBN 13 : 9781724003515
Total Pages : 30 pages
Book Rating : 4.0/5 (35 download)
Download or read book Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine. Part 1; Experimental Results written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-25 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: A combined computational and experimental study has been performed to investigate the detailed distribution of convective heat transfer coefficients on the first stage blade tip surface for a geometry typical of large power generation turbines(>100MW). This paper is concerned with the design and execution of the experimental portion of the study. A stationary blade cascade experiment has been run consisting of three airfoils, the center airfoil having a variable tip gap clearance. The airfoil models the aerodynamic tip section of a high pressure turbine blade with inlet Mach number of 0.30, exit Mach number of 0.75, pressure ratio of 1.45, exit Reynolds number based on axial chord of 2.57 x 10(exp 6), and total turning of about 110 degrees. A hue detection based liquid crystal method is used to obtain the detailed heat transfer coefficient distribution on the blade tip surface for flat, smooth tip surfaces with both sharp and rounded edges. The cascade inlet turbulence intensity level took on values of either 5% or 9%. The cascade also models the casing recess in the shroud surface ahead of the blade. Experimental results are shown for the pressure distribution measurements on the airfoil near the tip gap, on the blade tip surface, and on the opposite shroud surface. Tip surface heat transfer coefficient distributions are shown for sharp-edge and rounded-edge tip geometries at each of the inlet turbulence intensity levels. Bunker, Ronald S. and Bailey, Jeremy C. and Ameri, Ali A. Glenn Research Center NASA/CR-1999-209152, NAS 1.26:209152, E-11660, ASME-99-GT-169
Author :
Publisher :
ISBN 13 :
Total Pages : 492 pages
Book Rating : 4.:/5 (317 download)
Download or read book Turbine Engine Hot Section Technology, 1987 written by and published by . This book was released on 1987 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781721189052
Total Pages : 26 pages
Book Rating : 4.1/5 (89 download)
Download or read book A Numerical Analysis of Heat Transfer and Effectiveness on Film Cooled Turbine Blade Tip Models written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational study has been performed to predict the distribution of convective heat transfer coefficient on a simulated blade tip with cooling holes. The purpose of the examination was to assess the ability of a three-dimensional Reynolds-averaged Navier-Stokes solver to predict the rate of tip heat transfer and the distribution of cooling effectiveness. To this end, the simulation of tip clearance flow with blowing of Kim and Metzger was used. The agreement of the computed effectiveness with the data was quite good. The agreement with the heat transfer coefficient was not as good but improved away from the cooling holes. Numerical flow visualization showed that the uniformity of wetting of the surface by the film cooling jet is helped by the reverse flow due to edge separation of the main flow. Ameri, A. A. and Rigby, D. L. Glenn Research Center NASA/CR-1999-209165, NAS 1.26:209165, E-11756
Author : Charles F. Zalabak
Publisher :
ISBN 13 :
Total Pages : 32 pages
Book Rating : 4.3/5 (91 download)
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.
Author : Je-Chin Han
Publisher : CRC Press
ISBN 13 : 1439855684
Total Pages : 892 pages
Book Rating : 4.4/5 (398 download)
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.
Author : Francis S. Stepka
Publisher :
ISBN 13 :
Total Pages : 26 pages
Book Rating : 4.:/5 (31 download)
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:
Author : Bengt Sundén
Publisher : Witpress
ISBN 13 :
Total Pages : 544 pages
Book Rating : 4.3/5 (91 download)
Download or read book Heat Transfer in Gas Turbines written by Bengt Sundén and published by Witpress. This book was released on 2001 with total page 544 pages. Available in PDF, EPUB and Kindle. Book excerpt: This title presents and reflects current active research on various heat transfer topics and related phenomena in gas turbine systems. It begins with a general introduction to gas turbine heat transfer, before moving on to specific areas.
Author : Louis M. Russell
Publisher :
ISBN 13 :
Total Pages : 30 pages
Book Rating : 4.:/5 (317 download)
Download or read book Measurements of Heat Transfer, Flow, and Pressures in a Simulated Turbine Blade Internal Cooling Passage written by Louis M. Russell and published by . This book was released on 1997 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Author : Arthur N. Curren
Publisher :
ISBN 13 :
Total Pages : 42 pages
Book Rating : 4.3/5 (91 download)
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.
Author : Richard J. Goldstein
Publisher :
ISBN 13 : 9781573313292
Total Pages : 522 pages
Book Rating : 4.3/5 (132 download)
Download or read book Heat Transfer in Gas Turbine Systems written by Richard J. Goldstein and published by . This book was released on 2001-01-01 with total page 522 pages. Available in PDF, EPUB and Kindle. Book excerpt: Papers collected here were presented at an August 2000 conference entitled Turbine-2000: International Symposium on Heat Transfer in Gas Turbine Systems, sponsored by the International Center for Heat and Mass Transfer and held in Turkey. Keynote papers examine models of secondary flows, boundary la
Author : E. R. Norster
Publisher : Elsevier
ISBN 13 : 1483151794
Total Pages : 417 pages
Book Rating : 4.4/5 (831 download)
Download or read book Combustion and Heat Transfer in Gas Turbine Systems written by E. R. Norster and published by Elsevier. This book was released on 2013-10-22 with total page 417 pages. Available in PDF, EPUB and Kindle. Book excerpt: Combustion and Heat Transfer in Gas Turbine Systems is a compilation of papers from the Proceedings of an International Propulsion Symposium held at the College of Aeronautics, Cranfield in April 1969. This compilation deals with research done by academic and scientific institutions and of industrial organizations, with some research papers covering atomization, fuels, and high-temperature materials. One paper describes the combustion system of the Concorde engine used in commercial flights, temperature of metal parts, and some design modifications to increase the mechanical life of the combustion system. Another paper discusses the evolution of the RB 162 combustion system that is used in the vertical takeoff and landing aircrafts. The RB 162 has many design features of the earlier single reversal chamber and differs in only one or two points. The book then notes the necessity of a plenum chamber burning to further development of supersonic engines and flight. One paper also proposes an alternative theory to the traditional ignition theory of altitude relighting such as those developed by Lewis and von Elbe. Another paper reposts on some observations made of the atomizing characteristics of air-blast atomizers and proposes simple changes to improve the performance of the atomizer by prefilming and allowing air to both sides of the fuel. This compilation will prove very helpful for aeronautical engineers, aviation designers, physicists, students of engineering, and readers who are interested in the design and development of jet engines and supersonic aircrafts.
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781721526673
Total Pages : 28 pages
Book Rating : 4.5/5 (266 download)
Download or read book Heat Transfer in a Complex Trailing Edge Passage for a High Pressure Turbine Blade. Part 2 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-19 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: A combined experimental and numerical study to investigate the heat transfer distribution in a complex blade trailing edge passage was conducted. The geometry consists of a two pass serpentine passage with taper toward the trailing edge, as well as from hub to tip. The upflow channel has an average aspect ratio of roughly 14:1, while the exit passage aspect ratio is about 5:1. The upflow channel is split in an interrupted way and is smooth on the trailing edge side of the split and turbulated on the other side. A turning vane is placed near the tip of the upflow channel. Reynolds numbers in the range of 31,000 to 61,000, based on inlet conditions, were simulated numerically. The simulation was performed using the Glenn-HT code, a full three-dimensional Navier-Stokes solver using the Wilcox k-omega turbulence model. A structured multi-block grid is used with approximately 4.5 million cells and average y+ values on the order of unity. Pressure and heat transfer distributions are presented with comparison to the experimental data. While there are some regions with discrepancies, in general the agreement is very good for both pressure and heat transfer. Rigby, David L. and Bunker, Ronald S. Glenn Research Center NASA/CR-2002-211701, NAS 1.26:211701, ASME-2002-GT-30213, E-13430
Author : American Society of Mechanical Engineers. Winter Annual Meeting
Publisher :
ISBN 13 :
Total Pages : 98 pages
Book Rating : 4.3/5 (91 download)
Download or read book Heat Transfer in Gas Turbine Engines written by American Society of Mechanical Engineers. Winter Annual Meeting and published by . This book was released on 1987 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt:
