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Measurements And Computational Analysis Of Heat Transfer And Flow In A Simulated Turbine Blade Internal Cooling Passage
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Book Synopsis Measurements and Computational Analysis of Heat Transfer and Flow in a Simulated Turbine Blade Internal Cooling Passage by : Louis M. Russell
Download or read book Measurements and Computational Analysis of Heat Transfer and Flow in a Simulated Turbine Blade Internal Cooling Passage written by Louis M. Russell and published by . This book was released on 1993 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Heat Transfer, Flow, and Pressures in a Simulated Turbine Blade Internal Cooling Passage by : Louis M. Russell
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 :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722362997 Total Pages :26 pages Book Rating :4.3/5 (629 download)
Book Synopsis Measurements of Heat Transfer, Flow, and Pressures in a Simulated Turbine Blade Internal Cooling Passage by : National Aeronautics and Space Administration (NASA)
Download or read book Measurements of Heat Transfer, Flow, and Pressures in a Simulated Turbine Blade Internal Cooling Passage written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-20 with total page 26 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. Russell, Louis M. and Thurman, Douglas R. and Poinsatte, Philip E. and Hippensteele, Steven A. Glenn Research Center RTOP 505-62-52; DA Proj. 1L1-61102-AH-45...
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1994 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Complementary Velocity and Heat Transfer Measurements in a Rotating Turbine Cooling Passage by : Jeffrey Peter Bons
Download or read book Complementary Velocity and Heat Transfer Measurements in a Rotating Turbine Cooling Passage written by Jeffrey Peter Bons and published by . This book was released on 1997-08-01 with total page 200 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted on the internal flowfield of a simulated turbine blade cooling passage. The passage is of a square cross- section and was manufactured from quartz for optical accessibility. Velocity measurements were taken using Particle Image Velocimetry for both heated and non-heated cases. Thin film resistive heaters on the four passage walls allow heat to be added to the coolant flow without obstructing laser access. Under the same conditions, an infrared detector with associated optics collected wall temperature data for use in calculating local Nusselt number. The test section was operated with radial outward flow and at values of Reynolds number, Rotation number, and density ratio typical of applications. Velocity data for the non- heated case document the evolution of the Coriolis-induced double vortex. The vortex has the effect of increasing the leading side boundary layer thickness while decreasing the trailing side boundary layer thickness. Also, the streamwise component of the Coriolis acceleration creates a thinned side wall boundary layer. These data reveal an unsteady, turbulent flowfield in the cooling passage. Velocity data for the heated case show a strongly distorted streamwise profile indicative of a buoyancy effect on the leading side. The Coriolis vortex is the mechanism for the accumulation of stagnant flow on the leading side of the passage. Heat transfer data show a maximum factor of two difference in the Nusselt number from trailing side to leading side. An estimate of this heat transfer disparity based on the measured boundary layer edge velocity yields approximately the same factor of two. A momentum integral model was developed for data interpretation which accounts for Coriolis and buoyancy effects. Calculated streamwise profiles and secondary flows match the experimental data weg(8i>
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722891886 Total Pages :190 pages Book Rating :4.8/5 (918 download)
Book Synopsis A Combined Experimental/Computational Study of Flow in Turbine Blade Cooling Passage by : National Aeronautics and Space Administration (NASA)
Download or read book A Combined Experimental/Computational Study of Flow in Turbine Blade Cooling Passage written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 190 pages. Available in PDF, EPUB and Kindle. Book excerpt: Laser velocimetry was utilized to map the velocity field in a serpentine turbine blade cooling passage at Reynolds and Rotation numbers of up to 25.000 and 0.48. These results were used to assess the combined influence of passage curvature and Coriolis force on the secondary velocity field generated. A Navier-Stokes code (NASTAR) was validated against incompressible test data and then used to simulate the effect of buoyancy. The measurements show a net convection from the low pressure surface to high pressure surface. The interaction of the secondary flows induced by the turns and rotation produces swirl at the turns, which persisted beyond 2 hydraulic diameters downstream of the turns. The incompressible flow field predictions agree well with the measured velocities. With radially outward flow, the buoyancy force causes a further increase in velocity on the high pressure surface and a reduction on the low pressure surface. The results were analyzed in relation to the heat transfer measurements of Wagner et al. (1991). Predicted heat transfer is enhanced on the high pressure surfaces and in turns. The incompressible flow simulation underpredicts heat transfer in these locations. Improvements observed in compressible flow simulation indicate that the buoyancy force may be important. Tse, D. G. N. and Kreskovsky, J. P. and Shamroth, S. J. and Mcgrath, D. B. Unspecified Center BUOYANCY; CHANNEL FLOW; CONVECTIVE HEAT TRANSFER; COOLING; FLOW DISTRIBUTION; FLOW VELOCITY; TURBINE BLADES; COMPRESSIBLE FLOW; CORIOLIS EFFECT; INCOMPRESSIBLE FLOW; LASER DOPPLER VELOCIMETERS; NAVIER-STOKES EQUATION; REYNOLDS NUMBER; SECONDARY FLOW; VELOCITY DISTRIBUTION...
Book Synopsis Advanced Fluid Mechanics and Heat Transfer for Engineers and Scientists by : Meinhard T. Schobeiri
Download or read book Advanced Fluid Mechanics and Heat Transfer for Engineers and Scientists written by Meinhard T. Schobeiri and published by Springer Nature. This book was released on 2022-01-17 with total page 602 pages. Available in PDF, EPUB and Kindle. Book excerpt: The current book, Advanced Fluid Mechanics and Heat Transfer is based on author's four decades of industrial and academic research in the area of thermofluid sciences including fluid mechanics, aero-thermodynamics, heat transfer and their applications to engineering systems. Fluid mechanics and heat transfer are inextricably intertwined and both are two integral parts of one physical discipline. No problem from fluid mechanics that requires the calculation of the temperature can be solved using the system of Navier-Stokes and continuity equations only. Conversely, no heat transfer problem can be solved using the energy equation only without using the Navier-Stokes and continuity equations. The fact that there is no book treating this physical discipline as a unified subject in a single book that considers the need of the engineering and physics community, motivated the author to write this book. It is primarily aimed at students of engineering, physics and those practicing professionals who perform aero-thermo-heat transfer design tasks in the industry and would like to deepen their knowledge in this area. The contents of this new book covers the material required in Fluid Mechanics and Heat Transfer Graduate Core Courses in the US universities. It also covers the major parts of the Ph.D-level elective courses Advanced Fluid Mechanics and Heat Transfer that the author has been teaching at Texas A&M University for the past three decades.
Book Synopsis Effect of Blade-tip Crossover Passages on Natural-convection Water-cooling of Gas-turbine Blades by : Charles F. Zalabak
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.
Book Synopsis Effect of Diameter of Closed-end Coolant Passages on Natural-convection Water Cooling of Gas-turbine Blades by : Arthur N. Curren
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.
Book Synopsis A Combined Experiment/computational Study of Flow in Turbine Blade Cooling Passage by :
Download or read book A Combined Experiment/computational Study of Flow in Turbine Blade Cooling Passage written by and published by . This book was released on 1994 with total page 194 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 652 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Book Synopsis Heat Transfer in Gas Turbines by : Bengt Sundén
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.
Book Synopsis Effect of Chord Size on Weight and Cooling Characteristics of Air-cooled Turbine Blades by : Jack B. Esgar
Download or read book Effect of Chord Size on Weight and Cooling Characteristics of Air-cooled Turbine Blades written by Jack B. Esgar and published by . This book was released on 1957 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis has been made to determine the effect of chord size on the weight and cooling characteristics of shell-supported, air-cooled gas-turbine blades. In uncooled turbines with solid blades, the general practice has been to design turbines with high aspect ratio (small blade chord) to achieve substantial turbine weight reduction. With air-cooled blades, this study shows that turbine blade weight is affected to a much smaller degree by the size of the blade chord.
Book Synopsis Procedure for Calculating Turbine Blade Temperatures and Comparison of Calculated with Observed Values for Two Stationary Air-cooled Blades by : W. Byron Brown
Download or read book Procedure for Calculating Turbine Blade Temperatures and Comparison of Calculated with Observed Values for Two Stationary Air-cooled Blades written by W. Byron Brown and published by . This book was released on 1952 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Local and average blade temperatures were calculated for two stationary air-cooled turbine blades with 10 tubes and 13 fins forming the internal heat-transfer surfaces. These temperatures were calculated using previously published NACA temperature-distribution equations and the most recent theories for determining heat-transfer coefficients, including for the first time the allowance for effects of variable wall temperature on gas-to-blade heat-transfer coefficients at the leading and trailing sections of turbine blades. Comparison of calculated and experimental blade temperatures, for gas temperatures of 300° and 1000°F, resulted in good agreement.
Book Synopsis Monthly Catalogue, United States Public Documents by :
Download or read book Monthly Catalogue, United States Public Documents written by and published by . This book was released on 1994 with total page 1064 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis International Aerospace Abstracts by :
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1999 with total page 1020 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Computational and Experimental Investigation of Vortex Cooling of a Gas Turbine Blade Using 3-D Stereo-Particle Image Velocimetry and Liquid Crystals by : Daisy Galeana
Download or read book Computational and Experimental Investigation of Vortex Cooling of a Gas Turbine Blade Using 3-D Stereo-Particle Image Velocimetry and Liquid Crystals written by Daisy Galeana and published by . This book was released on 2022 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The limiting factor for most gas turbines has been the turbine inlet temperature. Furthermore, higher pressure ratios and turbine inlet temperatures improve the efficiencies on the gas turbine. A big focus has been on new schemes of internal cooling designs of turbine blades, using pressurized air from the engine compressor, and break-through in blade metallurgy, in order to achieve higher turbine inlet temperatures. Significant research has been ongoing for decades to design an internal cooling system for the first stage of the turbine blade consequently higher turbine inlet temperatures can be achieved. The challenging engineering intricacies related to improving the efficiency of a gas turbine engine come with the need to maximize the efficiency of the internal cooling of the turbine blade to withstand the high turbine inlet temperature. Understanding the fluid mechanics and heat transfer of internal blade cooling is therefore of paramount importance. This dissertation presents the impact of swirl flow cooling on the heat transfer of a gas turbine blade cooling passage to understand the mechanics of internal blade cooling. The focus is the continuous cooling flow that must be maintained via nonstop injection of tangential flow, whereby swirl flow is generated. The experimental investigation is presented first with three-dimensional (3-D) Stereo-Particle Image Velocimetry (Stereo-PIV) and second Thermochromic Liquid Crystal (TLC) of a swirl flow that models a gas turbine blade internal cooling configuration. The study is intended to provide an evaluation of the developments of swirl flow cooling methodology utilizing 3-D Stereo-PIV and liquid crystals. The objective of the experimental models is to determine the critical swirl number that has the potential to deliver the maximum axial velocity results with the highest heat transfer at three different Reynolds numbers, 7,000, 14,000, and 21,000. The swirl flow cooling methodology comprises of cooling air channeling through the blade's internal passages lowering the metal temperature, therefore the experimental cylindrical chamber is made of acrylic allowing detailed measurements and includes seven discrete tangential air inlets designed to create the swirl flow. Additionally, a 3D domain fluent setup employing a steady-state pressure-based solver with a standard k-epsilon turbulence model was applied. The energy equations were activated to handle the temperature effect; the gravitational acceleration is accounted for. Important variations of the swirl number are present near the air inlets and decrease with downstream distance as predicted since the second half of the chamber has no more inlets. The axial velocity reaches the maximum downstream in the second half of the chamber. The circumferential velocity decreases downstream distance and reaches the highest towards the center of the chamber. As part of the results relatively low heat transfer rates were observed near the upstream end of the cylindrical chamber, resulting from a low momentum swirl flow as well as crossflow effects. The TLC heat transfer results exemplify how the Nusselt Number (Nu) measured favorably at the midstream of the chamber and values decline downstream. Furthermore, experimental results when compared to the Computational Fluid Dynamics analysis are compatible with each other.
