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Author : Jin Taek Chung
Publisher :
ISBN 13 :
Total Pages : 566 pages
Book Rating : 4.:/5 (319 download)
Download or read book Flow and Heat Transfer Experiments in the Turbine Airfoil/endwall Region written by Jin Taek Chung and published by . This book was released on 1992 with total page 566 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 46 pages
Book Rating : 4.:/5 (227 download)
Download or read book Studies of Gas Turbine Heat Transfer: Airfoil Surfaces and End-Wall Cooling Effects written by and published by . This book was released on 1991 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report documents accomplishments made toward understanding the fluid flow and heat transfer processes in gas turbines at the University of Minnesota over the past two years. The research is divided into three subtopics: studies of film cooling, airfoil surface heat transfer and endwall flow and heat transfer. Film cooling experiments show the effects of interaction among jets on curved surfaces and calculations show that parabolic techniques give accurate effectiveness predictions in regions away from injection holes. The surface heat transfer program showed that tripping the flow or roughening the wall has a clear effect near airfoil transition and separation points and that recovery from concave curvature is surprisingly slow. Endwall studies show flow visualization on the cascade endwall and the value of a fence on the endwall for rerouting the horseshoe vortex away from the suction wall.
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 : 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 : Stephen M. Molter
Publisher :
ISBN 13 :
Total Pages : 322 pages
Book Rating : 4.:/5 (144 download)
Download or read book Heat Transfer in the Blade Row and Tip Region of a Modern Transonic High Pressure Turbine with and Without Forward Cavity Purge Flow written by Stephen M. Molter and published by . This book was released on 2006 with total page 322 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: A full scale rotating turbine rig operated at design corrected conditions has been used to study the heat transfer mechanisms affecting the flowpath surfaces within a modem single stage high-pressure (HP) turbine. The experimental rig was first run completely un-cooled and is currently being re-constructed to accommodate HP vane airfoil and endwall cooling and inner-stage cavity purge flow injection. Heat flux and pressure data were measured for both a flat and recessed, or squealer, HP blade tip and the stationary shroud above. The measurements indicate that the recessed tip, used in the majority of modem turbines to minimize blade damage from rubs, increases the blade heat load overall, and creates several hot spots on the floor of the recess for an un-cooled airfoil. The tip data also showed there were significant unsteady variations in the heat load at the vane passing frequency. Steady state CFD calculations were completed for both flat and squealer tip configurations to examine if the analysis could capture the details that were measured. The CFD, while not capable of estimating the unsteady heat load component and generally over predicting the overall heat flux by 10-25%, did capture the measured heat flux trends in the recessed tip. The steady state CFD prediction did show good agreement with the time-accurate data along the stationary shroud. These results show that steady-state CFD analysis can be useful in predicting the complex flow field and heat load distribution in turbine blade tips to help guide future blade designs. Pre-test CFD predictions were also performed for the upcoming series of experiments that include replacing the un-cooled vane row with a fully cooled HP vane row and the introduction of HP blade forward cavity purge flow, while leaving the HP blade un-cooled. The focus of the steady state predictions for the HP blade row was two fold; to assist in guiding the placement of new heat flux and pressure instrumentation and to study the cold flow migration through the HP blade row. Adiabatic wall temperature and Nusselt number predictions along the blade surface showed large radial, or spanwise, gradients, mostly along the suction side of the blade. Surface visualization on the suction side of the blade revealed two bands of cooler regions located at the upper and lower spans, with the middle spans being hotter, comparable to the pressure side. The lower band of cool flow is a result of the forward cavity purge flow, which mostly migrates to the suction side of the blade passage. By the trailing edge of the blade the purge flow has migrated upwards to an extent of approximately 20% of the blade span surface. The upper band of cool flow is a result of the cooling flow from the HP vane outer endwall. Blade tip secondary flows and the tip leakage vortex act to entrain this cool flow into the tip gap, resulting in its migration to the suction side of the blade. Due to a downward migration of the tip vortex along the suction side through the blade row, this cool band along the airfoil surface affects the upper 20% of the blade span. Results from the pre-test CFD predictions were also analyzed along the blade platform and rim seal surfaces. Migration of the forward cavity purge flow towards the suction side increases the Nusselt number along the rim seal and platform in these areas. Adiabatic wall temperatures on the platform surface were reasonably constant and lower than those on the blade surface, an effect of a portion of the purge flow being entrained into the platform boundary layer. Pressure asymmetries along the rim seal created circumferential variations in the local purge mass flow rates, with the leading edge of blade being the location of highest pressure and thus lower purge injection. Results also indicate the possibility of hot gas ingestion into the upper region of the rim seal at the leading edge. When data is available from the updated turbine rig, the comparisons will help to further validate this code as a useful design tool.
Author :
Publisher :
ISBN 13 :
Total Pages : 20 pages
Book Rating : 4.:/5 (317 download)
Download or read book Endwall Heat Transfer Measurements in a Transonic Turbine Cascade written by and published by . This book was released on 1996 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Turbine blade endwall heat transfer measurements are given for a range of Reynolds and Mach numbers. Data were obtained for Reynolds numbers based on inlet conditions of 0.5 and 1.0 x 10(exp 6), for isentropic exit Mach numbers of 1.0 and 1.3, and for freestream turbulence intensities of 0.25% and 7.0%. Tests were conducted in a linear cascade at the NASA Lewis Transonic Turbine Blade Cascade Facility. The test article was a turbine rotor with 136 deg of turning and an axial chord of 12.7 cm. The large scale allowed for very detailed measurements of both flow field and surface phenomena. The intent of the work is to provide benchmark quality data for CFD code and model verification. The flow field in the cascade is highly three-dimensional as a result of thick boundary layers at the test section inlet. Endwall heat transfer data were obtained using a steady-state liquid crystal technique.
Author :
Publisher :
ISBN 13 :
Total Pages : 76 pages
Book Rating : 4.:/5 (317 download)
Download or read book Fundamental Heat Transfer Research for Gas Turbine Engines written by and published by . This book was released on 1980 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Robert J. Boyle
Publisher :
ISBN 13 :
Total Pages : 20 pages
Book Rating : 4.:/5 (317 download)
Download or read book Three-dimensional Navier-Stokes Heat Transfer Predictions for Turbine Blade Rows written by Robert J. Boyle and published by . This book was released on 1992 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Download or read book Film Cooling and End Wall Heat Transfer in Small Turbine Blade Passages written by and published by . This book was released on 1978 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two topics have been studied related to the cooling of the end wall of a turbine passage. The first concerns the development of a method for measuring the adiabatic wall effectiveness and heat transfer coefficient of a film cooling system for protecting a surface from high heating derived from a hot compressible flow. The second concerns the measurement of the heat transfer rate distribution to a turbine cascade end wall in order to choose an appropriate film cooling system. These are related to providing the background to the final phase of the study in which the effectiveness of a film cooling system to cool a turbine end wall will be made combined with the measurement of the aerodynamic losses incurred by such a system. (Author).
Author :
Publisher :
ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.:/5 (317 download)
Download or read book Heat Transfer Measurements and Predictions on a Power Generation Gas Turbine Blade written by and published by . This book was released on 2000 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: Detailed heat transfer measurements and predictions are given for a power generation turbine rotor with 129 deg of nominal turning and an axial chord of 137 mm. Data were obtained for a set of four exit Reynolds numbers comprised of the design point of 628,000, -20%, +20%, and +40%. Three ideal exit pressure ratios were examined including the design point of 1.378, -10%, and +10%. Inlet incidence angles of 0 deg and +/-2 deg were also examined. Measurements were made in a linear cascade with highly three-dimensional blade passage flows that resulted from the high flow turning and thick inlet boundary layers. Inlet turbulence was generated with a blown square bar grid. The purpose of the work is the extension of three-dimensional predictive modeling capability for airfoil external heat transfer to engine specific conditions including blade shape, Reynolds numbers, and Mach numbers. Data were obtained by a steady-state technique using a thin-foil heater wrapped around a low thermal conductivity blade. Surface temperatures were measured using calibrated liquid crystals. The results show the effects of strong secondary vortical flows, laminar-to-turbulent transition, and also show good detail in the stagnation region.
Author : Steven Wayne Burd
Publisher :
ISBN 13 :
Total Pages : 604 pages
Book Rating : 4.:/5 (319 download)
Download or read book Secondary Flow and Heat Transfer Control in Gas Turbine Inlet Nozzle Guide Vanes written by Steven Wayne Burd and published by . This book was released on 1998 with total page 604 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Chunill Hah
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book Numerical Study of Three-dimensional Flow and Heat Transfer Near the Endwall of a Turbine Blade Row written by Chunill Hah and published by . This book was released on 1989 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 500 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 1995 with total page 500 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Budugur Lakshminarayana
Publisher : John Wiley & Sons
ISBN 13 : 9780471855460
Total Pages : 846 pages
Book Rating : 4.8/5 (554 download)
Download or read book Fluid Dynamics and Heat Transfer of Turbomachinery written by Budugur Lakshminarayana and published by John Wiley & Sons. This book was released on 1995-12-15 with total page 846 pages. Available in PDF, EPUB and Kindle. Book excerpt: Over the past three decades, information in the aerospace and mechanical engineering fields in general and turbomachinery in particular has grown at an exponential rate. Fluid Dynamics and Heat Transfer of Turbomachinery is the first book, in one complete volume, to bring together the modern approaches and advances in the field, providing the most up-to-date, unified treatment available on basic principles, physical aspects of the aerothermal field, analysis, performance, theory, and computation of turbomachinery flow and heat transfer. Presenting a unified approach to turbomachinery fluid dynamics and aerothermodynamics, the book concentrates on the fluid dynamic aspects of flows and thermodynamic considerations rather than on those related to materials, structure, or mechanical aspects. It covers the latest material and all types of turbomachinery used in modern-day aircraft, automotive, marine, spacecraft, power, and industrial applications; and there is an entire chapter devoted to modern approaches on computation of turbomachinery flow. An additional chapter on turbine cooling and heat transfer is unique for a turbomachinery book. The author has undertaken a systematic approach, through more than three hundred illustrations, in developing the knowledge base. He uses analysis and data correlation in his discussion of most recent developments in this area, drawn from over nine hundred references and from research projects carried out by various organizations in the United States and abroad. This book is extremely useful for anyone involved in the analysis, design, and testing of turbomachinery. For students, it can be used as a two-semester course of senior undergraduate or graduate study: the first semester dealing with the basic principles and analysis of turbomachinery, the second exploring three-dimensional viscid flows, computation, and heat transfer. Many sections are quite general and applicable to other areas in fluid dynamics and heat transfer. The book can also be used as a self-study guide to those who want to acquire this knowledge. The ordered, meticulous, and unified approach of Fluid Dynamics and Heat Transfer of Turbomachinery should make the specialization of turbomachinery in aerospace and mechanical engineering much more accessible to students and professionals alike, in universities, industry, and government. Turbomachinery theory, performance, and analysis made accessible with a new, unified approach For the first time in nearly three decades, here is a completely up-to-date and unified approach to turbomachinery fluid dynamics and aerothermodynamics. Combining the latest advances, methods, and approaches in the field, Fluid Dynamics and Heat Transfer of Turbomachinery features: The most comprehensive and complete coverage of the fluid dynamics and aerothermodynamics of turbomachinery to date A spotlight on the fluid dynamic aspects of flows and the thermodynamic considerations for turbomachinery (rather than the structural or material aspects) A detailed, step-by-step presentation of the analytical and computational models involved, which allows the reader to easily construct a flowchart from which to operate Critical reviews of all the existing analytical and numerical models, highlighting the advantages and drawbacks of each Comprehensive coverage of turbine cooling and heat transfer, a unique feature for a book on turbomachinery An appendix of basic computation techniques, numerous tables, and listings of common terminology, abbreviations, and nomenclature Broad in scope, yet concise, and drawing on the author's teaching experience and research projects for government and industry, Fluid Dynamics and Heat Transfer of Turbomachinery explains and simplifies an increasingly complex field. It is an invaluable resource for undergraduate and graduate students in aerospace and mechanical engineering specializing in turbomachinery, for research and design engineers, and for all professionals who are—or wish to be—at the cutting edge of this technology.
Author : Amy Mensch
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (915 download)
Download or read book Using Conjugate Heat Transfer to Assess the Cooling Performance on a Turbine Endwall written by Amy Mensch and published by . This book was released on 2015 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Advancements in cooling for applications such as gas turbines components require improved understanding of the complex heat transfer mechanisms and the interactions between those mechanisms. Turbine designers often rely on multiple thermal protection techniques, including internal cooling, external film cooling, and thermal barrier coatings to efficiently cool components and limit the use of coolant. Traditionally, the effectiveness of such cooling technologies is quantified by considering the convection and conduction heat transfer mechanisms separately. The current research considers the combined effects of both internal and external cooling in a single experiment or simulation using a conjugate heat transfer approach.The geometry used for this study is a turbine blade endwall, which is influenced by three-dimensional vortices generated by the passage flow. The experiments and computational simulations include impingement and film cooling as well as conduction through the endwall. Appropriate geometric and flow parameters are properly scaled to ensure engine relevant dimensionless temperatures are obtained. The overall effectiveness, which is a scaled wall temperature, is compared for multiple cases, including different cooling configurations and the implementation of endwall contouring, thermal barrier coatings, and contaminant deposition. The measurements showed that impingement cooling was a larger contributor to the combined overall effectiveness compared to film cooling. The area-averaged contoured endwall overall effectiveness was similar to the flat endwall despite local differences in film cooling effectiveness and impingement effectiveness. The thermal barrier coating significantly increased overall effectiveness by reducing the external heat transfer. Contaminant deposition increased surface roughness, which increased external heat transfer to the endwall.Computational simulations of conjugate heat transfer and time-resolved flowfield measurements helped to understand the complex mechanisms acting together to generate the overall cooling effectiveness. The predicted endwall temperature fields show the three-dimensional temperature gradients present in conjugate heat transfer. The flat and contoured endwall flowfield measurements show that film cooling jets and the passage vortex interact to generate the secondary flowfield impacting endwall heat transfer. Several recommendations for mitigating increased heat transfer and optimizing the cooling performance for gas turbine endwalls are given.
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Publisher :
ISBN 13 :
Total Pages : 438 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 438 pages. Available in PDF, EPUB and Kindle. Book excerpt:
