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Two Dimensional Cold Air Cascade Study Of A Film Cooled Turbine Stator Blade 5 Comparison Of Experimental And Analytical Aerodynamic Results For Blade With 12 Rows Of 0038 Centimeter 0015 Inch Diameter Coolant Holes Having Streamwise Ejection Angl
Download Two Dimensional Cold Air Cascade Study Of A Film Cooled Turbine Stator Blade 5 Comparison Of Experimental And Analytical Aerodynamic Results For Blade With 12 Rows Of 0038 Centimeter 0015 Inch Diameter Coolant Holes Having Streamwise Ejection Angl full books in PDF, epub, and Kindle. Read online Two Dimensional Cold Air Cascade Study Of A Film Cooled Turbine Stator Blade 5 Comparison Of Experimental And Analytical Aerodynamic Results For Blade With 12 Rows Of 0038 Centimeter 0015 Inch Diameter Coolant Holes Having Streamwise Ejection Angl ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781723300318 Total Pages :24 pages Book Rating :4.3/5 (3 download)
Book Synopsis Two-Dimensional Cold-Air Cascade Study of a Film-Cooled Turbine Stator Blade. 5 by : National Aeronautics and Space Administration (NASA)
Download or read book Two-Dimensional Cold-Air Cascade Study of a Film-Cooled Turbine Stator Blade. 5 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-20 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Published experimental aerodynamic efficiency results were compared with results predicted from two published analytical methods. This is the second of two such comparisons. One of the analytical methods was used as published; the other was modified for certain cases of coolant discharge from the blade suction surface. The results show that for 23 cases of single row and multirow discharge covering coolant fractions from 0 to about 9 percent, the difference between the experimental and predicted results was no greater than about 1 percent in any case and less than 1/2 percent in most cases. Prust, H. W., Jr. Glenn Research Center NASA-TP-1204, E-9342 RTOP 505-04
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781724754981 Total Pages :32 pages Book Rating :4.7/5 (549 download)
Book Synopsis Two-Dimensional Cold-Air Cascade Study of a Film-Cooled Turbine Stator Blade. 4 by : National Aeronautics and Space Administration (NASA)
Download or read book Two-Dimensional Cold-Air Cascade Study of a Film-Cooled Turbine Stator Blade. 4 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-06 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Previously published experimental aerodynamic efficiency results for a film cooled turbine stator blade are compared with analytical results computed from two published analytical methods. One method was used as published; the other was modified for certain cases of coolant discharge from the blade suction surface. For coolant ejection from blade surface regions where the surface static pressures are higher than the blade exit pressure, both methods predict the experimental results quite well. However, for ejection from regions with surface static pressures lower than the blade exit pressure, both methods predict too small a change in efficiency. The modified method gives the better prediction. Prust, H. W., Jr. Glenn Research Center NASA-TP-1151, E-9187 RTOP 505-04
Book Synopsis Reinventing the Propeller by : Jeremy R. Kinney
Download or read book Reinventing the Propeller written by Jeremy R. Kinney and published by Cambridge University Press. This book was released on 2017-03-24 with total page 391 pages. Available in PDF, EPUB and Kindle. Book excerpt: An international community of specialists reinvented the propeller during the Aeronautical Revolution, a vibrant period of innovation in North America and Europe from World War I to the end of World War II. They experienced both success and failure as they created competing designs that enabled increasingly sophisticated and 'modern' commercial and military aircraft to climb quicker and cruise faster using less power. Reinventing the Propeller nimbly moves from the minds of these inventors to their drawing boards, workshops, research and development facilities, and factories, and then shows us how their work performed in the air, both commercially and militarily. Reinventing the Propeller documents this story of a forgotten technology to reveal new perspectives on engineering, research and development, design, and the multi-layered social, cultural, financial, commercial, industrial, and military infrastructure of aviation.
Book Synopsis Introduction to Aeronautics by : Steven A. Brandt
Download or read book Introduction to Aeronautics written by Steven A. Brandt and published by AIAA. This book was released on 2004 with total page 544 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :Kevin Michaels Publisher :American Institute of Aeronautics and Astronautics Incorporated ISBN 13 :9781624104022 Total Pages :0 pages Book Rating :4.1/5 (4 download)
Download or read book Aerodynamic written by Kevin Michaels and published by American Institute of Aeronautics and Astronautics Incorporated. This book was released on 2018 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Traces the transformation of the commercial aircraft business from 1990 to the present. This $300bn industry is not only the pinnacle of high technology and advanced manufacturing; it is also amongst the largest export industries for many advanced economies and a key enabler of military aerospace and national defense.
Book Synopsis Hypersonic Aerothermodynamics by : John J. Bertin
Download or read book Hypersonic Aerothermodynamics written by John J. Bertin and published by AIAA. This book was released on 1994 with total page 644 pages. Available in PDF, EPUB and Kindle. Book excerpt: A modern treatment of hypersonic aerothermodynamics for students, engineers, scientists, and program managers involved in the study and application of hypersonic flight. It assumes an understanding of the basic principles of fluid mechanics, thermodynamics, compressible flow, and heat transfer. Ten chapters address: general characterization of hypersonic flows; basic equations of motion; defining the aerothermodynamic environment; experimental measurements of hypersonic flows; stagnation-region flowfield; the pressure distribution; the boundary layer and convective heat transfer; aerodynamic forces and moments; viscous interactions; and aerothermodynamics and design considerations. Includes sample exercises and homework problems. Annotation copyright by Book News, Inc., Portland, OR
Book Synopsis Sustainable Aviation by : T. Hikmet Karakoc
Download or read book Sustainable Aviation written by T. Hikmet Karakoc and published by Springer. This book was released on 2019-04-23 with total page 158 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book provides readers with a basic understanding of the concepts and methodologies of sustainable aviation.The book is divided into three sections : basic principles the airport side, and the aircraft side. In-depth chapters discuss the key elements of sustainable aviation and provide complete coverage of essential topics including airport, energy, and noise management along with novel technologies, standards and a review of the current literature on green airports, sustainable aircraft design, biodiversity management, and alternative fuels. Engineers, researchers and students will find the fundamental approach useful and will benefit from the many engineering examples and solutions provided.
Book Synopsis Aerospace Design by : A. M. Springer
Download or read book Aerospace Design written by A. M. Springer and published by . This book was released on 2003 with total page 204 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book explores the physical aspects of aviation and space flight through an appreciation of design evolution, powers of scale, materials, tools of the trade and imagery that captures not only moments in history, but also tire realization of theories and ideas. Each chapter, written by a specialist in aerospace history or aerospace technology, engagingly describes all aspect of the evolution of flight, from ground-testing designs and components to the aircraft and spacecraft themselves. The authors raise numerous fascinating questions: Why (to the vehicles look the way they (lo? How do these designs relate to other forms in our society? What will aircraft and spacecraft look like in the future? The answers to every conceivable question about aerospace design are provided in this landmark publication, which is stunningly illustrated throughout with e broad range of images from NASA's unsurpassable collection. This book is essential reading for anyone interested in aircraft, spacecraft or the broader issues of design.
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)
Book Synopsis Effect of Film-Hole Shape on Turbine Blade Film Cooling Performance by : National Aeronautics and Space Administration (NASA)
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 :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721933846 Total Pages :228 pages Book Rating :4.9/5 (338 download)
Book Synopsis Unsteady High Turbulence Effects on Turbine Blade Film Cooling Heat Transfer Performance Using a Transient Liquid Crystal Technique by : National Aeronautics and Space Administration (NASA)
Download or read book Unsteady High Turbulence Effects on Turbine Blade Film Cooling Heat Transfer Performance Using a Transient Liquid Crystal Technique written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-27 with total page 228 pages. Available in PDF, EPUB and Kindle. Book excerpt: Unsteady wake effect, with and without trailing edge ejection, on detailed heat transfer coefficient and film cooling effectiveness distributions is presented for a downstream film-cooled gas turbine blade. Tests were performed on a five-blade linear cascade at an exit Reynolds number of 5.3 x 10(exp 5). Upstream unsteady wakes were simulated using a spoke-wheel type wake generator. Coolant blowing ratio was varied from 0.4 to 1.2; air and CO2 were used as coolants to simulate different density ratios. Surface heat transfer and film effectiveness distributions were obtained using a transient liquid crystal technique; coolant temperature profiles were determined with a cold wire technique. Results show that Nusselt numbers for a film cooled blade are much higher compared to a blade without film injection. Unsteady wake slightly enhances Nusselt numbers but significantly reduces film effectiveness versus no wake cases. Nusselt numbers increase only slic,htly but film cooling, effectiveness increases significantly with increasing, blowing ratio. Higher density coolant (CO2) provides higher effectiveness at higher blowing ratios (M = 1.2) whereas lower density coolant (Air) provides higher 0 effectiveness at lower blowing ratios (M = 0.8). Trailing edge ejection generally has more effect on film effectiveness than on the heat transfer, typically reducing film effectiveness and enhancing heat transfer. Similar data is also presented for a film cooled cylindrical leading edge model. Han, J. C. and Ekkad, S. V. and Du, H. and Teng, S. Glenn Research Center NAG3-1656; RTOP 714-01-4A
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781725097346 Total Pages :28 pages Book Rating :4.0/5 (973 download)
Book Synopsis An Experimental Study of the Effect of Wake Passing on Turbine Blade Film Cooling by : National Aeronautics and Space Administration (NASA)
Download or read book An Experimental Study of the Effect of Wake Passing on Turbine Blade Film Cooling written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-16 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effect of wake passing on the showerhead film cooling performance of a turbine blade has been investigated experimentally. The experiments were performed in an annular turbine cascade with an upstream rotating row of cylindrical rods. Nickel thin-film gauges were used to determine local film effectiveness and Nusselt number values for various injectants, blowing ratios, and Strouhal numbers. Results indicated a reduction in film effectiveness with increasing Strouhal number, as well as the expected increase in film effectiveness with blowing ratio. An equation was developed to correlate the span-average film effectiveness data. The primary effect of wake unsteadiness was found to be correlated by a streamwise-constant decrement of 0.094.St. Steady computations were found to be in excellent agreement with experimental Nusselt numbers, but to overpredict experimental film effectiveness values. This is likely due to the inability to match actual hole exit velocity profiles and the absence of a credible turbulence model for film cooling. Heidmann, James D. and Lucci, Barbara L. and Reshotko, Eli Glenn Research Center NASA-TM-107425, NAS 1.15:107425, E-10671 RTOP 505-62-10...
