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Summary. Professor Reitz's research interests include internal combustion engines, chemical kinetics and sprays. A major research focus of his work has been the development and application of advanced computer models for the design of fuel injected engines, including diesel and spark-ignited engines.
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Theoretical and experimental analysis of droplet diameter, temperature, and evaporation rate evolution in cryogenic sprays. ... R.D. Ingebo, Characteristics of vaporizing cryogenic sprays for rocket combustion modeling, NASA Technical Memorandum 106615.4004966696, 1994.
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flow and atomization characteristics of cryogenic fluid from Download flow and atomization characteristics of cryogenic fluid from or read online here in PDF or EPUB. Please click button to get flow and atomization characteristics of cryogenic fluid from book now. All books are in clear copy here, and all files are secure so don't worry about it.
The present work demonstrates the application of the GRR technique to the cryogenic sprays.  ... “ Chraracteristics of Vaporizing Cryogenic Sprays for Rocket Combustion Modeling,” Proceedings of the 1994 ASME International Joint Power Generation Conference, ... ROBERT INGEBO;
Ingebo, Robert D. and United States. National Aeronautics and Space Administration. Characteristics of vaporizing cryogenic sprays for rocket combustion modeling [microform] / Robert D. Ingebo National Aeronautics and Space Administration ; National Technical Information Service, distributor [Washington, DC] : [Springfield, Va 1994
The reusable solid rocket motors were fabricated in segments and pinned together incorporating O-ring seals. Similarly, nozzles consisted of multiple components joined and sealed at six joint locations using O-rings. A layer of rubber insulation, referred to as “joint fill” compound, kept the 3,038°C (5,500°F) combustion
Liquid oxygen—abbreviated LOx, LOX or Lox in the aerospace, submarine and gas industries—is the liquid form of elemental oxygen.It was used as the oxidizer in the first liquid-fueled rocket invented in 1926 by Robert H. Goddard an application which has continued to the present.
Characteristics of Vaporizing Cryogenic Sprays for Rocket Combustion Modeling . By Robert D. Ingebo. Abstract. Experimental measurements of the volume-median drop diameter, Dv.5e, of vaporizing cryogenic sprays were obtained with a drop size measuring instrument developed at NASA Lewis Research Center.
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Radial characteristics of radiation of high-frequency electrodeless lamps Article in Optics and Spectroscopy 101(3):371-374 · September 2006 with 11 Reads How we measure 'reads'
02.07.2019 · Buy Characteristics of vaporizing cryogenic sprays for rocket combustion modeling (SuDoc NAS 1.15:106615) by Robert D. Ingebo (ISBN: ) from Amazon's Book Store. Everyday low prices and free delivery on eligible orders.
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Delivered values of C* range from about 1,333 m/s for monopropellant hydrazine up to about 2,360 m/s for cryogenic oxygen/hydrogen. Rocket Engines. A typical rocket engine consists of the nozzle, the combustion chamber, and the injector, as shown in Figure 1.4. The combustion chamber is where the burning of propellants takes place at high pressure.
Stanford Libraries' official online search tool for books, media, journals, databases, government documents and more. Characteristics of vaporizing cryogenic sprays for rocket combustion modeling [microform] in SearchWorks catalog
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An optical sensor for multi-species impurity monitoring in hydrogen fuel Article in Sensors and Actuators B Chemical s 171–172:416–422 · August 2012 with 108 Reads How we measure 'reads'
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Get this from a library! Characteristics of vaporizing cryogenic sprays for rocket combustion modeling. [Robert D Ingebo; United States. National Aeronautics and Space Administration.]
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R-134a spray dynamics and impingement cooling in the non-boiling regime. ... R.D. Ingebo. Atomization of ... R.D. Ingebo, Characteristics of vaporizing cryogenic sprays for rocket combustion modeling, NASA Technical Memorandum 106615. 4004966696, 1994. Google Scholar
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NASA Technical Memorandum 1066 15. Characteristics of Vaporizing Cryogenic Sprays for Rocket Combustion Modeling. Robert D. Ingebo Lewis Research Center Cleveland, Ohio. Prepared for the ASME International Joint Power Generation Conference sponsored by the American Society of Mechanical Engineers Phoenix, Arizona, October 2-6, 1994. National Aeronautics and
Ingebo, Robert D. and Lewis Research Center. Characterization of simulated small-droplet fuel sprays [microform] / Robert D. Ingebo National Aeronautics and Space Administration, Lewis Research Center [Cleveland, Ohio 1986. Australian/Harvard Citation. Ingebo, Robert D. & Lewis Research Center.
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Combustion of fuel, droplets and sprays – Combustion systems – Pulverised fuel furnaces – fixed, Entrained and Fluidised Bed Systems. Unit – 5 : Environmental considerations – Air pollution – Effects on Environment, Human Health etc. Principal pollutants – Legislative Measures …
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Christopher D. Radke, J. Patrick McManamen, Alan L. Kastengren, Andrew B. Swantek, Terrence R. Meyer. (2017) Synchrotron X-Ray Interrogation of Turbulent Gas–Liquid Mixing in Cryogenic Rocket Sprays. AIAA Journal 55:12, 4306-4313
Spray formation. Spray atomization can be formed by several methods. The most common method is through a spray nozzle which typically has a fluid passage that is acted upon by different mechanical forces that atomize the liquid. The first atomization nozzle was invented by Thomas A. DeVilbiss of Toledo, Ohio in the late 1800s His invention was bulb atomizer that used pressure to impinge upon a ...