Download or read book Performance and Screech Characteristics of a Series of 2500 pound thrust per element Injectors for a Liquid oxygen Hydrogen Rocket Engine written by and published by . This book was released on 1966 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Thrust Per Element on Combustion Stability Characteristics of Hydrogen oxygen Rocket Engines written by Reino J. Salmi and published by . This book was released on 1968 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book M 1 Engine Subscale Injector Tests written by Herbert E. Scott and published by . This book was released on 1967 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA Technical Note written by and published by . This book was released on 1968 with total page 830 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Liquid Propellant Rocket Combustion Instability written by David T. Harrje and published by . This book was released on 1972 with total page 668 pages. Available in PDF, EPUB and Kindle. Book excerpt: The solution of problems of combustion instability for more effective communication between the various workers in this field is considered. The extent of combustion instability problems in liquid propellant rocket engines and recommendations for their solution are discussed. The most significant developments, both theoretical and experimental, are presented, with emphasis on fundamental principles and relationships between alternative approaches.

Download or read book Liquid Propellant Rocket Combustion Instability written by and published by . This book was released on 1972 with total page 668 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Interim Summary of Liquid Rocket Acoustic mode instability Studies at a Nominal Thrust of 20 000 Pounds written by E. William Conrad and published by . This book was released on 1968 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: Liquid rocket acoustic instability for hydrogen-oxygen and earth storable propellant combinations.

Download or read book M 1 Injector Development written by and published by . This book was released on 1968 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Liquid Rocket Engine Injectors written by and published by . This book was released on 1976 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Liquid Rocket Engine Combustion Instability written by Vigor Young and published by AIAA. This book was released on 1995 with total page 606 pages. Available in PDF, EPUB and Kindle. Book excerpt: Annotation Since the invention of the V-2 rocket during World War II, combustion instabilities have been recognized as one of the most difficult problems in the development of liquid propellant rocket engines. This book is the first published in the United States on the subject since NASA's Liquid Rocket Combustion Instability (NASA SP-194) in 1972. In this book, experts cover four major subject areas: engine phenomenology and case studies, fundamental mechanisms of combustion instability, combustion instability analysis, and engine and component testing. Especially noteworthy is the inclusion of technical information from Russia and China--a first.

Download or read book Investigation of Injectors for a Low chamber pressure Hydrogen fluorine Rocket Engine written by Harold G. Price and published by . This book was released on 1962 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Some Injector Element Detail Effects on Screech in Hydrogen oxygen Rockets written by and published by . This book was released on 1974 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA SP written by and published by . This book was released on 1969 with total page 884 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Throttling Characteristics of a Hydrogen Oxygen Regeneratively Cooled Pump fed Rocket Engine written by and published by . This book was released on 1964 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Injection Element Radial Distribution and Chamber Geometry on Acoustic mode Instability in a Hydrogen Oxygen Rocket written by John P. Wanhainen and published by . This book was released on 1969 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Injector radial distribution and thrust chamber geometry effect on acoustic mode instability in hydrogen oxygen engines.

Download or read book Stabilizing Effects of Several Injector Face Baffle Configurations on Screech in a 20 000 pound thrust Hydrogen oxygen Rocket written by Ned P. Hannum and published by . This book was released on 1968 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Oxygen hydrogen Injector Thrust Per Element Size Maximization written by Howard V. Main and published by . This book was released on 1965 with total page 57 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of the tests and evaluations performed on highly simplified, large thrust per element (LTE) injectors utilizing cryogenic propellants are presented. Phase II of Project Scorpio was conducted to determine the maximum thrust per injector element which could be utilized and still achieve high performance. High combustion efficiency, combustion stability, and heat transfer characteristics were the major items of concern. Twenty-nine test firings were conducted. The three injector patterns investigated were the: (1) single-element concentric pentad, (2) four-element concentric pentad, and (3) four-element concentric triplet. Two thrust chamber configurations, one uncooled and the other film cooled, were utilized. The basic characteristic length of 45 inches was varied to 75 inches by installing a section between the injector and thrust chamber. After a series of tests on each injector, modifications were made to the first two and the third one was fired reversed, i.e., fuel injected through oxidizer manifold and oxidizer injected through fuel manifold, to determine the effect on performance. Also, the injector film coolant holes and chamber film coolant passages were sealed to facilitate injector performance evaluation. Chamber stagnation pressure and mixture ratio were varied from 556 to 753 psia and 3.6/ 1 to 5.7/1, respectively. Combustion efficiency above 90% characteristic velocity was achieved with the four-element concentric pentad injector over a range of mixture ratios and chamber pressures.