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Injector element characterization methodologyCharacterization of liquid rocket engine injector elements is an important part of the development process for rocket engine combustion devices. Modern nonintrusive instrumentation for flow velocity and spray droplet size measurement, and automated, computer-controlled test facilities allow rapid, low-cost evaluation of injector element performance and behavior. Application of these methods in rocket engine development, paralleling their use in gas turbine engine development, will reduce rocket engine development cost and risk. The Alternate Turbopump (ATP) Hot Gas Systems (HGS) preburner injector elements were characterized using such methods, and the methodology and some of the results obtained will be shown.
Document ID
19900019318
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cox, George B., Jr.
(Pratt and Whitney Aircraft West Palm Beach, FL, United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1988
Publication Information
Publication: NASA, Marshall Space Flight Center, Advanced Earth-to-Orbit Propulsion Technology 1988, Volume 1
Subject Category
Spacecraft Propulsion And Power
Accession Number
90N28634
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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