NDLI: Photographic combustion characterization of lox/hydrocarbon type propellants (Document No: 19810006605)

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Photographic combustion characterization of lox/hydrocarbon type propellants (Document No: 19810006605)

Content Provider	NASA Technical Reports Server (NTRS)
Author	Judd, D. C.
Copyright Year	1980
Description	One hundred twenty-seven tests were conducted over a chamber pressure range of 125-1500 psia, a fuel temperature range of -245 F to 158 F, and a fuel velocity range of 48-707 ft/sec to demonstrate the advantages and limitations of using high speed photography to identify potential combustion anomalies such as pops, fuel freezing, reactive stream separation and carbon formations. Combustion evaluation criteria were developed to guide selection of the fuels, injector elements, and operating conditions for testing. Separate criteria were developed for fuel and injector element selection and evaluation. The photographic test results indicated conclusively that injector element type and design directly influence carbon formation. Unlike spray fan, impingement elements reduce carbon formation because they induce a relatively rapid near zone fuel vaporization rate. Coherent jet impingement elements, on the other hand, exhibit increased carbon formation.
File Size	1969630
Page Count	55
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19810006605
Archival Resource Key	ark:/13960/t7tn21k5x
Language	English
Publisher Date	1980-08-15
Access Restriction	Open
Subject Keyword	Propellants And Fuels Color Photography Methane Liquid Ammonia Injectors Carbon Propellant Combustion Combustion Physics Rp-1 Rocket Propellants Liquid Oxygen Hydrocarbon Fuels Oxygen-hydrocarbon Rocket Engines High Speed Cameras Cryogenic Rocket Propellants Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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