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Effects of compression and expansion ramp fuel injector configuration on scramjet combustion and heat transferA scramjet combustor with four wall-ramp injectors containing Mach-1.7 fuel jets in the base of the ramps was investigated experimentally. During the test program, two swept ramp injector designs were evaluated. One swept-ramp model had 10-deg compression-ramps and the other had 10-deg expansion cavities between flush wall ramps. The scramjet combustor model was instrumented with pressure taps and heat-flux gages. The pressure measurements indicated that both injector configurations were effective in promoting mixing and combustion. Autoignition occurred for the compression-ramp injectors, and the fuel began to burn immediately downstream of the injectors. In tests of the expansion ramps, a pilot was required to ignite the fuel, and the fuel did not burn for a distance of at least two gaps downstream of the injectors. Once initiated, combustion was rapid in this configuration. Heat transfer measurements showed that the heat flux differed greatly both across the width of the combustor and along the length of the combustor.
Document ID
19930037117
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Stouffer, Scott D.
(Virginia Polytechnic Inst. and State Univ. Blacksburg, United States)
Baker, N. R.
(Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Capriotti, D. P.
(Analytical Services and Materials, Inc. Hampton, VA, United States)
Northam, G. B.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 93-0609
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 11, 1993
End Date: January 14, 1993
Sponsors: AIAA
Accession Number
93A21114
Distribution Limits
Public
Copyright
Other

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