Cavity Coupled Aeroramp Injector Combustion Study

The objective of this study was to provide a direct comparison between the single angled injector and the aeroramp injector arrays in such a combustion environment. Ignition limits and pre-combustion shock position were used to define the operability differences while combustion efficiency and strea...

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Bibliographic Details
Main Authors: Olmstead, Dell T, Gruber, Mark R, Collatz, MacKenzie J, Branam, Richard D, Lin, Kuo-Cheng
Format: Report
Language:English
Subjects:
AERORAMP
BOOST PHASE
CAVITIES
COMBUSTION
Combustion and Ignition
COMBUSTORS
COMPARISON
COUPLING(INTERACTION)
FLAME HOLDERS
FLAMEHOLDING
FUEL INJECTION
IGNITION
INJECTORS
NEAR FIELD
PE62203F
Reciprocating and Rotating Engines
STATIC PRESSURE
SUPERSONIC COMBUSTION RAMJET ENGINES
SYMPOSIA
WUAFRL3012AI00
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Summary:The objective of this study was to provide a direct comparison between the single angled injector and the aeroramp injector arrays in such a combustion environment. Ignition limits and pre-combustion shock position were used to define the operability differences while combustion efficiency and stream thrust were used for performance comparisons. These parameters were determined by operating a scramjet combustor in dual-mode operation over the range of Mach numbers expected during scramjet takeover from a boost vehicle. Performance and operability conclusions are based on raw data from static pressures, temperature measurements, and thrust stand loading. It was determined that the operability reduces significantly for the aeroramp injector for all conditions tested, but the performance is virtually identical to that of the round injectors. The aeroramp injector performance indicated improved nearfield combustion with the potential for better performance in higher Mach number flow to include full supersonic combustion mode for which it was designed. Published in the Proceedings of the 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA 2009-5227, held in Denver, CO, on 2-5 Aug 2009. Prepared in cooperation with Air Force Institute of Technology and with Taitech, Inc.