Accession Number:

ADA532997

Title:

Cavity Coupled Aeroramp Injector Combustion Study

Descriptive Note:

Conference paper (postprint)

Corporate Author:

AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH PROPULSION DIRECTORATE

Report Date:

2009-08-01

Pagination or Media Count:

18.0

Abstract:

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.

Subject Categories:

  • Combustion and Ignition
  • Reciprocating and Rotating Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE