Supersonic combustion with supersonic injection through diamond-shaped orifices

S. Tomioka, T. Kohchi, R. Masumoto, M. Izumikawa, Akiko Matsuo

Research output: Chapter in Book/Report/Conference proceedingConference contribution

3 Citations (Scopus)

Abstract

Supersonic injections through diamond-shaped injectors were applied to a supersonic combustor with a diverging section, with a Mach 2.4 incoming vitiated airflow at a total temperature of 2000 K, and combustion characteristics were experimentally investigated and compared to those with sonic injection through circular injectors. Without any flame-holding devices installed, scramjet-mode combustion was attained in wide range of fuel flow rate, in which the supersonic injections resulted in a higher pressure-rise in far-field than the sonic injections. Regardless of the injection scheme (i.e, orifice shape, orifice number, and injection conditions), transition to dual-mode combustion enhanced the thrust production, and the supersonic injection through the diamond-shaped orifice had lesser ability to cause the transition than the sonic injection through the circular orifice. The ability was enhanced by installation of a recess and introduction of recess fueling, and resulting combustor performance was slightly better than that with the sonic injection, in the case with single orifice. Both the number of the orifice and the injection pressure (by changing the total orifice throat area) were varied for the supersonic injection through the diamond-shaped orifice for fixed fuel flow rates, and the change in combustion characteristics were also reported.

Original languageEnglish
Title of host publication45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Publication statusPublished - 2009
Event45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit - Denver, CO, United States
Duration: 2009 Aug 22009 Aug 5

Other

Other45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
CountryUnited States
CityDenver, CO
Period09/8/209/8/5

Fingerprint

supersonic combustion
orifices
Orifices
diamond
Diamonds
combustion
diamonds
injection
Combustors
fuel flow
recesses
airflow
thrust
combustion chambers
Flow rate
injectors
Fueling
flow velocity
supersonic combustion ramjet engines
Mach number

ASJC Scopus subject areas

  • Aerospace Engineering
  • Control and Systems Engineering
  • Space and Planetary Science
  • Energy(all)
  • Electrical and Electronic Engineering
  • Mechanical Engineering

Cite this

Tomioka, S., Kohchi, T., Masumoto, R., Izumikawa, M., & Matsuo, A. (2009). Supersonic combustion with supersonic injection through diamond-shaped orifices. In 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Supersonic combustion with supersonic injection through diamond-shaped orifices. / Tomioka, S.; Kohchi, T.; Masumoto, R.; Izumikawa, M.; Matsuo, Akiko.

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2009.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Tomioka, S, Kohchi, T, Masumoto, R, Izumikawa, M & Matsuo, A 2009, Supersonic combustion with supersonic injection through diamond-shaped orifices. in 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Denver, CO, United States, 09/8/2.
Tomioka S, Kohchi T, Masumoto R, Izumikawa M, Matsuo A. Supersonic combustion with supersonic injection through diamond-shaped orifices. In 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2009
Tomioka, S. ; Kohchi, T. ; Masumoto, R. ; Izumikawa, M. ; Matsuo, Akiko. / Supersonic combustion with supersonic injection through diamond-shaped orifices. 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2009.
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