PSP measurement of fuel mixing in a supersonic combustor of scram-jet engine model

Masashi Matsumoto, Goro Masuya, Sadatake Tomioka, Yuji Ikeda, Susumu Teramoto

Research output: Contribution to conferencePaper

1 Citation (Scopus)

Abstract

The mixing fields within a scram-jet combustion chamber are visualized using pressure-sensitive paint (PSP) as an oxygen sensor. The experiments are performed in a small supersonic wind tunnel at the National Aerospace Laboratory - Kakuda Research Center (NAL-KRC). The main stream Mach number is 2.4, and the dynamic pressure ratios between the injected gas and the main stream are 0.3, 0.7, 1.1 and 1.5. Three fuel injection nozzles are used; both oxygen and air are injected from these nozzles. The spread of the injected gas is measured to observe the effects of placing the nozzles in different positions. The results show that the jet has its own independent flow structure, and that little mixing of gases occurs between the flow structures created by each nozzle. When the injection dynamic pressure ratio is increased, the fuel mixing in the vicinity of the wall surface decreases.

Original languageEnglish
Publication statusPublished - 2002 Dec 1
Event40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States
Duration: 2002 Jan 142002 Jan 17

Other

Other40th AIAA Aerospace Sciences Meeting and Exhibit 2002
CountryUnited States
CityReno, NV
Period02/1/1402/1/17

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

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  • Cite this

    Matsumoto, M., Masuya, G., Tomioka, S., Ikeda, Y., & Teramoto, S. (2002). PSP measurement of fuel mixing in a supersonic combustor of scram-jet engine model. Paper presented at 40th AIAA Aerospace Sciences Meeting and Exhibit 2002, Reno, NV, United States.