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

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

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

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

ENG - Graduate School of Engineering (Common)

Research output: Contribution to conference › Paper › peer-review

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 language	English
Publication status	Published - 2002 Dec 1
Event	40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States Duration: 2002 Jan 14 → 2002 Jan 17

Other

Other	40th AIAA Aerospace Sciences Meeting and Exhibit 2002
Country/Territory	United States
City	Reno, NV
Period	02/1/14 → 02/1/17

ASJC Scopus subject areas

Space and Planetary Science
Aerospace Engineering

Cite this

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title = "PSP measurement of fuel mixing in a supersonic combustor of scram-jet engine model",

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.",

author = "Masashi Matsumoto and Goro Masuya and Sadatake Tomioka and Yuji Ikeda and Susumu Teramoto",

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T1 - PSP measurement of fuel mixing in a supersonic combustor of scram-jet engine model

AU - Matsumoto, Masashi

AU - Masuya, Goro

AU - Tomioka, Sadatake

AU - Ikeda, Yuji

AU - Teramoto, Susumu

PY - 2002/12/1

Y1 - 2002/12/1

N2 - 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.

AB - 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.

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T2 - 40th AIAA Aerospace Sciences Meeting and Exhibit 2002

Y2 - 14 January 2002 through 17 January 2002

ER -

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

Abstract

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