Abstract
The Mach 2 hydrogen-air supersonic combustor model without diffuser was designed and tested in atmospheric inflow condition. A new supersonic mixer, which was vent slot mixer (VSM), was developed and confirmed its performance as a mixing device. At low enthalpy inflow condition, plasma jet torch was used as the igniter and the flame-holder. The VSM showed that the interaction between the fuel and the air through the vent spread the fuel to the spanwise direction in the recirculation region. The shock train structure generally depends on the combustion pressure, and the combustor condition becomes the unstart condition with combustion pressure increase. Although the mixer loses its mixing efficiency under the shock train, the VSM shows that it stabilizes the combustion around the vent. Therefore, the VSM has distinct characteristics for the mixing efficiency and the combustion stabilization.
| Original language | English |
|---|---|
| Title of host publication | 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference |
| Publication status | Published - 2009 |
| Externally published | Yes |
| Event | 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference - Bremen, Germany Duration: Oct 19 2009 → Oct 22 2009 |
Other
| Other | 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference |
|---|---|
| Country | Germany |
| City | Bremen |
| Period | 10/19/09 → 10/22/09 |
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ASJC Scopus subject areas
- Engineering(all)
Cite this
Development of a new supersonic mixer for dual-mode scramjet engine combustor. / Kim, Chae Hyoung; Jeung, In Seuck; Choi, Byungil; Kouchi, Toshinori; Masuya, Goro.
16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. 2009. 2009-7257.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Development of a new supersonic mixer for dual-mode scramjet engine combustor
AU - Kim, Chae Hyoung
AU - Jeung, In Seuck
AU - Choi, Byungil
AU - Kouchi, Toshinori
AU - Masuya, Goro
PY - 2009
Y1 - 2009
N2 - The Mach 2 hydrogen-air supersonic combustor model without diffuser was designed and tested in atmospheric inflow condition. A new supersonic mixer, which was vent slot mixer (VSM), was developed and confirmed its performance as a mixing device. At low enthalpy inflow condition, plasma jet torch was used as the igniter and the flame-holder. The VSM showed that the interaction between the fuel and the air through the vent spread the fuel to the spanwise direction in the recirculation region. The shock train structure generally depends on the combustion pressure, and the combustor condition becomes the unstart condition with combustion pressure increase. Although the mixer loses its mixing efficiency under the shock train, the VSM shows that it stabilizes the combustion around the vent. Therefore, the VSM has distinct characteristics for the mixing efficiency and the combustion stabilization.
AB - The Mach 2 hydrogen-air supersonic combustor model without diffuser was designed and tested in atmospheric inflow condition. A new supersonic mixer, which was vent slot mixer (VSM), was developed and confirmed its performance as a mixing device. At low enthalpy inflow condition, plasma jet torch was used as the igniter and the flame-holder. The VSM showed that the interaction between the fuel and the air through the vent spread the fuel to the spanwise direction in the recirculation region. The shock train structure generally depends on the combustion pressure, and the combustor condition becomes the unstart condition with combustion pressure increase. Although the mixer loses its mixing efficiency under the shock train, the VSM shows that it stabilizes the combustion around the vent. Therefore, the VSM has distinct characteristics for the mixing efficiency and the combustion stabilization.
UR - http://www.scopus.com/inward/record.url?scp=77958592214&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=77958592214&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:77958592214
SN - 9781600867408
BT - 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference
ER -