Development of a new supersonic mixer for dual-mode scramjet engine combustor

Chae Hyoung Kim, In Seuck Jeung, Byungil Choi, Toshinori Kouchi, Goro Masuya

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

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 languageEnglish
Title of host publication16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference
Publication statusPublished - 2009
Externally publishedYes
Event16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference - Bremen, Germany
Duration: Oct 19 2009Oct 22 2009

Other

Other16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference
CountryGermany
CityBremen
Period10/19/0910/22/09

Fingerprint

Vents
Combustors
Engines
Plasma jets
Air
Mach number
Enthalpy
Stabilization
Hydrogen

ASJC Scopus subject areas

  • Engineering(all)

Cite this

Kim, C. H., Jeung, I. S., Choi, B., Kouchi, T., & Masuya, G. (2009). Development of a new supersonic mixer for dual-mode scramjet engine combustor. In 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference [2009-7257]

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 proceedingConference contribution

Kim, CH, Jeung, IS, Choi, B, Kouchi, T & Masuya, G 2009, Development of a new supersonic mixer for dual-mode scramjet engine combustor. in 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference., 2009-7257, 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, Bremen, Germany, 10/19/09.
Kim CH, Jeung IS, Choi B, Kouchi T, Masuya G. Development of a new supersonic mixer for dual-mode scramjet engine combustor. In 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. 2009. 2009-7257
Kim, Chae Hyoung ; Jeung, In Seuck ; Choi, Byungil ; Kouchi, Toshinori ; Masuya, Goro. / Development of a new supersonic mixer for dual-mode scramjet engine combustor. 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. 2009.
@inproceedings{4eac80490e4a48caaadbf2baff32dc1c,
title = "Development of a new supersonic mixer for dual-mode scramjet engine combustor",
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.",
author = "Kim, {Chae Hyoung} and Jeung, {In Seuck} and Byungil Choi and Toshinori Kouchi and Goro Masuya",
year = "2009",
language = "English",
isbn = "9781600867408",
booktitle = "16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference",

}

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 -