Numerical experiments of scramjet combustion with boundary-layer bleeding

Toshinori Kouchi, Tohru Mitani, Masatoshi Kodera, Goro Masuya

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

4 Citations (Scopus)

Abstract

Airframe-integrated scramjet engines swallow the boundary-layer which develops on the airframe of space planes. The scramjet engine easily falls into engine stall (engine unstart) due to the boundary-layer separation resulting from combustion. In this study, to investigate the unstart characteristics, numerical simulations of a scramjet engine with boundary-layer bleeding were performed using a reacting flow code which includes a one-equation turbulence model. This computation is calibrated by the experimental wall pressure distributions, heat fluxes and thrusts. The computation reproduces the prevention of engine unstart in the combustion tests with bleeding. Bleeding of 0.6% in a captured flow rate suppresses the flow separation and extends the start limit from the fuel equivalence ratio (φ) of 0.5 to 1.0. The computation at φ=1.0 shows that small-scale circular diffusion flames are anchored around individual fuel jets near the injectors. These structures disappear to form a large-scale envelope diffusion flame downstream of the combustor. The circular flames near the injectors account for 80% of the combustion efficiency and control the thrust performance.

Original languageEnglish
Title of host publication12th AIAA International Space Planes and Hypersonic Systems and Technologies
Publication statusPublished - 2003
Externally publishedYes
Event12th AIAA International Space Planes and Hypersonic Systems and Technologies 2003 - Norfolk, VA, United States
Duration: Dec 15 2003Dec 19 2003

Other

Other12th AIAA International Space Planes and Hypersonic Systems and Technologies 2003
CountryUnited States
CityNorfolk, VA
Period12/15/0312/19/03

Fingerprint

supersonic combustion ramjet engines
bleeding
airframes
engines
boundary layers
engine
Boundary layers
boundary layer
combustion
diffusion flames
Engines
injectors
thrust
combustion control
jet engine fuels
combustion efficiency
boundary layer separation
reacting flow
wall pressure
flow separation

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering
  • Control and Systems Engineering

Cite this

Kouchi, T., Mitani, T., Kodera, M., & Masuya, G. (2003). Numerical experiments of scramjet combustion with boundary-layer bleeding. In 12th AIAA International Space Planes and Hypersonic Systems and Technologies

Numerical experiments of scramjet combustion with boundary-layer bleeding. / Kouchi, Toshinori; Mitani, Tohru; Kodera, Masatoshi; Masuya, Goro.

12th AIAA International Space Planes and Hypersonic Systems and Technologies. 2003.

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

Kouchi, T, Mitani, T, Kodera, M & Masuya, G 2003, Numerical experiments of scramjet combustion with boundary-layer bleeding. in 12th AIAA International Space Planes and Hypersonic Systems and Technologies. 12th AIAA International Space Planes and Hypersonic Systems and Technologies 2003, Norfolk, VA, United States, 12/15/03.
Kouchi T, Mitani T, Kodera M, Masuya G. Numerical experiments of scramjet combustion with boundary-layer bleeding. In 12th AIAA International Space Planes and Hypersonic Systems and Technologies. 2003
Kouchi, Toshinori ; Mitani, Tohru ; Kodera, Masatoshi ; Masuya, Goro. / Numerical experiments of scramjet combustion with boundary-layer bleeding. 12th AIAA International Space Planes and Hypersonic Systems and Technologies. 2003.
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