Combustion performance of supersonic combustor with stinger-shaped fuel injector

Toshinori Kouchi, K. Hirano, A. Matsuo, K. Kobayashi, S. Tomioka, M. Izumikawa

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

4 Citations (Scopus)

Abstract

Supersonic combustor with single "stinger-shaped" injector or multi ones arranged side-by-side in the spanwise direction were tested in a direct-connect wind-tunnel facility at a Mach 2.5 with a stagnation condition of 1.05 MPa and 2060 K. The stinger-shaped injector, having sharp leading edge followed by a streamwise slit, produced higher jet penetration in the height-wise direction as compared with the circular injector case at low jet dynamic pressure regime in our previous cold flow tests. In the combustion test, the single stinger-shaped injector produced higher jet penetration, resulting in 10 % higher thrust than the circular case when combustion region was limited in the diverging-area combustor. This injector also provided higher thrust even when flame was anchored around the injector with increasing fuel equivalence ratio (i.e. jet dynamic pressure), though the penetration reduced. This was because the stinger-shaped injector had better flame-holding performance near the injector. In the multi injector case, even with the stinger-shaped injector, the plume growing in the vertical direction, the adjacent fuel jets merged and the large plume was formed. The advantage of the stinger shape was diminished. The thrust performance in the stinger case, however, remained higher than that in the circular case.

Original languageEnglish
Title of host publication44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Publication statusPublished - 2008
Externally publishedYes
Event44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit - Hartford, CT, United States
Duration: Jul 21 2008Jul 23 2008

Other

Other44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
CountryUnited States
CityHartford, CT
Period7/21/087/23/08

Fingerprint

combustion chambers
Combustors
injectors
combustion
penetration
thrust
plume
high thrust
Jet fuel
dynamic pressure
Mach number
Wind tunnels
wind tunnel
plumes
cold flow tests
flames
sharp leading edges
jet engine fuels
wind tunnels
slits

ASJC Scopus subject areas

  • Aerospace Engineering
  • Control and Systems Engineering
  • Space and Planetary Science
  • Energy(all)
  • Electrical and Electronic Engineering
  • Mechanical Engineering

Cite this

Kouchi, T., Hirano, K., Matsuo, A., Kobayashi, K., Tomioka, S., & Izumikawa, M. (2008). Combustion performance of supersonic combustor with stinger-shaped fuel injector. In 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Combustion performance of supersonic combustor with stinger-shaped fuel injector. / Kouchi, Toshinori; Hirano, K.; Matsuo, A.; Kobayashi, K.; Tomioka, S.; Izumikawa, M.

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2008.

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

Kouchi, T, Hirano, K, Matsuo, A, Kobayashi, K, Tomioka, S & Izumikawa, M 2008, Combustion performance of supersonic combustor with stinger-shaped fuel injector. in 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Hartford, CT, United States, 7/21/08.
Kouchi T, Hirano K, Matsuo A, Kobayashi K, Tomioka S, Izumikawa M. Combustion performance of supersonic combustor with stinger-shaped fuel injector. In 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2008
Kouchi, Toshinori ; Hirano, K. ; Matsuo, A. ; Kobayashi, K. ; Tomioka, S. ; Izumikawa, M. / Combustion performance of supersonic combustor with stinger-shaped fuel injector. 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2008.
@inproceedings{a7ae56f52cf74269a087e01e9300c45c,
title = "Combustion performance of supersonic combustor with stinger-shaped fuel injector",
abstract = "Supersonic combustor with single {"}stinger-shaped{"} injector or multi ones arranged side-by-side in the spanwise direction were tested in a direct-connect wind-tunnel facility at a Mach 2.5 with a stagnation condition of 1.05 MPa and 2060 K. The stinger-shaped injector, having sharp leading edge followed by a streamwise slit, produced higher jet penetration in the height-wise direction as compared with the circular injector case at low jet dynamic pressure regime in our previous cold flow tests. In the combustion test, the single stinger-shaped injector produced higher jet penetration, resulting in 10 {\%} higher thrust than the circular case when combustion region was limited in the diverging-area combustor. This injector also provided higher thrust even when flame was anchored around the injector with increasing fuel equivalence ratio (i.e. jet dynamic pressure), though the penetration reduced. This was because the stinger-shaped injector had better flame-holding performance near the injector. In the multi injector case, even with the stinger-shaped injector, the plume growing in the vertical direction, the adjacent fuel jets merged and the large plume was formed. The advantage of the stinger shape was diminished. The thrust performance in the stinger case, however, remained higher than that in the circular case.",
author = "Toshinori Kouchi and K. Hirano and A. Matsuo and K. Kobayashi and S. Tomioka and M. Izumikawa",
year = "2008",
language = "English",
isbn = "9781563479434",
booktitle = "44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit",

}

TY - GEN

T1 - Combustion performance of supersonic combustor with stinger-shaped fuel injector

AU - Kouchi, Toshinori

AU - Hirano, K.

AU - Matsuo, A.

AU - Kobayashi, K.

AU - Tomioka, S.

AU - Izumikawa, M.

PY - 2008

Y1 - 2008

N2 - Supersonic combustor with single "stinger-shaped" injector or multi ones arranged side-by-side in the spanwise direction were tested in a direct-connect wind-tunnel facility at a Mach 2.5 with a stagnation condition of 1.05 MPa and 2060 K. The stinger-shaped injector, having sharp leading edge followed by a streamwise slit, produced higher jet penetration in the height-wise direction as compared with the circular injector case at low jet dynamic pressure regime in our previous cold flow tests. In the combustion test, the single stinger-shaped injector produced higher jet penetration, resulting in 10 % higher thrust than the circular case when combustion region was limited in the diverging-area combustor. This injector also provided higher thrust even when flame was anchored around the injector with increasing fuel equivalence ratio (i.e. jet dynamic pressure), though the penetration reduced. This was because the stinger-shaped injector had better flame-holding performance near the injector. In the multi injector case, even with the stinger-shaped injector, the plume growing in the vertical direction, the adjacent fuel jets merged and the large plume was formed. The advantage of the stinger shape was diminished. The thrust performance in the stinger case, however, remained higher than that in the circular case.

AB - Supersonic combustor with single "stinger-shaped" injector or multi ones arranged side-by-side in the spanwise direction were tested in a direct-connect wind-tunnel facility at a Mach 2.5 with a stagnation condition of 1.05 MPa and 2060 K. The stinger-shaped injector, having sharp leading edge followed by a streamwise slit, produced higher jet penetration in the height-wise direction as compared with the circular injector case at low jet dynamic pressure regime in our previous cold flow tests. In the combustion test, the single stinger-shaped injector produced higher jet penetration, resulting in 10 % higher thrust than the circular case when combustion region was limited in the diverging-area combustor. This injector also provided higher thrust even when flame was anchored around the injector with increasing fuel equivalence ratio (i.e. jet dynamic pressure), though the penetration reduced. This was because the stinger-shaped injector had better flame-holding performance near the injector. In the multi injector case, even with the stinger-shaped injector, the plume growing in the vertical direction, the adjacent fuel jets merged and the large plume was formed. The advantage of the stinger shape was diminished. The thrust performance in the stinger case, however, remained higher than that in the circular case.

UR - http://www.scopus.com/inward/record.url?scp=77957855721&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=77957855721&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:77957855721

SN - 9781563479434

BT - 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

ER -