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 language | English |
|---|---|
| Title of host publication | 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit |
| Publication status | Published - 2008 |
| Externally published | Yes |
| Event | 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit - Hartford, CT, United States Duration: Jul 21 2008 → Jul 23 2008 |
Other
| Other | 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit |
|---|---|
| Country | United States |
| City | Hartford, CT |
| Period | 7/21/08 → 7/23/08 |
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ASJC Scopus subject areas
- Aerospace Engineering
- Control and Systems Engineering
- Space and Planetary Science
- Energy(all)
- Electrical and Electronic Engineering
- Mechanical Engineering
Cite this
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 proceeding › Conference contribution
}
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 -