FullText URL JPP_29_3_639.pdf
Author Kouchi, Toshinori| Masuya, Goro| Hirano, Kohshi| Matsuo, Akiko|
Abstract We developed a stinger-shaped injector (stinger injector) for supersonic combustors in cold-flow experiments. The stinger injector has a port geometry with a sharp leading edge in front of a streamwise slit. This injector produced higher jet penetration at a lower jet-tocrossflow momentum flux ratio (J) than a conventional circular injector. We applied the injector in a Mach 2.44 combustion test at a stagnation temperature of 2060 K. At a low fuel equivalence ratio (Φ) regime (i.e., low J regime), the injector produced 10% higher pressure thrust than the circular injector because of high jet penetration as expected from the coldflow experiments. Even at a moderate Φ regime, the stinger injector produced higher pressure thrust than the circular injector. At moderate Φ, the stinger injector held the flame around the injector and generated a precombustion shock wave in front of the injector. The presence of the precombustion shock wave decreased the momentum flux of the crossflow air and diminished the advantage of the injector for jet penetration. The injector, however, produced higher pressure thrust because better flame-holding produced higher pressure around the injector. At a higher Φ regime, the precombustion shock wave went upstream with both injectors. The far-upstream presence of a precombustion shock wave increased the turbulence in the crossflow and spread the fuel from both injectors. Thus, the difference in injector shape was insignificant for thrust performance
Note This is an Accepted Manuscript of an article published by American Institute of Aeronautics and Astronautics
Published Date 2013
Publication Title Journal of Propulsion and Power
Volume volume29
Issue issue3
Publisher American Institute of Aeronautics and Astronautics
Start Page 639
End Page 647
ISSN 0748-4658
NCID AA10459896
Content Type Journal Article
language 英語
OAI-PMH Set 岡山大学
File Version author
DOI 10.2514/1.B34524
Web of Sience KeyUT 000318826400015
Related Url isVersionOf https://doi.org/10.2514/1.B34524
FullText URL JPP_28_1_106.pdf
Author Kouchi, Toshinori| Masuya, Goro| Mitani, Tohru| Tomioka, Sadatake|
Abstract A sidewall compression scramjet engine operated in two combustion modes under Mach 6 flight condition, weak- and intensive-combustion modes. The weak mode occurred below the overall fuel equivalence ratio (Φ) of around 0.4. Transition from the weak mode to the intensive mode occurred at Φ ~ 0.4, accompanied by a sudden increase in thrust. Mechanisms of the transition were numerically investigated in this study. Our simulations captured the sudden increase in thrust at the mode transition. In the weak mode, combustion occurred in only a region near the topwall where an igniter was installed. The combustion region expanded toward the cowl with boundary-layer separation at the mode transition. Our simulations demonstrated that low ignition capability resulted in the weak mode. We demonstrated that the presence of additional igniters on the sidewalls improved the ignition capability and achieved the intensive mode in the entire Φ range.
Note This is an Accepted Manuscript of an article published by American Institute of Aeronautics and Astronautics
Published Date 2012
Publication Title Journal of Propulsion and Power
Volume volume28
Issue issue1
Publisher American Institute of Aeronautics and Astronautics
Start Page 106
End Page 112
ISSN 07484658
NCID AA10459896
Content Type Journal Article
language 英語
OAI-PMH Set 岡山大学
File Version author
DOI 10.2514/1.B34172
Web of Sience KeyUT 000299461500009
Related Url isVersionOf https://doi.org/10.2514/1.B34172