New injector geometry for penetration enhancement of perpendicular jet into supersonic flow

K. Hirano, Akiko Matsuo, T. Kouchi, M. Izumikawa, S. Tomioka

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

6 Citations (Scopus)

Abstract

Both the wind tunnel experiments and the numerical analyses on helium injections with various injector geometry configurations were performed in order to achieve high penetration and effective mixing between supersonic crossflow and injectant. The plume from the multiple-type injector, which is drawn upon the genetic algorithm, prevented plume diffusion because of aiming to reduce total pressure loss. The injectant from the orifice, which has sharp leading edge, mixed more effectively than the case of blunt leading edge injector and the smaller the half angle of the wedge shaped injector was, the larger the penetration height was obtained. In order to reduce the disturbance to the mainstream, the stinger shaped injector was proposed using the numerical analyses. When the stinger shaped injector was used, the penetration height increased by approximately 60% in comparison with the circular injector case and showed the most effective penetration performance. It is considerable that as the disturbance became smaller, the penetration height became larger. However, the stinger shaped injector has effective performance for the penetration in the condition of low dynamic pressure ratio only unlike the circular injector.

Original languageEnglish
Title of host publicationCollection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Pages238-252
Number of pages15
Volume1
Publication statusPublished - 2007
Event43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference - Cincinnati, OH, United States
Duration: 2007 Jul 82007 Jul 11

Other

Other43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
CountryUnited States
CityCincinnati, OH
Period07/7/807/7/11

Fingerprint

supersonic jet flow
injectors
penetration
geometry
augmentation
plume
disturbance
plumes
blunt leading edges
disturbances
sharp leading edges
wind tunnel
genetic algorithm
helium
pressure ratio
dynamic pressure
orifices
wind tunnels
genetic algorithms
wedges

ASJC Scopus subject areas

  • Space and Planetary Science

Cite this

Hirano, K., Matsuo, A., Kouchi, T., Izumikawa, M., & Tomioka, S. (2007). New injector geometry for penetration enhancement of perpendicular jet into supersonic flow. In Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference (Vol. 1, pp. 238-252)

New injector geometry for penetration enhancement of perpendicular jet into supersonic flow. / Hirano, K.; Matsuo, Akiko; Kouchi, T.; Izumikawa, M.; Tomioka, S.

Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Vol. 1 2007. p. 238-252.

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

Hirano, K, Matsuo, A, Kouchi, T, Izumikawa, M & Tomioka, S 2007, New injector geometry for penetration enhancement of perpendicular jet into supersonic flow. in Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference. vol. 1, pp. 238-252, 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Cincinnati, OH, United States, 07/7/8.
Hirano K, Matsuo A, Kouchi T, Izumikawa M, Tomioka S. New injector geometry for penetration enhancement of perpendicular jet into supersonic flow. In Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Vol. 1. 2007. p. 238-252
Hirano, K. ; Matsuo, Akiko ; Kouchi, T. ; Izumikawa, M. ; Tomioka, S. / New injector geometry for penetration enhancement of perpendicular jet into supersonic flow. Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Vol. 1 2007. pp. 238-252
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