Combustion Performance of Supersonic Combustor with Stinger-Shaped Fuel Injector

Kouchi, Toshinori; Hirano, Kohshi; Matsuo, Akiko; Kobayashi, Kan; Tomioka, Sadatake; Izumikawa, Muneo

doi:10.2514/6.2008-4503

Cited by 4 publications

(4 citation statements)

References 5 publications

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“…We experimentally confirmed that the performance of a combustor with a stinger injector installed is much higher than that with a conventional circular injector. 9,10) In the series of experiments, we only considered single-injector configurations.…”

Section: Introductionmentioning

confidence: 99%

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Supersonic Combustion using Multiple Stinger-shaped Injectors

Kouchi

Tomioka

Hirano

et al. 2017

Trans. Japan Soc. Aero. S Sci.

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Section: Introductionmentioning

confidence: 99%

“…The geometrical shape of each stinger port is the same as the previous one. [8][9][10] The center-to-center spacing of the injectors (s) was set to be 20 mm with the four injectors oriented to have equal spacing for the combustor width (94.3-mm-width/5 intervals for 4 injectors). This corresponded to s=D $ 6:7.…”

Section: Introductionmentioning

confidence: 99%

Supersonic Combustion using Multiple Stinger-shaped Injectors

Kouchi

Tomioka

Hirano

et al. 2017

Trans. Japan Soc. Aero. S Sci.

Self Cite

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“…Compared with wall injection techniques such as cavity, fuel was injected into the core stream directly from strut, which can result in a better distribution of fuel in the core stream and lower wall temperature and higher value in the core stream. In addition, the improved combustion performance brings larger thrust increment [6,7], which can overcome the drag caused by strut. However, the drag cannot be neglected in the coldstate flow.…”

Section: Introductionmentioning

confidence: 99%

Effects of strut swept angle on the drag of scramjet

Bao

Zong

Chang

et al. 2011

Proceedings of the Institution of Mechanical Engineers, Part G:

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Swept angle is one of the most important geometric parameters of the strut in scramjet. The change in swept angle will make the geometric shape of the strut different and lead to distinct performances. Computational fluid dynamics method has been used in this study to obtain the cold-state flow field of scramjet model with struts of different swept angles at freestream Mach numbers 5 and 6. The results show that the effect of strut swept angle (from 0 to 60 ) on the flow-field structure, total pressure losses, and drag coefficients is less. However, in the cases when strut swept angle is larger than 60 , the shock waves have been weakened significantly and so are the total pressure losses and the strut drag coefficients. In addition, the drag coefficients of all the struts are overall very small because of the small wedge angle of the leading edge. Also, the drag coefficient on the struts reduces when Mach number of freestream increases.

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“…relative force of blowing), 2 the geometry of the jet itself (e.g. disturbance to the crossflow), 7,20 and the angle of injection. The dynamic pressure ratio is bounded by maximum fuel system pressure and the desire to produce an underexpanded plume.…”

Section: Design Tradeoffs Of Injection and Mixingmentioning

confidence: 99%

Study of Forebody Injection and Mixing with Application to Hypervelocity Airbreathing Propulsion

Axdahl

Kumar²,

Wilhite

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The use of premixed, shock-induced combustion in the context of a hypervelocity, airbreathing vehicle requires effective injection and mixing of hydrogen fuel and air on the vehicle forebody. Three dimensional computational simulations of fuel injection and mixing from flush-wall and modified ramp and strut injectors are reported in this study. A well-established code, VULCAN, is used to conduct nonreacting, viscous, turbulent simulations on a flat plate at conditions relevant to a Mach 12 flight vehicle forebody. In comparing results of various fuel injection strategies, it is found that strut injection provides the greatest balance of performance between mixing efficiency and stream thrust potential.

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Combustion Performance of Supersonic Combustor with Stinger-Shaped Fuel Injector

Cited by 4 publications

References 5 publications

Supersonic Combustion using Multiple Stinger-shaped Injectors

Supersonic Combustion using Multiple Stinger-shaped Injectors

Effects of strut swept angle on the drag of scramjet

Study of Forebody Injection and Mixing with Application to Hypervelocity Airbreathing Propulsion

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