Supersonic Combustion using Multiple Stinger-shaped Injectors

Kouchi, Toshinori; Tomioka, Sadatake; Hirano, Kohshi; Matsuo, Akiko; Masuya, Goro

doi:10.2322/tjsass.60.56

Cited by 4 publications

(2 citation statements)

References 15 publications

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“…The peak value of pressure-rise was located at the injection point, showing that the airflow decelerated to subsonic speed throughout pseudo-shock wave system. 12) Because this trend of wall pressure distributions was also observed in the ramjet-mode combustion case 13) , the flow field with pseudo-shock wave system was produced in cold flow.…”

Section: The Influence Of Injectant Gas Species On Mixing Characterissupporting

confidence: 54%

Research on Fuel Mixing in a Non-reacting Situation Simulating a Dual-mode Combustor

Arakawa

Tomioka

2019

AEROSPACE TECHNOLOGY JAPAN

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We investigated the influence of injectant species and air total temperature to mixing characteristics to find out dominant parameters to simulate mixing process in a dual-mode combustor with non-reacting mixing experiment, the combustor being capable to operate can in a ramjet-mode (subsonic combustion) and in a scramjet-mode (supersonic combustion). To evaluate mixing efficiency, Pitot pressure measurement and gas sampling at the several cross-sections were carried out with plural gases (helium, nitrogen, or argon) injected at sonic speed from wall-flushed mounted injectors to M2.5 cold (room temperature) or hot (1000K, 2000K) airflow without or with pseudo-shock wave system. By matching dynamic pressure ratio, the influence of injectant species to mixing characteristics was negligible in ramjet-and scramjet-mode cases, but the influence of air total temperature was not negligible in the ramjet-mode case.

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Section: The Influence Of Injectant Gas Species On Mixing Characterissupporting

confidence: 54%

Research on Fuel Mixing in a Non-reacting Situation Simulating a Dual-mode Combustor

Arakawa

Tomioka

2019

AEROSPACE TECHNOLOGY JAPAN

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“…5) Then, the PSW dramatically changes fuel and air mixing characteristics compared to those of scramjetmode operation. 6) Thus, mixing characteristics under ramjetmode operation should be investigated with the presence of the shock train. However, observation of mixing in reacting flows is hard to perform.…”

Section: Introductionmentioning

confidence: 99%

Fuel/Air Mixing in Reacting and Non-reacting Flows within a Dual-mode Combustor

Arakawa

Nojima

Kobayashi

et al. 2021

Trans. Japan Soc. Aero. S Sci.

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An experimental investigation on fuel and air mixing characteristics within a dual-mode combustor is presented. To determine the dominant parameters of mixing characteristics of fuel with airflow, fuel (H 2 or C 2 H 4 ) or inert gas (He, N 2 or Ar) were perpendicularity injected from plural circular orifices into high-or room-temperature M2.5 airflows decelerated through pseudo-shockwave systems. Under similar dynamic pressure ratios, fuel mass flux contours downstream of the injector were similar between the H 2 and C 2 H 4 reacting cases. However, fuel mass flux contours were different between the C 2 H 4 reacting and Ar non-reacting cases due to the heat-release effect during local mixing. On the other hand, heatrelease effect on mixing efficiency was found to be minor in bulk-scale mixing evaluation. It was found that C 2 H 4 mixing efficiency with an equivalence ratio of 1.6 could be predicted within an error of a few percent from Ar mixing results under similar dynamic pressure ratio and similar peak pressure.

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