A comparative study of hypersonic fuel/air mixing enhancement by ramp and cantilevered ramp injectors

Sislian, J. P.; Schumacher, J.

doi:10.2514/6.1999-4873

Cited by 14 publications

(8 citation statements)

References 31 publications

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“…64 inferences were drawn: mixing efficiency of cantilevered ramp injector for the considered flow conditions was 45 percent higher than that of conventional ramp at an expense of 20 percent total pressure loss, higher than conventional ramp [66]. …”

Section: (A) (B)mentioning

confidence: 99%

See 1 more Smart Citation

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Tourani

2011

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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Section: (A) (B)mentioning

confidence: 99%

“…Also, strong vortices (M and N), present behind the bluff-body further enhance the mixing process along with providing a flame-holding zone, similar to a low angled wall injection [65]. A numerical study has been performed by Sislian and Schumacher [66] comparing conventional and cantilevered ramp injectors. The following…”

Section: Ramp Injectionmentioning

confidence: 99%

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Tourani

2011

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…On the flow conditions considered in ref. [6], its mixing efficiency is about 45% higher than that of the conventional ramp at x=0.8 m downstream of the injector exit with an approximately 20% penalty in the total pressure loss.…”

Section: Fuel/air Premixingmentioning

confidence: 91%

“…In order to improve the premixed performance, Sis-lian and Schumacher [6] put forward an injector geometry, which embodies the characteristics of both conventional ramp and low angle wall injection techniques, referred to as a cantilevered ramp injector，as shown in Figure 3. Numerical results showed that the mixing performances of the cantilevered ramp injector are appreciably superior to those of the conventional ramp injectors.…”

Section: Fuel/air Premixingmentioning

confidence: 99%

Research status of key techniques for shock-induced combustion ramjet (shcramjet) engine

Huang

Qin

Luo

et al. 2010

Sci. China Ser. E-Technol. Sci.

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As one of the most promising propulsion systems in the future, shock-induced combustion ramjet engine can remedy the disadvantages in the integrated design of scramjet engine and airframe. It can shorten the length of the combustor, lighten the structure weight of the engine and keep better performance in a broad range of flight Mach number. The elementary principle of shockinduced combustion ramjet engine is introduced. The key technologies of this kind of propulsion system are described, while their research status is presented in detail. Suggestion on the development of shcramjet engine in China is put forward. aerospace propulsion system, shock-induced combustion ramjet engine, premature ignition, premixed efficiency, denotationCitation: Huang W, Qin H, Luo S B, et al. Research status of key techniques for shock-induced combustion ramjet (shcramjet) engine. Sci China Tech Sci, 2010, 53: 220−226,

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“…3,36,27,24,37 Cantilevered ramp fuel injectors act similarly to regular ramp injectors in that they create streamwise vortices and baroclinique torque that serve to enhance the mixing process. The difference is that they are lifted and seperated from the wall such that the fuel is injected away from the wall and the hot boundary layer.…”

Section: Fuel / Air Premixingmentioning

confidence: 99%

Numerically Simulated Comparative Performance of a Scramjet and Shcramjet at Mach 11

Chan

Sislian

Alexander

2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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This study investigates the design and aeropropulsive performance of a complete, hydrogen powered, shock-induced combustion ramjet (shcramjet) at a flight Mach number of 11 and altitude of 34.5 km. The design includes a Prandtl-Meyer compression inlet, cantilevered ramp fuel injectors, a shock-inducing wedge and a divergent nozzle. Numerical studies are undertaken using the WARP code that solves the three-dimensional Favre-averaged Navier-Stokes equations closed by the Wilcox k-ω turbulence model and the Jachimowski H 2 /air chemical kinetics model. Studies of fuel injection properties, mixing duct length, combustor wedge and nozzle geometry are completed to maximize the overall performance of the vehicle. The final shcramjet configuration generates a specific impulse of 1110 s. A comparison is undertaken with a scramjet vehicle at identical flight conditions and using many of the same components. The comparable scramjet generates a higher specific impulse of 1450 s although it is significantly larger and therefore heavier.ii

show abstract

A comparative study of hypersonic fuel/air mixing enhancement by ramp and cantilevered ramp injectors

Cited by 14 publications

References 31 publications

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Research status of key techniques for shock-induced combustion ramjet (shcramjet) engine

Numerically Simulated Comparative Performance of a Scramjet and Shcramjet at Mach 11

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