Recent progress in scramjet/combined cycle engines at JAXA, Kakuda space center

Hiraiwa, Tetsuo; Ito, Katsuhiro; Sato, Shigeru; Ueda, Shuichi; Tani, Kazuo; Tomioka, Sadatake; Kanda, Takeshi

doi:10.1016/j.actaastro.2008.04.011

Cited by 23 publications

(12 citation statements)

References 12 publications

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“…[2] The deflagration front tip deformed into a V-shape around Φ max = 3.00, which caused the triple points to be doubled. The apex of the V-shape did not almost recede under strong non-uniformities.…”

Section: Resultsmentioning

confidence: 99%

“…Today, a totally reusable spaceplane is attracting increasing attention for its potential of improving substantial problems of the conventional rockets, such as their payload capacities and launching costs. 1,2) An air-breathing engine, instead of the conventional rocket engines, is suited for such reusability due to its high specific thrust. 1,2) No oxidizer needs to be mounted, which enables us to take more payload weight to the orbit.…”

Section: Introductionmentioning

confidence: 99%

“…1,2) An air-breathing engine, instead of the conventional rocket engines, is suited for such reusability due to its high specific thrust. 1,2) No oxidizer needs to be mounted, which enables us to take more payload weight to the orbit. In addition, since the spaceplane takes off and lands in the same way as conventional airplanes do, it will be more reliable and safe.…”

Section: Introductionmentioning

confidence: 99%

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Numerical Simulation of Incompletely Premixed Oblique Detonation Stabilized on a Solid Surface

Iwata

Nakaya

Tsue

2016

AEROSPACE TECHNOLOGY JAPAN

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Oblique detonation under incompletely premixed conditions has not been well understood and is of great concern when difficulty of high-speed premixing in Oblique Detonation Wave Engine (ODWE), which is one of the most potential hypersonic aerospace propulsion systems, is taken into account. This study numerically investigated effects of fuel concentration gradients on oblique detonation and shock-induced combustion formed on a 28.20° wedge by solving two-dimensional Navier-Stokes equations with a detailed chemical kinetic mechanism of hydrogen-air combustion. Oblique detonation with smooth-transition formed at a Mach number of 8.00, a static temperature of 300 K, and a static pressure of 8.50 kPa was referred as the completely premixed case. Fuel concentration gradients were described by the Gaussian function. At the maximum equivalence ratio of 2.00, Smooth-transition was replaced by abrupt-transition. When maximum equivalence ratio exceeded 3.00, a V-shaped flame front appeared with its leading edge located away from the wedge, which caused two separate triple-points to be observed. Second triple point appeared at the intersection of the incident shock or the detonation front and a reflected shock generated by compression waves on the lower side of the deflagration front. Increase of the front angle enabled intensive combustion to be maintained downstream of it.

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Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Numerical Simulation of Incompletely Premixed Oblique Detonation Stabilized on a Solid Surface

Iwata

Nakaya

Tsue

2016

AEROSPACE TECHNOLOGY JAPAN

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“…A rocket-based combined-cycle (RBCC) combustor [7,8] is yet another type of advanced propulsion system. This type of system has the widest flight envelope and application scope of those mentioned, and it can satisfy the various requirements of future aircraft, such as high altitude, high speed, and flight maneuverability.…”

Section: Introductionmentioning

confidence: 99%

Study of thermal throat of RBCC combustor based on one-dimensional analysis

Wang

Qin

et al. 2015

Acta Astronautica

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“…In this study Escher examined both SSTO and Two-Stage-To-Orbit (TSTO) applications for this engine. Hiraiwa et al (2008) presented their study of a scramjet and rocketramjet combined cycle engine which included both wind tunnel experiments and CFD evaluation of the combined cycle engine. The experiments were carried out at HIEST (High Enthalpy Shock Tunnel) and RJTF (Ramjet Test Facility) at the Kakuda space center, Japan.…”

Section: Introductionmentioning

confidence: 99%

Dynamics of Sonic Hydrogen Jet Injection and Mixing Inside Scramjet Combustor

Rana

Thornber

Drikakis

2013

Engineering Applications of Computational Fluid Mechanics

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This paper presents the application of a Finite Volume Godunov-type implicit large eddy simulation method to study fuel injection into the combustion chamber of HyShot-II scramjet engine without chemical reaction/combustion in order to understand the fuel injection and air-fuel (hydrogen) mixing. The study is carried out in two parts; part one presents analysis of 2D HyShot-II geometry (without fuel injection) incorporating high temperature gas formulation which is validated against the NASA Thermally-Perfect-Gas code in order to obtain the combustion chamber inlet conditions. These combustor initial conditions are then utilized in part two for 3D combustion chamber simulations with hydrogen injection but cold flow where a digital filter based turbulent inflow boundary condition has been utilized. The purpose of the study is to understand the flow physics, hydrogen jet penetration and air & fuel mixing inside the HyShot-II combustor which is vital at the design stages. Various flow features are investigated such as the Mach number, velocity, pressure distributions, temperature, turbulent kinetic energy, Reynolds stresses and the effect of counter rotating vortices on mixing. The results of full geometry simulations are compared with computational results from the German Aerospace Centre, DLR, whereas due to unavailability of any data for hydrogen cold flow the validity of the results is based upon a similar validation case presented earlier (Rana et al., 2011b).

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Recent progress in scramjet/combined cycle engines at JAXA, Kakuda space center

Cited by 23 publications

References 12 publications

Numerical Simulation of Incompletely Premixed Oblique Detonation Stabilized on a Solid Surface

Numerical Simulation of Incompletely Premixed Oblique Detonation Stabilized on a Solid Surface

Study of thermal throat of RBCC combustor based on one-dimensional analysis

Dynamics of Sonic Hydrogen Jet Injection and Mixing Inside Scramjet Combustor

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