Numerical Simulation of Vitiation Effects on a Hydrogen-Fueled Dual-Mode Scramjet

Vyas, Manan A.; Engblom, William; Georgiadis, Nicholas J.; Trefny, Charles J.; Bhagwandin, Vishal A.

doi:10.2514/6.2010-1127

Cited by 22 publications

(17 citation statements)

References 23 publications

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“…The variation of the temperature at the wall shows to have an e¨ect on the peak combustion pressure, length, and location of the shock train. Similar in §uences were observed by Vyas et al [19]. Figure 19a shows the surface pressure distribution at the top wall for T wall = 300, 600, and 900 K with a constant equivalence ratio of φ = 0.55.…”

Section: In §Uence Of Wall Temperaturesupporting

confidence: 84%

Numerical investigation of a hydrogen-fueled scramjet combustor at flight conditions

Rabadan

2013

Progress in Propulsion Physics

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Numerical investigations of a hydrogen-fueled scramjet combustor at cruise §ight conditions of Mach 8 at an altitude of 30 km have been performed. Two combustor con¦gurations were investigated: a single-stage combustor with a central strut injector and a two-staged combustor combining the central strut and wall-mounted ramp injectors. These numerical simulations are aimed to study the §ow structure, supersonic mixing, autoignition, and combustion for the present combustor con¦gurations. A turbulent §ow from a separate intake calculation was used as in §ow condition for the combustor. A better performance for the two-staged combustor con¦guration was observed. The combination of the central strut injection together with the wall-ramp injection improved the turbulent mixing and, consequently, the combustion process. Inside the supersonic combustion chamber, the autoignition zone occurred downstream of the injectors, and combustion takes place accompanied by high heat release and pressure rise. As the equivalence ratio was increased, the combustion became stronger causing an upstream displacement of the shock train producing di¨erent pressure variations. For the two-staged combustor con¦guration, the location of the autoignition zone was found to appear further upstream compared to single-stage combustor. Mixing was improved by addition of the second-stage injection. The in §uence of the wall temperature was also investigated showing an e¨ect on the combustion pressure rise and the length and location of the shock train.

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Section: In §Uence Of Wall Temperaturesupporting

confidence: 84%

Numerical investigation of a hydrogen-fueled scramjet combustor at flight conditions

Rabadan

2013

Progress in Propulsion Physics

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“…The fuel injector geometry is a convergent-divergent nozzle. We have applied RANS based calculations to this configuration, 12,53,54 with much of the focus on determining the capability of CFD to replicate differences between clean air and vitiated air on engine performance as a function of fuel equivalence ratio. Gupte et al 55 used finite element analysis to examine the thermal-structural response of the UVA test article and found substantial effects of the thermal deformation on the predicted flowfield when comparing CFD solutions from the baseline to the thermally deformed configuration.…”

Section: Combustor / Exhaust System Modelingmentioning

confidence: 99%

Status of turbulence modeling for hypersonic propulsion flowpaths

Georgiadis

Yoder

Vyas

et al. 2014

Theor. Comput. Fluid Dyn.

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“…50 However, CFD results can match wall pressure data even when the flowfield is not correctly simulated, so the real test of the simulation is a comparison of CFD predictions to experimental measurements for velocity and other quantities in the core of the flow. All three components of velocity from CFD results are compared here to corresponding velocity components from SPIV measurements.…”

Section: Qualitative Comparison To Cfd Results Flowpathmentioning

confidence: 99%

Stereoscopic Particle Image Velocimetry Measurements in Scramjet Combustors

Smith¹

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The prospect of atmospheric flight at five times the speed of sound, or greater, has captivated researchers for many years. One type of hypersonic propulsion engine capable of providing such astounding flight-speeds is the Dual-mode scramjet (DMSJ). This engine is especially attractive because a single flowpath is used over a wide range of flight Mach numbers. However, the complex combustion process in a DMSJ is not well understood. The flowfield of a DMSJ combustor is highly turbulent and highly threedimensional due to fuel injection schemes and massive flow separation. These characteristics, along with temperatures in excess of 1200K, make experimental measurements extremely challenging.Therefore, three-component velocity

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Numerical Simulation of Vitiation Effects on a Hydrogen-Fueled Dual-Mode Scramjet

Cited by 22 publications

References 23 publications

Numerical investigation of a hydrogen-fueled scramjet combustor at flight conditions

Numerical investigation of a hydrogen-fueled scramjet combustor at flight conditions

Status of turbulence modeling for hypersonic propulsion flowpaths

Stereoscopic Particle Image Velocimetry Measurements in Scramjet Combustors

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