Tests of the JAPHAR dual mode ramjet engine

Dessornes, O.; Scherrer, Dominique

doi:10.1016/j.ast.2005.01.007

Cited by 30 publications

(4 citation statements)

References 3 publications

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“…In this respect, it must be emphasized that such a PSR or well-stirred reactor (WSR) representation is standardly retained as a one of the elementary building blocks of supersonic combustion modeling within either the RANS or the LES framework [53][54][55][56]. The composition of the reactive mixture of hydrogen and vitiated air is described using nine chemical species: H 2 , H 2 O, N 2 , O 2 , OH, H, O, HO 2 and H 2 O 2 , and the finite-rate chemical reactions are described with the eighteen step chemical scheme proposed by Jachimowski [57].…”

Section: Turbulent Reactive Flow Modelingmentioning

confidence: 99%

Wall Roughness Effects on Combustion Development in Confined Supersonic Flow

Pelletier

Ferrier

Vincent‐Randonnier

et al. 2021

Journal of Propulsion and Power

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Reactive and non-reactiveReynolds-averaged Navier-Stokes (RANS) simulations of hydrogen injection into a confined transverse supersonic flow of vitiated air are conducted. The corresponding conditions were studied in the LAPCAT-II combustor. We consider two operating conditions, which differ in the value of the momentum ratio between the hydrogen and vitiated air inlet streams, thus leading to two distinct values of the equivalence ratio (ER). For its smallest value, smooth combustion develops subject to a preliminary thermal runaway period, while for its largest value, combustion is more strongly intertwined with shock wave dynamics and boundary layer separation. Special emphasis is placed on the possible effects of wall roughness on this reactive flow development. One amongst the conclusions of preliminary computational analyses of the present flowfield was that it may play a significant role on combustion development. This is firmly confirmed in the present study, which takes explicitly the influence of wall roughness into account within the equivalent sand grain modeling framework. For the largest ER value, the combustion stabilization mechanism is found to change dramatically whether roughness is taken into account or not. Its influence is assessed through a detailed comparison with available experimental data.

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Section: Turbulent Reactive Flow Modelingmentioning

confidence: 99%

Wall Roughness Effects on Combustion Development in Confined Supersonic Flow

Pelletier

Ferrier

Vincent‐Randonnier

et al. 2021

Journal of Propulsion and Power

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“…Dessorness et al [1] studied on the influence of equivalence ratio on combustion mode transition, they found that the combustor changed from supersonic combustion mode to subsonic combustion mode as the equivalence ratio became larger. Sunami et al [2] studied on the mechanism of the mode transition from the weak combustion to the intensive combustion.…”

Section: Introductionmentioning

confidence: 98%

“…In the weak com-E-mail address: tianye@cardc.cn (Y. Tian). 1 Postgraduate student. 2 Research assistant.…”

Section: Introductionmentioning

confidence: 99%

Experimental and computational study on combustion performance of a kerosene fueled dual-mode scramjet engine

Tian

Xiao

Zhang

et al. 2015

Aerospace Science and Technology

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“…Thus, this heating method is widely used in many institutions (Ref. [5][6][7]. The heated gas, however, contains some vitiations e.g., radicals and water vapor.…”

Section: Introductionmentioning

confidence: 99%

Evaluation of Dual-Mode Combustor Characteristics with Vitiated and non-Vitiated Inflow

Noda

Tomioka

Sakuranaka

et al. 2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Supersonic combustion tests were conducted with a direct connected dual-mode combustor. To generate high enthalpy flow, either a hydrogen fueled vitiation heater or a storage heater was used to compare the inflow vitiation effects on the combustor wall pressure distributions. Regarding the storage heated flow, two stagnation temperature conditions were tested. One had a same level stagnation temperature to the vitiated flow, and the other was a higher stagnation temperature which was estimated to gives a matching pressure increase between vitiated and clean air flow. The experimental results showed that the pressure increase ratio of this higher stagnation temperature condition with clean flow seemed to give slightly smaller pressure magnitudes compared to the vitiated flow case at same equivalence ratio. In addition, OH radical gave small effects on pressure distributions. NomenclatureJ/kg H = ramp injector height, H = 6.35mm M = Mach number MW = Molecular weight P = pressure Ru = Universal gas constant T = temperature VAH = Vitiation Air Heater SAH = Storage Air Heater γ = specific heat ratio φ = Fuel equivalence ratio dq = Fuel heat release value, J/kg * = throat condition 0 = stagnation condition air = condition of air flow fuel = condition of fuel flow w = condition on wall

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Tests of the JAPHAR dual mode ramjet engine

Cited by 30 publications

References 3 publications

Wall Roughness Effects on Combustion Development in Confined Supersonic Flow

Wall Roughness Effects on Combustion Development in Confined Supersonic Flow

Experimental and computational study on combustion performance of a kerosene fueled dual-mode scramjet engine

Evaluation of Dual-Mode Combustor Characteristics with Vitiated and non-Vitiated Inflow

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