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

Huang, Wei; Qin, Hui; Luo, Shibin; Wang, Zhenguo

doi:10.1007/s11431-009-0379-7

Cited by 56 publications

(15 citation statements)

References 17 publications

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“…It is an important parameter for the flame holder design in combustor, which affects the efficiency of mixing and combustion [34][35][36][37]. The higher expansion ratio may lead to complex shock reflections and severe boundary layer separations, as to be discussed later, which can yield small cross-section area for inflow air and even causes congestions especially under the combustion condition.…”

Section: Effect Of Expansion Ratio On Reattachment Length the Expansmentioning

confidence: 99%

Effects of Inflow Mach Number and Step Height on Supersonic Flows over a Backward-Facing Step

Liu

Wang

Guo

et al. 2013

Advances in Mechanical Engineering

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The backward-facing step is practically implicated in many devices, encountering the massive separation flows. In the present study, simulations of supersonic flow over a backward-facing step have been carried out employing both RANS and LES. The simulated results are validated against the experimental data. The results of RANS and LES show a good comparison with the experimental results. Different inflow Mach numbers and expansion ratios are also investigated. The reattachment length decreases with the increase of inflow Mach number. The duct height has a great effect on the flow patterns. The present conclusions are helpful to understand the physics in supersonic separation flows and also provide theory basis for engineering applications.

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Section: Effect Of Expansion Ratio On Reattachment Length the Expansmentioning

confidence: 99%

Effects of Inflow Mach Number and Step Height on Supersonic Flows over a Backward-Facing Step

Liu

Wang

Guo

et al. 2013

Advances in Mechanical Engineering

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“…, hypersonic propulsion technology has drawn increasing attention from researchers. However, the flame-holding mechanism in the scramjet combustor cannot satisfy the requirement for cruising a long time in near-space [3] because of the short residence time of the mixture remaining in the supersonic flow, which is in the order of milliseconds [4]. This restricts improvement of the aerodynamic performance of hypersonic vehicles.…”

mentioning

confidence: 99%

“…To solve this problem, some fuel injection techniques have been proposed. The strut [5][6][7][8][9][10][11][12][13][14], the cavity [15][16][17][18], the cantilevered ramp [4], the backward facing step [19][20][21] and the combination [22][23][24][25], whose principle is to generate vorticity in the vicinity of the walls of the combustor. The region forming the vorticity, namely the recirculation zone, has low flow velocity.…”

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confidence: 99%

Parametric effects on the combustion flow field of a typical strut-based scramjet combustor

et al. 2011

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The flame-holding mechanism in hypersonic propulsion technology is the most important factor in prolonging the duration time of hypersonic vehicles. The two-dimensional coupled implicit Reynolds-averaged Navier-Stokes equations, the shear-stress transport k- turbulence model and the finite-rate/eddy-dissipation reaction models were used to simulate the combustion flow field of a typical strut-based scramjet combustor. We investigated the effects of the hydrogen-air reaction mechanism and fuel injection temperature and pressure on the parametric distributions in the combustor. The numerical results show qualitative agreement with the experimental data. The hydrogen-air reaction mechanism makes only a slight difference in parametric distributions along the walls of the combustor, and the expansion waves and shock waves exist in the combustor simultaneously. Furthermore, the expansion wave is formed ahead of the shock wave. A transition occurs from the shock wave to the normal shock wave when the injection pressure or temperature increases, and the reaction zone becomes broader. When the injection pressure and temperature both increase, the waves are pushed out of the combustor with subsonic flows. When the waves are generated ahead of the strut, the separation zone is formed in double near the walls of the combustor because of the interaction of the shock wave and the boundary layer. The separation zone becomes smaller and disappears with the disappearance of the shock wave. Because of the horizontal fuel injection, the vorticity is generated near the base face of the strut, and this region is the main origin for turbulent combustion. , hypersonic propulsion technology has drawn increasing attention from researchers. However, the flame-holding mechanism in the scramjet combustor cannot satisfy the requirement for cruising a long time in near-space [3] because of the short residence time of the mixture remaining in the supersonic flow, which is in the order of milliseconds [4]. This restricts improvement of the aerodynamic performance of hypersonic vehicles. To solve this problem, some fuel injection techniques have been proposed. The strut [5][6][7][8][9][10][11][12][13][14], the cavity [15][16][17][18], the cantilevered ramp [4], the backward facing step [19][20][21] and the combination [22][23][24][25], whose principle is to generate vorticity in the vicinity of the walls of the combustor. The region forming the vorticity, namely the recirculation zone, has low flow velocity. In this region the fuel mixes with the supersonic flow and the mixture can stay in the scramjet combustor for a long time. Zou et al. [6] have used a newly-proposed partiallyresolved numerical simulation procedure to investigate turbulent combustion in a two-dimensional DLR scramjet engine, and the large-scale turbulence was defined by the temporal filtering. Oevermann [7] has used a two-equation k- turbulence model combined with a stretched laminar

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“…The ranges of the angles of attack and sideslip are chosen due to the cantilevered ramp injector being widely employed as an effective fuel injector in the forebody/inlet of the shcramjet engine, 3) and the forebody/inlet would encounter a serious environment when the vehicle is cruising in near-space, 5) i.e., the variance of the incoming boundary condition. Figure 3 shows a comparison of the axial distributions of the maximum injectant mole fraction for different angles of attack, namely ¼ À6 , À4 , À2 , 2 , 4 , 6 and 8 .…”

Section: Resultsmentioning

confidence: 99%

Influences of Angles of Attack and Sideslip on the Flow Field of a Cantilevered Ramp Injector in Supersonic Flows

Huang

Wang

Liu

et al. 2014

Trans. Japan Soc. Aero. S Sci.

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The cantilevered ramp injector has been employed as an effective fuel injection strategy in the shock-induced combustion ramjet engine, and its flow field characteristics have attracted increasing attention. Three-dimensional ReynoldsAveraged Navier-Stokes (RANS) equations coupled with the RNG k-" turbulence model have been employed to investigate the flow field of a cantilevered ramp injector in a freestream with a Mach number of 6.0. The effects of the angles of attack and sideslip on the flow field of a cantilevered ramp injector have been studied, and the predicted axial distribution of the maximum injectant mole fraction shows good agreement with the available experimental data in public literature. The obtained results show that the case with an angle of attack 3 can promote the mixing process between the fuel and air most efficiently in a typical cantilevered ramp injector. However, it cannot prevent the premature ignition of the premixed combustible flow. The mixing process cannot be promoted when the normalized axial distance is larger than 7.55 in cases with different angles of sideslip, and larger angles of sideslip can reduce the effect of premature ignition for the premixed combustible flow.

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

Cited by 56 publications

References 17 publications

Effects of Inflow Mach Number and Step Height on Supersonic Flows over a Backward-Facing Step

Effects of Inflow Mach Number and Step Height on Supersonic Flows over a Backward-Facing Step

Parametric effects on the combustion flow field of a typical strut-based scramjet combustor

Influences of Angles of Attack and Sideslip on the Flow Field of a Cantilevered Ramp Injector in Supersonic Flows

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