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Combustion enhancement in rearward step based scramjet combustor by air injection at step base

Propulsion and Power Research 2021年第3期10卷 224-234页

作者： Amit Thakur nishanth thillai Amritesh Sinha Mechanical Engineering PES UniversityIndia Institute for Aerospace Studies University of TorontoCanada Aerodynamics Energetics and PropulsionISAE SupaeroFrance

Numerical simulations were performed to model the non-reacting and reacting flow behind a rearward step flameholder in Mach 1.6 supersonic flow with fuel injection at the step *** combustor geometry was based on the University of Florida scramjet experimental *** was modeled using k-u shear stress transport(SST),laminar flamelet was used for combustion *** static pressure showed good agreement with experimental data for non-reacting and reacting *** non-reacting flow,dummy fuel helium mole fraction distribution in the recirculation region behind the step was validated with planar laser induced fluorescence(PLIF)images in *** improve the combustion characteristics,air was injected in tandem with hydrogen at step base using various *** all fuel injection as baseline,the case with 2 air jets around each fuel jet and air injected at 2 times the stagnation pressure of fuel showed the most improvement compared to other *** was most effective in reducing the local fuel richness,shortening the flame length and increasing combustion efficiency.

关键词： Step flameholder Scramjet combustor Local equivalence ratio Air injection Combustion efficiency

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Analysis of flow-field in a dual mode ramjet combustor with boundary layer bleed in isolator

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Propulsion and Power Research 2021年第1期10卷 37-47页

作者： nishanth thillai Amit Thakur Srikrishnateja K. Dharani J. Department of Mechanical Engineering PES UniversityBangaloreIndia

A two-dimensional Reynolds averaged Navier Stokes(RANS)simulation of a dual mode ramjet(DMRJ)combustor is performed,modeling the University of Michigan dual-mode combustor experimental setup operating in reacting mode with different equivalence ratios(4).The simulations are carried out using a k-u SST turbulence model and a steady diffusion flamelet model for non-premixed *** enters the isolator at Mach 2.2,stagnation pressure and temperature of 549.2 kPa and 1400 K *** is injected transverse to the flow direction and upstream of the cavity flame holder to simulate ramjet(4 Z 0.29)and scramjet(4 Z 0.19)modes of *** static pressure plots are used to validate numerical results against experimental *** of flow separation in ramjet mode due to the presence of a shock train in the isolator is carried out by means of numerical Schlieren images overlapped with contours of negative axial velocity,showing the effects of shock wave boundary layer interaction(SWBLI).Active control through wall normal boundary layer bleed in the separated flow region is implemented,which weakens the shock train and moves it downstream closer to the *** results in an improved stagnation pressure recovery in ramjet mode,with a marginal increase in combustion efficiency.

关键词： Dual mode ramjet Scramjet combustor Shock wave boundary layer interaction Boundary-layer bleed Flamelet combustion model

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