Experimental Studies on Piloted Supersonic Combustion Using the Petal Nozzle

Narayanan, Anil K.; Damodaran, K. A.

doi:10.2514/2.5139

Cited by 3 publications

(3 citation statements)

References 13 publications

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“…Whereas the configurations under examination in this and previous studies had planar orientations, as in Fig. 1, they may in fact be viewed as a section of a cylindrically oriented, daisy-or petal-shaped injector, analogous to the petal nozzles or mixers studied by Narayanan and Damodaran, 17 for example.…”

Section: Introductionmentioning

confidence: 94%

Passive Fuel-Air Mixing and Emissions Control Via Lobed Injectors

2004

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Section: Introductionmentioning

confidence: 94%

Passive Fuel-Air Mixing and Emissions Control Via Lobed Injectors

2004

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“…. (13) Here, W and V are the averaged transverse and spanwise velocities respectively, and the vorticity is normalised by U a /λ. Positive value of the vorticity in Fig.…”

Section: The Influence On the Streamwise Vorticity Developmentmentioning

confidence: 99%

“…The most widely application of the lobed mixer is in the exhaust systems of turbofan engines for nozzle noise reduction (5)(6)(7)(8) , as well as for thrust augmentation and infrared radiation suppression in ejector systems (9)(10)(11) . Recently, the mixers are widely exploited in the combustion of scramjets, referred to as the petal nozzles (12,13) or lobed injectors (14)(15)(16) , to improve the molecular mixing of chemical species.…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical study of mixing characteristics of a rectangular lobed mixer in supersonic flow

Feng¹,

Shen²,

Wang

et al. 2015

Aeronaut.j.

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A combined experimental and computational study on a rectangular lobed mixer is performed. A series of simulations based on a steady Reynolds-averaged Navier-Stokes Simulation (RANS) are conducted to analyse the mixing mechanisms of large-scale streamwise structure shed by the trailing edge of lobed mixer, with emphasis being placed on the effect of turbulence modeling and inflow conditions. The simulations are validated in respect of velocity and scalar distribution against the data obtained through Particle Image Velocimetry (PIV) and Nanoparticle-based Planar Laser Scattering (NPLS) technique. The computational results predicted by the SST k -ω turbulence model show better agreement with the experimental data. But the small-scale turbulence structures are not captured accurately by these turbulence models. The convoluted shear layer shed from trailing edge is stretched and rotated by the large-scale streamwise vortices, forming an unstable 'pinching-off' structure, which increases the interfacial area. And at the interface of two streams, a large number of small-scale turbulence structures are formed, which contribute a lot to the mixing enhancement along with the increased interfacial area. The streamwise vorticity decays more rapidly with the decrease of velocity ratio and total pressure ratio of two streams. The scalar thickness which reflects the mixing rate of two streams increases with the decreasing velocity ratio and total pressure ratio.

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Numerical studies on the mixing of CH4 and kerosene injected into a supersonic flow with H2 pilot injection

Sheng-li¹,

Peng-tao²,

Han³

2001

Appl Math Mech

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Abs~act: Two-fluid model and divisional computation techniques were used. The multispecies gas fully N-S equations were solved by upwind TVD scheme. Liquid phase equations were solved by NND scheme. The phases-interaction ODE equations were solved by 2 nd Runge-Kutta approach. The favorable agreement is obtained between computational results and PLIF experimental results of iodized air injected into a supersonic flow. Then, the numerical studies were carried out on the mixing of CH4 and kerosene injected into a supersonic flow with [-12 pilot injection. The results indicate that the penetration of kerosene approaches maximum when it is injected from the second injector. But the kerosene is less diffused compared with the gas fuels. The free droplet region appears in the flow field. The mixing mechanism of CH 4 with H 2 pilot injection is different from that of kerosene. In the staged duct, H 2 can be entrained into both recirculation zones produced by the step and injectors. But CH 4 can only be carried into the recirculation between the injectors. Therefore, initiations of H 2 and CH 4 can occur in those regions. The staged duct is better in enhancing mixing and initiation with H 2 pilot flame.

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Experimental Studies on Piloted Supersonic Combustion Using the Petal Nozzle

Cited by 3 publications

References 13 publications

Passive Fuel-Air Mixing and Emissions Control Via Lobed Injectors

Passive Fuel-Air Mixing and Emissions Control Via Lobed Injectors

Experimental and numerical study of mixing characteristics of a rectangular lobed mixer in supersonic flow

Numerical studies on the mixing of CH4 and kerosene injected into a supersonic flow with H2 pilot injection

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