Numerical simulation of interaction directional shock wave and transverse gas get blown into supersonic flow


Аuthors

Snazin A. A., Sevchenko V. I.*

Mlitary spaсe Aсademy named after A.F. Mozhaisky, Saint Petersburg, Russia

*e-mail: vka@mil.ru

Abstract

Efficient interaction of blown gas jets with supersonic flow is one of the topical issues, to which a large number of researches and developments are devoted. Blowing jets into supersonic flow, is a common method of increasing the efficiency of gas mixing and influencing the shock-wave structure of the flow. Studies show that transverse gas jet blowing is one of the traditional and reliable methods providing fast gas mixing and high penetration of the jet into the supersonic transverse flow [1-3]. The object of study is a channel with dimensions l = 180mm, h = 30mm and w = 80mm, where at a distance b = 80mm from the inlet there is a gas jet blowout point. At a distance n = b /2 there is a ramp of length m = 5mm and 10mm, and angle of inclination β = 30o. The impinging supersonic flow is given by M∞ = 4.2, static pressure P∞ = 1200 Pa, and static temperature T∞ = 227 K. The Mach number of the blown jet is Mj  =  1, the total temperature Tj = 293 K, and the ratio of jet pressure to static pressure Pj/P∞ = 0.16 [4]. The jet blowing condition was fixing throughout the calculation. The sticking and adiabatic wall condition are imposed on the lower and upper walls of the channel. The model was solved using the Reynolds-averaged Navier-Stokes equations, which were closed by the SST k-ω turbulence model equation. [5] The mesh topology was constructed to resolve near-wall flows and turbulent structures in areas of large gradients of gasdynamic parameters. In near-wall regions, the dimensionless layer height y+ < 1. The total number of finite element mesh cells is 1.6×106 elements. Half of the channel was modeled and the symmetry condition was imposed on the interface plane. As a result of this research, a picture of shock-wave structures was obtained and a numerical study of the interaction between a falling compaction jump and a transversely blown gas jet was carried out. The size of the ledge was varied in order to investigate its effect on the supersonic flow in the channel. As a result, it is obtained that increasing the size of the ledge has a great effect on the flow structure in the channel. In this case, the falling compaction jump formed in front of the blown gas jet is shifted closer to the channel entrance. Considering this tendency, it can be assumed that at a sufficiently large pj/p∞ ratio, the falling compaction jump can be displaced to the channel entrance, since the increase of the ledge leads to greater compression of the supersonic flow in the channel. Further increase in the size of the ledge can lead to "locking" of the channel, which in turn is an unfavorable condition for mixing of the blown jet gas and the surging flow. Also, the shock-wave structure near the blown jet changes, the zones of wall layer detachment increase with increasing intensity of the compaction jump formed by the ledge.

Keywords:

blown gas jet, supersonic flow, mesh adaptation, shock wave

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