A Review and Progress of Multiphase Flows in Atmospheric and low Pressure Plasma Spray Advanced Coating

This paper presents the results of mathematical modeling of the interaction of supersonic twin jet flow with a flat obstacle. The influence of the distance between the nozzles on the shock-wave structure of the gas flow for the Mach numbers 4.7 on the nozzle exit are studied. In the studies, the distance from the nozzle exit to obstacle was 0.5 meters, the distance between the nozzles varied from 0.1 to 4.0 nozzle exit diameters. It was found that in the range of distances between nozzles 0.1-1 nozzle exit diameters, the shock-wave structure of the flow and pressure distribution along the obstacle are similar. With an increase in the distance between the nozzles of more than 1.0 nozzle exit diameters the maximum pressure on the obstacle is two times less. For distance 4.0 of nozzle exit dimeter in the region of the triple configuration of shock waves oscillations are observed.

Numerical investigation of the interaction of a single supersonic jet with a flat obstacle

Reconstruction of the supersonic underexpanded jet flow parameters by the velocity and total pressure fields measurements results

https://iopscience.iop.org/article/10.1088/1757-899X/597/1/012076/pdf

Mathematical modelling of a single supersonic jet impingement with a flat obstacle

The article discusses the issues of computational-experimental research of intersecting supersonic flooded jets interaction features at various values of their velocity heads ratio. The influence of the jets mutual position on the change in the resulting angle of the high enthalpy flow velocity vector is estimated. Experimental data are compared with the results of numerical simulations using various turbulence models. For calculations, we used RANS-models of turbulence such as Spalart-Almaras, k-ω Standard and k-e Standard. Recommendations on the use of these models to solve such problems are developed. The research results can be used to analyze the effectiveness of injection systems in promising power plants.

Calculation and experimental study of supersonic flooded jets interaction features

The paper presents an experimental studies overview of the free supersonic jet flow structure Ma = 1.0, Npr = 5, exhausting from a convergent profiled nozzle into a ambient space. Also was observed the jets in the presence of artificial streamwise vortices created by chevrons and microjets located on the nozzle exit. The technique of experimental investigation, schlieren-photographs and schemes of supersonic jets, and Pitot pressure distributions, are presented. A significant effect of vortex generators on the shock-wave structure of the flow is shown.

/pdf/investigation-of-supersonic-jets-shock-wave-structure-8wnoponuiy.pdf

Investigation of supersonic jets shock-wave structure

The flow structure behind the Mach disk in the first cell of free supersonic underexpanded jets exhuasting from nozzles of different geometric Mach numbers at nozzle exit was examined. Flow visualization pictures obtained with the help of the direct-shadow method, the schlieren method, and the laser sheet technique are presented. It is shown that, in the subsonic zone behind the Mach disk of free supersonic non-isobaric jets exhausting from conical nozzles with Ma = 2.5 and Ma = 3 in a wide range of gas-dynamic regimes, the shape of the Mach disk corresponds to that of a normal shock, and this shape undergoes no deformation, i.e. no recirculation region is registered behind the Mach disk. Experiments using the contactless panoramic laser PIV method were performed. From measured fields of flow velocity at outflow regimes of free supersonic jet with Npr = 8.5 and Ma = 1.5, the non-occurrence of flow recirculation zone behind the Mach disk was demonstrated.

Flow structure behind the Mach disk in supersonic non-isobaric jet

A method of calculating the pressure from the velocity field measurement data by using the PIV contactless technique is considered in the work. The pressure distribution was calculated by using the...

I. N. Kavun

Papers

Investigation of supersonic jets shock-wave structure

Flow structure behind the Mach disk in supersonic non-isobaric jet

Determination of the gas-dynamic flow parameters by the PIV measurements

Pulsations parameters in the mixing layer of high-speed subsonic jet

Study gas-dynamic structure of supersonic non-isobaric jets