Hyper Afterburner Jet Engines

This paper introduces a thrust augmentation method for super- and hypersonic jet engines by means of applying water at the engine intake. This method expands the use of jet engines with subsonic combustion, allowing velocities up to Mach 8 and altitude up to 45 km. At velocities higher than 3–4 Mach, stagnation temperature of the air is getting higher than the critical temperature of water, which makes the existence of water at the gas turbine engine intake impossible. Water vapour as a working medium of a jet engine creates the so-called inner thermodynamic circle. This phenomenon defines the physics of the thrust augmentation method proposed. The author discusses three variants of hyper afterburner application: hyper afterburner turbojet, hyper afterburner ramjet, and hyper afterburner turbo ejecting engine. The presented basic specifications of the hyper afterburner engines qualitatively differ from those of their prototypes (engines without the hyper afterburner thrust augmentation function). The proposed thrust augmentation method of jet engines is of a special interest for the aerospace field, particularly, for creating air launch systems. It is shown that the application of hyper afterburner in turbo ejecting engines can increase velocity and altitude of the launch aircraft up to Mach 7 and 40 km respectively, thus opening new avenues in space exploration.

Modeling of the Potential Pit and Force Field to Limit the Motion of the Plasma Particles

Paper is devoted to development of the potential barrier model allowing to take into account the interaction between elastic reflection of particles and plasmatron walls. The coaxial magneto-plasma accelerator which has been put into practice is considered.Plasma clot change of speed and weight depending on the coordinate determined by both power characteristics and gas dynamic regularities of hypersonic jet currents in the cylindrical channel was investigated in the accelerator. Potential function and force field type modeling spatial restriction of plasma particles scattering is presented. Dynamics ofcharged particles distribution in electromagnetic field andthe plot of energy balance taking into account the erosion of channel walls have been presented. The developed model of the coaxial magneto-plasma accelerator taking into account an erosion caused by particles distribution on a low-frequency helixhas been shown.Low-frequency helixpath motion is presented as superposition of longitudinal and transverse motions. Differential equations were solved using the fourth-order Runge-Kutta fixed-step method.

Investigation of Ultradispersed Powders FexOy Obtained in the Electric Discharge Plasma

The paper shows the iron oxide powder production in the hypersonic jet of electro discharge plasma generated by a coaxial magnetoplasma accelerator with steel electrodes. The influence of gaseous atmosphere parameters has been investigated by carrying out experiments in normal atmospheric conditions and with the introduction of additional oxidant into the plasma discharge. Studies of the structure of synthesized powders and their magnetic properties have been carried out. It has been found that by introducing of additional oxidant it is possible to regulate the phase composition in the direction of increasing the yield of magnetite phase. Specific saturation magnetization decreases with decreasing of the magnetic nanoparticle sizes.