TURBO-JET ENGINE AND CONTROL METHOD THEREOF Russian patent published in 2018 - IPC F02C7/16 F02C3/30 F02C3/32 F02C9/28 F02K3/00 

FIELD: engines and pumps.

SUBSTANCE: turbo-jet engine consisting of an inlet device, a compressor, a main combustion chamber, a single-stage turbine, a gas ejector, the high-pressure channel of which is connected on one side with the compressor through the main combustion chamber, and on the other side – with the turbine through a mixing chamber, the low pressure channel on one side is connected to the atmosphere through the inlet device, and on the other side – with the turbine through the mixing chamber, a mixing heat exchanger located before the compressor, an afterburner combustion chamber, an outlet device. In the high and low pressures channels of the gas ejector at the entrance to the mixing chamber there are nozzle assemblies, in the low-pressure channel of the gas ejector there is a damper, the turbine blades are cooled by air, to which the fuel and water are mixed. Method for the turbo-jet engine control is to use the control law n_spec = const (constant specific speed of the compressor) within the entire operational range of the aircraft, as well as – the hyperforsed mode – an increase of the engine thrust due to the supply of a liquid (water, liquid air, liquid oxygen, kerosene in an amount not exceeding 3 % of the air flow rate) to the compressor inlet at flight speeds of more than four Mach numbers. Use of turbo-jet engines will let increase speed and altitude of the booster aircraft flight up to M ~ 7 and H ~ 40 km, at which the first stage of the Space and Missile System becomes unnecessary.

EFFECT: this will increase the power of the second stage of the Space and Missile System by times and, accordingly, increase the payload by dozens of times.

6 cl, 7 dwg