SMALL-SIZE BYPASS TURBOJET ENGINE Russian patent published in 2024 - IPC F02K3/06 F02C7/06 F02C7/16 

FIELD: engine building.

SUBSTANCE: invention relates to small-size bypass turbojet engines with lubrication and cooling system of engine parts. Small-size bypass turbojet engine comprises gas generator with fuel system, combustion chamber and with a high-pressure turbine impeller and a high-pressure centrifugal compressor with a pressure pipeline installed on the hollow rotor, a fan with a drive device, low pressure turbine with a shaft located in the rotor cavity of the gas generator and mechanically connected to the fan drive, and an internal circuit with a nozzle and a flow section, as well as a lubrication and cooling system of engine parts with a lubricant supply source, a cooling heat exchanger, a high-pressure air supply channel connected to the high-pressure compressor discharge pipeline, and cooling medium supply channels, wherein high-pressure compressor is installed in housing with formation of inner cavity, gas generator rotor and low-pressure turbine shaft are installed in the housing on the front and rear bearing supports connected to the cooling medium supply channels, high-pressure turbine impeller is installed in the housing with formation of pre-disk and rear-disk cavities connected to the high-pressure air supply channel and to the flow part of the internal circuit. Fan drive is combined with the low-pressure turbine shaft front bearing support and is made in the form of a planetary reduction gear with an autonomous lubrication system, engine parts lubrication and cooling system is equipped with a mixer, connected by inputs to the inner cavity of the housing and to the lubricant supply source, and by the output to the cooling medium supply channels, and the cooling heat exchanger is connected to the fuel system of the gas generator and is placed in the inner cavity of the housing communicated with the high-pressure air supply channel, wherein one of the cooling medium supply channels is connected in series to the gas generator rotor front and rear bearing supports and the high-pressure turbine pre-disc cavity, and the other coolant supply channel sequentially communicates the rear bearing support of the gas generator rotor with the rear bearing support of the low-pressure turbine shaft and the rear cavity of the high-pressure turbine.

EFFECT: use of a cooling heat exchanger in the proposed system of lubrication and cooling of engine parts allows for preheating of fuel before it enters the combustion chamber due to which engine efficiency and reliability of its operation are increased.

2 cl, 4 dwg