Aerospace turbofan engines

An aerospace turbofan engine that injects oxygen-enriched gas from an inlet and an afterburner individually or simultaneously, comprising:

• an oxygen-enriched gas injection component;
• a body structure;
• an afterburner middle portion;
• and
• a second afterburner outer ring;
• wherein the oxygen-enriched gas injection component comprises:
• an oxygen-enriched gas three-way pipe;
• an oxygen-enriched gas introduction pipe;
• an oxygen-enriched gas collector;
• and
• an oxygen-enriched gas injection ring;
• wherein the body structure comprises:
• an inlet outer wall;
• a low-pressure compressor;
• a high-pressure compressor;
• a primary combustion chamber;
• a high-pressure turbine;
• a low-pressure turbine;
• a central exhaust nozzle;
• an outer wall of an outer duct;
• a thickened inner wall of the outer duct;
• and
• an outer wall flange of the outer duct;
• wherein the afterburner middle portion comprises:
• a nozzle outer wall;
• a fuel collector;
• and
• a fuel introduction pipe;
• wherein the second afterburner outer ring comprises:
• an acoustic cavity;
• a plurality of screw piles;
• a plurality of nuts;
• a dual collector;
• an annular cover plate;
• an oxygen-enriched gas intake pipe;
• an oxygen-enriched gas three-way pipe;
• an angular cover plate;
• a coolant eduction pipe;
• a spiral groove inner wall;
• a spiral groove outer wall;
• a coolant inflow collector;
• a coolant intake pipe;
• and
• a plurality of baffle plates
• wherein all of components except the body structure, the plurality of screw piles and the plurality of nuts are fixedly welded;
• a plurality of radial holes configured to inject oxygen-enriched gas into the inlet are formed on the oxygen-enriched gas injection ring and uniformly distributed along a circumference of the oxygen-enriched gas injection ring;
• a plurality of oxygen-enriched gas holes are formed on the dual collector and uniformly distributed along a circumference of the dual collector;
• the oxygen-enriched gas is composed of oxygen and water vapor and is produced by catalytic decomposition of hydrogen peroxide with a concentration of 70-79%;
• a plurality of fuel vertical holes are formed on the nozzle outer wall;
• a plurality of fuel oblique holes are formed on the fuel collector;
• the plurality of fuel vertical holes and the plurality of fuel oblique holes are configured to inject kerosene or liquid hydrogen fuel into the afterburner for afterburning;
• and
• a plurality of spiral grooves through which the hydrogen peroxide having a concentration of 70-79% flows for regenerative cooling are milled on an outer surface of the spiral groove inner wall, wherein the spiral groove inner wall is brazed together with the spiral groove outer wall into a whole.

An aerospace turbofan engine that introduces no oxygen-enriched gas, comprising:

• a body structure;
• an afterburner middle portion;
• and
• a first afterburner outer ring;
• wherein
• the first afterburner outer ring uses kerosene or liquid hydrogen fuel as a coolant;
• wherein the body structure comprises:
• an inlet outer wall;
• a low-pressure compressor;
• a high-pressure compressor;
• a primary combustion chamber;
• a high-pressure turbine;
• a low-pressure turbine;
• a central exhaust nozzle;
• an outer wall of an outer duct;
• a thickened inner wall of the outer duct;
• and
• an outer wall flange of the outer duct;
• wherein the afterburner middle portion comprises:
• a nozzle outer wall;
• a fuel collector;
• and
• a fuel introduction pipe;
• wherein the first afterburner outer ring comprises:
• an acoustic cavity;
• a plurality of screw piles;
• a plurality of nuts;
• a coolant outflow collector;
• a coolant eduction pipe;
• a spiral groove inner wall;
• a spiral groove outer wall,
• a coolant inflow collector;
• a coolant introduction pipe;
• and
• a plurality of baffle plates;
• wherein all of components except the body structure, the plurality of screw piles and the plurality of nuts are fixedly welded;
• a plurality of fuel vertical holes are formed on the nozzle outer wall;
• a plurality of fuel oblique holes are formed on the fuel collector;
• the plurality of fuel vertical holes and the plurality of fuel oblique holes are configured to inject kerosene or liquid hydrogen fuel into an afterburner for afterburning;
• and
• a plurality of spiral grooves through which the kerosene or liquid hydrogen fuel flows for regenerative cooling are milled on an outer surface of the spiral groove inner wall, wherein the spiral groove inner wall is brazed together with the spiral groove outer wall into a whole.

An aerospace turbofan engine that introduces oxygen-enriched gas from an afterburner, comprising:

• a body structure;
• an afterburner middle portion;
• and
• a second afterburner outer ring;
• wherein the body structure comprises:
• an inlet outer wall;
• a low-pressure compressor;
• a high-pressure compressor;
• a primary combustion chamber;
• a high-pressure turbine;
• a low-pressure turbine;
• a central exhaust nozzle;
• an outer wall of an outer duct;
• a thickened inner wall of the outer duct;
• and
• an outer wall flange of the outer duct;
• wherein the afterburner middle portion comprises:
• a nozzle outer wall;
• a fuel collector;
• and
• a fuel introduction pipe;
• wherein the second afterburner outer ring comprises:
• an acoustic cavity;
• a plurality of screw piles;
• a plurality of nuts;
• a dual collector;
• an annular cover plate;
• an oxygen-enriched gas intake pipe;
• an oxygen-enriched gas three-way pipe;
• an angular cover plate;
• a coolant eduction pipe;
• a spiral groove inner wall;
• a spiral groove outer wall;
• a coolant inflow collector;
• a coolant intake pipe;
• and
• a plurality of baffle plates
• wherein all of components except the body structure, the plurality of screw piles and the plurality of nuts are fixedly welded;
• a plurality of oxygen-enriched gas holes are formed on the dual collector and uniformly distributed along a circumference of the dual collector;
• the oxygen-enriched gas is composed of oxygen and water vapor and is produced by catalytic decomposition of hydrogen peroxide with a concentration of 70-79%;
• a plurality of fuel vertical holes are formed on the nozzle outer wall;
• a plurality of fuel oblique holes are formed on the fuel collector;
• the plurality of fuel vertical holes and the plurality of fuel oblique holes are configured to inject kerosene or liquid hydrogen fuel into the afterburner for afterburning;
• and
• a plurality of spiral grooves through which the hydrogen peroxide having a concentration of 70-79% flows for regenerative cooling are milled on an outer surface of the spiral groove inner wall, wherein the spiral groove inner wall is brazed together with the spiral groove outer wall into a whole.