CN112160847A - Bimodal full-speed full-adaptive variable-cycle rotary jet type aviation jet engine - Google Patents
Bimodal full-speed full-adaptive variable-cycle rotary jet type aviation jet engine Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/224—Heating fuel before feeding to the burner
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infra-red radiation suppressors
- F02K1/825—Infra-red radiation suppressors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/52—Toroidal combustion chambers
Abstract
The bimodal full-speed fully-adaptive variable-circulation rotary jet type aviation jet engine comprises two parts, namely a thrust jet engine and a bimodal air supercharger, which are separated, wherein the thrust jet engine adopts a rotary jet structure as a basic power device, and adopts an air axial flow power generation technology to solve the problem of random power generation, and the bimodal air supercharger adopts a bimodal mode to intake air: the air inlet mode adopts an electric pressurization mode in a low-speed state, the air inlet mode adopts a stamping mode in a high-speed state, the two modes are automatically switched in work, and the generated high-pressure air is conveyed to a thrust jet and is mixed with fuel for combustion to finally generate thrust. The novel and advanced technology and scientific and reasonable structural design enable the invention to comprehensively overcome all the defects and shortcomings of the existing like products such as complex structure, high manufacturing difficulty, severe material selection, failure of the compressor at a certain high speed and the like, and simultaneously have the excellent characteristics of ultrahigh thermal efficiency, low noise, excellent controllability and instantaneous response, easy manufacturing, low cost, non-severe material selection, rapid starting and the like.
Description
The technical field is as follows. The invention belongs to an aviation jet engine, and relates to the technical field of gas rotary jet aviation jet engines, permanent magnet power generation and ram air intake.
Background of the invention is described. The prior gas power turbine aviation jet engine and the rotary spray type variable cycle aviation jet engine (patent number 201810092409.9) which is granted by the inventor of the prior invention patent have a common characteristic that the air participating in combustion is continuously pressurized by a plurality of stages of turbofan and then enters a combustion chamber to participate in combustion, and the result is that: with the further increase of the speed of the airplane, the force of high-speed airflow impacting a turbofan blade is continuously enhanced, the kinetic energy of air is continuously converted into heat energy, the heat energy enables the temperature of air before entering a combustion chamber to be greatly increased, the effective oxygen content in the air is correspondingly and greatly reduced with higher air temperature, so that the air and fuel are difficult to combust, the chemical energy in the fuel cannot be effectively released, the airplane in flight cannot obtain additional energy from the fuel, the thrust of an engine is reduced to zero, and the speed of the airplane cannot be continuously increased, so that the speed of the aero-jet engine adopting the mechanical air compression mode of the air compressor has a limit value. Moreover, it is obvious that the mechanical air compression mode can additionally consume energy, which is extremely not beneficial to the improvement of the thermal efficiency of the aero-jet engine, in order to overcome the defect of the aero-engine, people invent a ramjet engine which does not need mechanical air compression, but the ramjet engine can be started to play a role only when the flying speed of an aircraft reaches a certain degree, and basically cannot be manually controlled, and is mostly used for rocket and missile flight, in order to overcome the defect of the ramjet engine, people think that the gas turbine aero-jet engine and the ramjet engine are combined to implement a dual mode, invent a sub-combustion ramjet engine and a super-combustion ramjet engine, and call the sub-combustion ramjet engine and the super-combustion ramjet engine as a human sixth generation aero-engine (called a six generation machine for short) to represent the future of the aero-. Obviously, the two engines have extremely complex structures, great difficulty, poor operability and practicability, and are not popularized and applied so far.
Before this, the inventor has obtained the patent of the invention of the jet-propelled gas jet engine with variable cycle of jet-propelled jet engine with jet-propelled gas (patent number 201810092409.9), which has great technical progress to overcome various inherent disadvantages of the existing jet-propelled gas turbine jet engine, but has no substantial improvement on the air intake mode of the engine, and we know that the technical progress is endless and the innovation is endless.
The invention relates to a method for processing a semiconductor chip. In order to overcome all the defects of a human 'six-generation machine' in human ideal, provide a gas aviation jet engine which has the excellent characteristics of free adaptability to various cruising states in flight, excellent controllability and transient response, relatively simple structure, relatively low manufacturing difficulty, low cost, low noise, relatively ultrahigh thermal efficiency, relatively less strict manufacturing materials, relatively less strict applied fuel, relatively environmental protection and the like, and can be freely controlled like the prior piston engine, the invention provides a bimodal full-speed fully-adaptive variable-cycle rotary jet aviation jet engine, and the technical scheme is as follows: the engine is integrally divided into an engine air jet thrust part (which can be called a thrust jet) and an air intake combustion part (which can be called a bimodal air supercharger) which are separated from each other, the bimodal air supercharger specially producing high-pressure air conveys the high-pressure air for mixing and combusting with fuel to the thrust jet through an air conveying pipeline, and the thrust jet specially produces the thrust required by the aircraft engine. For a thrust jet engine, firstly, an existing gas turbine power device is replaced by a high-efficiency and scientific and reasonable-structure gas rotary jet mechanism, then the existing worm shaft-connected mechanical power generation technology is replaced by the same high-efficiency and scientific and reasonable-structure gas axial flow power generation technology to solve the random power generation problem, for a dual-mode air supercharger, a traditional and single air inlet mode of replacing an existing series multi-stage compressor is formed by connecting a plurality of electric centrifuges in a parallel connection mode and a stamping air inlet mode in parallel, and the dual-mode air supercharger adopts a dual-mode to inlet air: the air inlet is carried out in an electric pressurization mode in a low-speed state, the air inlet is carried out in a stamping mode in a high-speed state, and the two modes are automatically switched during working; in the thrust jet plane, combustion air delivered by the dual-mode air supercharger is mixed with fuel and combusted to generate high-pressure mixed gas and release chemical energy, the chemical energy is efficiently converted into mechanical energy by the gas rotary spraying mechanism, the gas rotary spraying mechanism drives a thrust jet plane spindle (namely an aircraft engine spindle) to rotate, and the rotating aircraft engine spindle drives a turbofan in a gas axial flow power generation device and an additional turbofan arranged on the aircraft engine spindle to rotate together; inside the air duct in the thrust jet machine, outside air enters the air duct from a thrust air inlet pipe at one end of the air duct, the air is continuously pressurized by a multi-stage turbofan such as a self turbofan, an additional turbofan and an axial flow generating device turbofan of a rotary jet mechanism, and finally rushes out of the air duct from a tail nozzle at the other end of the air duct at a high speed, and the reaction force generated by the high-speed rushed mixed gas is the forward huge thrust generated by the device.
The invention adopts a specific technical scheme for solving the technical problem. The bimodal full-speed fully-adaptive variable-circulation rotary jet type aviation jet engine comprises a thrust jet, a bimodal air supercharger, a fuel storage box, a storage battery pack and a fuel delivery pump, wherein the fuel storage box is provided with a fuel output flange interface, the thrust jet is provided with a combustion air input 1 st flange interface, a fuel heat exchange front input flange interface, a fuel heat exchange rear output flange interface, a combustion air input 2 nd flange interface and a fuel heat exchange rear input flange interface which are 5 external connecting parts, and the fuel heat exchange rear input flange interface and a fuel delivery regulating valve outlet end flange are fixedly connected together through bolts and nuts; a plurality of high-pressure air output flange interfaces are arranged on the bimodal air supercharger, namely 2 high-pressure air output 1 st flange interfaces and 2 high-pressure air output 2 nd flange interfaces are externally connected with the flange interfaces, and the high-pressure air output 1 st flange interfaces and the high-pressure air output 2 nd flange interfaces are respectively and fixedly connected with 2 valves, namely a combustion air 1 st regulating valve and a combustion air 2 nd regulating valve, through bolts and nuts; the fuel output flange interface on the fuel storage box is fixedly connected with the inlet end flange of the fuel delivery pump, the outlet end flange of the fuel delivery pump is communicated with the inlet end flange interface before fuel heat exchange by the fuel delivery pipe without heat exchange, the outlet end flange interface after the fuel heat exchange is communicated with the inlet end of the fuel delivery regulating valve by the fuel delivery pipe after the heat exchange, the outlet end of a 2 nd regulating valve of combustion air is communicated with the 1 st flange interface of the combustion air input by a 2 nd air delivery pipe, the outlet end of the 1 st regulating valve of the combustion air is communicated with the 2 nd flange interface of the combustion air input by the 1 st air delivery pipe, and the storage battery is provided with a conductive wire which is connected with the.
The bimodal full-speed fully-adaptive variable-cycle jet-type aviation jet engine is characterized in that the basic structure of the jet thrust engine is as follows: the thrust jet comprises a thrust air inlet pipe and a tail jet pipe, wherein the thrust air inlet pipe positioned at the foremost end of the thrust jet is provided with a thrust air inlet pipe connecting flange, a power generation unit is arranged behind the thrust air inlet pipe and is abutted against the thrust air inlet pipe, the power generation unit is provided with a power generation unit front connecting flange and a power generation unit rear connecting flange, and the power generation unit front connecting flange and the thrust air inlet pipe connecting flange are fixedly connected together by a plurality of thrust jet 1 st set of bolt nuts; the front case is provided with a front case front connecting flange and a front case rear connecting flange on the back of the power generation unit and is abutted against the power generation unit, and the front case front connecting flange and the power generation unit rear connecting flange are fixedly connected together by a plurality of thrust jet machine 2 nd set of bolts and nuts; the power unit is provided with a power unit front connecting flange and a power unit rear connecting flange on the rear surface of the front case and is abutted against the front case, and the power unit front connecting flange and the front case rear connecting flange are fixedly connected together by a plurality of thrust jet machine 3 rd sets of bolts and nuts; the combustion unit is provided with a combustion unit front connecting flange and a combustion unit rear connecting flange on the rear surface of the power unit and is abutted against the power unit, and the combustion unit front connecting flange and the power unit rear connecting flange are fixedly connected together by a plurality of thrust jet machine 4 th set of bolts and nuts; the rear part of the combustion unit is abutted against the combustion unit, and a raw material preparation unit front connecting flange, a raw material preparation unit rear connecting flange and a plurality of combustion air input flange interfaces are arranged on the combustion unit, namely a combustion air input 1 st flange interface and a combustion air input 2 nd flange interface, and the raw material preparation unit front connecting flange and the combustion unit rear connecting flange are fixedly connected together by a plurality of thrust jet machine 5 th set of bolts and nuts; the fuel preparation unit is provided with a fuel preparation unit front connecting flange, a fuel preparation unit rear connecting flange and a fuel heat exchange rear input flange interface on the rear part of the raw material preparation unit and is abutted against the raw material preparation unit, and the fuel preparation unit front connecting flange and the raw material preparation unit rear connecting flange are fixedly connected together by a plurality of thrust jet machine 6 th sets of bolts and nuts; the composite rear case is provided with 4 accessories, namely a composite rear case front connecting flange, a composite rear case rear connecting flange, a fuel heat exchange front input flange interface and a fuel heat exchange rear output flange interface, on the upper surface of the composite rear case, and the composite rear case front connecting flange and the fuel preparation unit rear connecting flange are fixedly connected together by a plurality of thrust jet engine 7 th sets of bolts and nuts; the tail nozzle 33 with a tail nozzle connecting flange is arranged on the rear surface of the composite rear casing and is abutted against the composite rear casing, and the tail nozzle connecting flange and the rear connecting flange of the composite rear casing are fixedly connected together by a plurality of 8 th sets of bolts and nuts; a main shaft including the main shaft and an auxiliary part surrounding the main shaft are arranged in the thrust jet main body, and an additional turbofan is fixedly arranged on the main shaft and positioned in the raw material preparation unit; a plurality of penetrating rods respectively penetrate through 16 flange holes corresponding to the flanges on the front end of each penetrating rod and lock the 16 flanges at the two ends of each penetrating rod through a thrust air inlet pipe connecting flange, a front connecting flange, a power generation unit rear connecting flange, a front casing front connecting flange, a front casing rear connecting flange, a power unit rear connecting flange, a combustion unit front connecting flange, a combustion unit rear connecting flange, a raw material preparation unit front connecting flange, a raw material preparation unit rear connecting flange, a fuel preparation unit front connecting flange, a fuel preparation unit rear connecting flange, a composite rear casing front connecting flange, a composite rear casing rear connecting flange and a tail nozzle connecting flange, wherein the penetrating rods are formed by a thrust jet machine 1 sleeve bolt nut, a thrust jet machine 2 sleeve bolt nut, a thrust jet machine 3 sleeve bolt nut, a thrust jet machine 4 sleeve bolt nut, and a thrust jet machine 4 sleeve bolt nut, The 5 th set of bolt and nut of the thrust jet, the 6 th set of bolt and nut of the thrust jet, the 7 th set of bolt and nut of the thrust jet and the 8 th set of bolt and nut of the thrust jet are arranged in a line which is staggered and arranged at intervals.
The bimodal full-speed fully-adaptive variable-cycle jet aero-jet engine is characterized in that the bimodal air supercharger is basically structurally characterized in that: the dual-mode air supercharger comprises a high-pressure air storage tank, a spherical communication and an air gathering hopper, wherein the spherical communication comprises a spherical communication main air inlet flange interface and a spherical communication main air outlet flange interface which are positioned in opposite directions and have the center line on one diameter, the central line of the air outlet interfaces is in the same plane vertical to the diameter, namely the air outlet interfaces of a first branch are communicated in a spherical mode, the air outlet interfaces of a second branch are communicated in a spherical mode, the air outlet interfaces of a third branch are communicated in a spherical mode, the air outlet interfaces of a fourth branch are communicated in a spherical mode, the air outlet interfaces of a third branch are communicated in a spherical mode, the air outlet interfaces of a fourth branch are communicated in a spherical mode, the air collecting hopper comprises an air collecting hopper air outlet flange interface and an air collecting hopper air inlet straight cylinder part, the main body in the middle of the air collecting hopper is a conical; the high-pressure air storage tank is closed, two end faces of the high-pressure air storage tank are respectively an air inlet end face and an air outlet end face, the air outlet end face is provided with a plurality of high-pressure air output interfaces, namely a high-pressure air output flange 1 and a high-pressure air output flange 2, a high-pressure air storage tank fastening flange is arranged on the periphery of the air inlet end face along the circumferential side face of the high-pressure air storage tank, the central part of the upper surface of the high-pressure air storage tank main air inlet flange interface is provided with a high-pressure air storage tank main air inlet flange interface, the upper surface of the high-pressure air storage tank main air inlet flange interface is provided with an outlet end of a main air inlet one; a plurality of branch air inlet interfaces are arranged around the main air inlet flange interface of the high-pressure air storage tank, namely, the 1 st branch air inlet flange interface of the high-pressure air storage tank, the 2 nd branch air inlet flange interface of the high-pressure air storage tank, the 3 rd branch air inlet flange interface of the high-pressure air storage tank and the 4 th branch air inlet flange interface of the high-pressure air storage tank share the 4-branch air inlet flange interface, the 1 st electric centrifugal air supercharger air outlet flange interface, the 2 nd electric centrifugal air supercharger air outlet flange interface, the 3 rd electric centrifugal air supercharger air outlet flange interface and the 4 th electric centrifugal air supercharger air outlet flange interface are respectively and fixedly arranged on the 4-branch air inlet flange interfaces through bolts and nuts, and the 1 st electric centrifugal air supercharger air inlet flange interface, the 2 nd electric centrifugal air supercharger air inlet flange interface, the 3 rd electric centrifugal air supercharger air inlet flange, Outlet end flanges of 4 branch check valves including a 1 st branch check valve, a 2 nd branch check valve, a 3 rd branch check valve and a 4 th branch check valve are respectively installed and fixed on the 4 th electric centrifugal air supercharger inlet flange interface and the 4 th flange interface through bolts and nuts, and inlet end flanges of the 4 branch check valves are respectively and fixedly connected with a 1 st branch outlet flange interface, a 2 nd branch outlet flange interface, a 3 rd branch outlet flange interface and a 4 th branch outlet flange interface and the 4 th branch outlet flange interface through bolts and nuts; the spherical communicating main air inlet flange interface is fixed with the air outlet flange interface of the air gathering hopper through bolts and nuts; the supporting and protecting sleeve with a plurality of inspection windows arranged between the circumferential side walls is cylindrical in shape, one end of the supporting and protecting sleeve is fixed with the straight cylinder part of the air inlet of the air gathering hopper through a 2 nd set of bolt and nut 42 of the supercharger, and the other end of the supporting and protecting sleeve is fixed with the fastening flange of the high-pressure air storage tank through a 1 st set of bolt and nut of the supercharger.
The thrust jet engine is characterized in that the thrust air inlet pipe is basically structurally characterized in that: the thrust intake pipe is by big straight section of thick bamboo intake pipe, round platform shape intake pipe, little straight section of thick bamboo intake pipe and thrust intake pipe special connecting flange altogether 4 parts constitute, its big open end of round platform shape intake pipe is in the same place with the export end fixed connection of big straight section of thick bamboo intake pipe, its little open end is in the same place with the import end fixed connection of little straight section of thick bamboo intake pipe, near the export end port of little straight section of thick bamboo intake pipe installation be fixed with thrust intake pipe special connecting flange, big straight section of thick bamboo intake pipe, round platform shape intake pipe, little straight section of thick bamboo intake pipe altogether 4 parts possess the same central axis, by big straight section of thick bamboo intake pipe, round platform shape intake pipe, little straight section of thick bamboo intake pipe altogether 3.
The thrust jet engine is characterized in that the power generation unit is basically structurally characterized in that: the cylindrical power generation unit shell of the power generation unit is respectively provided and fixed with a power generation unit front connecting flange and a power generation unit rear connecting flange at two ends, an annular electromagnetic coil stator which is provided with a concave groove in the middle and is arranged and fixed on the inner wall surface of the power generation unit shell is arranged inside the power generation unit shell, three sides of the concave groove in the electromagnetic coil stator surround an annular permanent magnet rotor, the permanent magnet rotor is fixed on a rotor support chassis, a certain gap is reserved between the electromagnetic coil stator and the permanent magnet rotor, and when the permanent magnet rotor rotates in the electromagnetic coil stator, an electromagnetic coil in the electromagnetic coil stator always cuts the magnetic line of force of a magnetic field where the permanent magnet rotor; the rotor support chassis is internally provided with a tip pressing disk and a plurality of adjustable spoke supports, two ends of each adjustable spoke support positioned between the tip pressing disk and the rotor support chassis are respectively fixed on the inner wall surface of the rotor support chassis and the outer wall surface of the tip pressing disk, the pressure tip disk is internally provided with a power generation turbofan chassis and a plurality of power generation turbofan blades, the head part of each power generation turbofan blade is installed and fixed on the inner wall surface of the tip pressing disk, the root part of each blade is installed and fixed on the outer surface of the power generation turbofan chassis, the inner circumferential wall surface of the hollow cylindrical power generation turbofan chassis is provided with a key slot parallel to the central axis direction of the power generation turbofan chassis, namely a key slot of the power generation turbofan chassis, 6 parts of a power generation unit shell, an electromagnetic coil stator, a permanent magnet rotor, the rotor support chassis, the tip pressing disk and the power generation turbofan chassis share a common central axis, and the central symmetrical surfaces on the flat strip adjustable spoke supports parallel to the surface with a larger area are all parallel through the central symmetrical surfaces Passing through the common central axis.
The thrust jet engine is characterized in that the front casing is basically structurally characterized in that: the front cartridge receiver comprises a front cartridge receiver shell and a front cartridge receiver bearing sleeve, wherein two ports on the outer side surface of the front cartridge receiver shell are respectively and fixedly provided with annular sheet inner side surfaces of a rear end panel of the front cartridge receiver and an inner side surface of a front end panel of the front cartridge receiver, and the outer side surfaces of the front end panel of the front cartridge receiver and an outer ring of the rear end panel of the front cartridge receiver are respectively and fixedly provided with a front cartridge receiver front connecting flange and a front cartridge receiver rear connecting flange; the rear end panel of the front casing and the front end panel of the front casing are connected and reinforced into a whole by a plurality of support connecting rods of which two ends are respectively fixed on the two inner end surfaces of the outer ends and the two opposite inner end surfaces of the rear end panel of the front casing and the front end panel of the front casing near the connecting flanges, and the plurality of support connecting rods are arranged on the same circumferential surface; the front casing shell with the same central axis is connected with the front casing bearing sleeve in a supporting manner through a plurality of casing supporting spokes, two ends of the front casing shell are respectively fixed on the inner wall surface of the front casing shell and are in supporting connection with a plurality of casing supporting spokes on the circumferential outer surface of the front casing bearing sleeve, a plurality of front casing bearing sleeve through holes are formed in the hollow cylindrical front casing bearing sleeve in the direction parallel to the central axis of the front casing bearing sleeve, the central axes of all the front casing bearing sleeve through holes are all on the same circumferential surface with the central axis of the front casing bearing sleeve as the central axis, the end surfaces of two sides of the front casing bearing sleeve are respectively in the plane extension surfaces of the outer end surfaces of the front casing rear end panel and the front casing front end panel, and the central symmetry surface, parallel to the surface with a large area, of the flat strip-shaped front casing supporting spokes all pass through the central axis of the.
The thrust jet engine is characterized in that the power unit is basically structurally characterized in that: the power unit comprises a power turbine disc, a spray ring and a power ring, wherein the power turbine disc with a power turbine disc key groove is positioned in the center of the power unit, the outer surface of the circumferential side of the power turbine disc is fixedly provided with the root parts of a plurality of power turbofan blades, the top parts of the power turbofan blades are fixedly arranged on the inner wall surface of the circumferential side of a power ring base on the power ring, a plurality of power ring saw-shaped teeth and power ring tooth grooves with the same rotation direction are arranged on the power ring base, a power ring tooth groove is formed between every two adjacent power ring saw-shaped teeth, the power ring tooth groove is formed by a plane passing through the central axis of the power ring and another plane vertical to the plane, the two sides of the power ring tooth groove are power ring tooth groove protecting edges, the tooth socket protecting edge of the power ring is the remaining part of the cylindrical body of the power ring which is remained without removing the end surfaces at two sides of the cylindrical body after removing the tooth socket space volume of the power ring from the cylindrical body of the power ring to the outer surface at the circumference side within the range which is less than the width of the outer surface at the circumference side of the power ring; the spraying ring is surrounded outside the power ring, the power ring and the spraying ring share a central axis, a certain gap is reserved between the power ring and the spraying ring, the spraying ring is in a hollow circular ring shape, one end of the outer surface of the circumference side of the spraying ring is fixedly provided with a power unit rear connecting flange, and the other end of the outer surface of the circumference side of the spraying ring is fixedly provided with a power unit front connecting flange; the spraying ring comprises a spraying ring spraying cavity and a spraying ring spraying channel, wherein the closed space inside the hollow spraying ring is the spraying ring spraying cavity, a plurality of power unit high-pressure gas input ports which are annularly arranged are formed in the end surface of a connecting flange after a power unit is installed and fixed, and the power unit high-pressure gas input ports enable the internal space of the spraying ring spraying cavity to be communicated with the space outside the end surface of the spraying ring where the spraying ring spraying cavity is located; a plurality of spray ring spray channels are arranged between the thicker ring body walls of the radial inner layers of the spray ring spray cavities, the spray ring spray channels enable the inner spaces of the spray ring spray cavities to be communicated with the spaces inside the inner surfaces of the circumferential sides of the spray rings, and the directions of all the spray ring spray channels are consistent according to the same clockwise rotation direction; the spray ring spray channel consists of two parallel planes which are parallel to the central axis of the spray ring and two opposite transitional arc surfaces between the two parallel planes, and the shape of the section of the spray ring spray channel in the section passing through the central axis of the spray ring is the section of the spray ring spray channel; and a sectional line of the plane of the inner wall of the spray ring spray channel, which is farthest away from the central axis of the spray ring in the section perpendicular to the central axis of the spray ring, in the section is tangential to a circumferential line of the inner surface of the inner circumference side of the spray ring in the section.
The thrust jet engine is characterized in that the combustion unit is basically structurally characterized in that: the combustion unit comprises an annular combustion chamber shell, an inner wall surface on the circumferential side of the annular combustion chamber and an ignition device, the surface of the inner wall surface on the circumferential side of the annular combustion chamber is covered by a lining heat insulation layer, the outer surface of the annular combustion chamber shell is covered by a shell heat insulation layer, one end of the annular combustion chamber shell is fixedly provided with a combustion unit front connecting flange, and the other end of the annular combustion chamber shell is fixedly provided with a combustion unit rear connecting flange; the annular combustion chamber shell, the inner wall surface of the annular combustion chamber on the circumferential side of the annular combustion chamber on the inner surface of the annular combustion chamber shell, and the four parts of the annular combustion chamber front end panel and the annular combustion chamber rear end panel are closed together to form an inner space, namely an annular combustion chamber; a plurality of high-pressure gas output ports which are distributed in an annular mode are formed in the upper face of the front end face plate of the annular combustion chamber, a plurality of mixed raw material input ports which are arranged in an annular mode are formed in the upper face of the rear end face plate of the annular combustion chamber, the outward end plane of the front connecting flange of the combustion unit and the outer end face of the front end face plate of the annular combustion chamber are in the same plane, and the outward end plane of the rear connecting flange of the combustion unit and the outer end face of the rear end face plate of the annular combustion chamber are.
The thrust jet engine is characterized in that the basic structure of the raw material preparation unit is as follows: the raw material preparation unit comprises a raw material preparation unit circumferential shell and an air preparation unit, wherein a plurality of openings are arranged between the walls of the raw material preparation unit circumferential shell, a raw material preparation unit air inlet flange interface is correspondingly installed and fixed on each opening on the outer surface of the raw material preparation unit circumferential shell, namely a combustion air input 1 st flange interface and a combustion air input 2 nd flange interface, a raw material preparation unit front connecting flange is installed and fixed on one end of the outer surface of the raw material preparation unit circumferential shell, a raw material preparation unit rear connecting flange is installed and fixed on the other end of the outer surface of the raw material preparation unit circumferential shell, the raw material preparation unit circumferential inner wall, the raw material preparation unit rear end panel and the raw material preparation unit front end panel which are the same as the central axis of the raw material preparation unit circumferential inner wall and, the two ends of the separating ring are respectively fixed on the inner wall surfaces of the rear end panel of the raw material preparation unit and the front end panel of the raw material preparation unit, the air preparation chamber surrounds the raw material mixing chamber, a plurality of air distribution holes which are arranged in a sieve mesh shape are arranged on the separating ring, a plurality of fuel nozzle insertion holes with the central axis on the same circumferential surface are arranged on the rear end panel of the raw material preparation unit at the raw material mixing chamber, and a plurality of raw material preparation unit mixed raw material output ports which are arranged in a ring shape are arranged on the front end panel of the raw material preparation unit at the raw material.
The thrust jet engine is characterized in that the basic structure of the fuel preparation unit is as follows: the fuel preparation unit comprises a raw material preparation unit circumferential shell, a fuel preparation chamber and a fuel nozzle, wherein the fuel preparation chamber is a space formed by sealing the raw material preparation unit circumferential shell, a fuel preparation unit circumferential inner wall which is the same as the raw material preparation unit circumferential shell and has the same central axis with the raw material preparation unit circumferential outer wall, and a fuel preparation unit front end panel and a fuel preparation unit rear end panel together; the circumferential shell of the fuel preparation unit is provided with an opening between the walls, the opening is fixedly provided with a fuel heat exchange input flange interface which is directly communicated with the inside of the fuel preparation chamber, the circumferential surface of one side surface of the outer surface of the circumferential shell close to the front panel of the fuel preparation unit is fixedly provided with a front connecting flange of the fuel preparation unit, and the circumferential surface of one side surface of the outer surface of the circumferential shell close to the rear panel of the fuel preparation unit is fixedly provided with a rear connecting flange of the fuel preparation unit; a plurality of fuel nozzles with central axes on the same circumferential surface are arranged and fixed between the walls of the front end panel of the fuel preparation unit, and the fuel nozzles are communicated with the inside and the outside of the fuel preparation chamber.
The thrust jet engine is characterized in that the basic structure of the composite rear casing is as follows: the composite rear cartridge receiver comprises a composite rear cartridge receiver shell and a composite rear cartridge receiver bearing sleeve, two ports on the outer side surface of the composite rear cartridge receiver shell are respectively provided with and fixed with annular sheet-shaped composite rear cartridge receiver rear end panel and inner ring inner side surfaces of a composite rear cartridge receiver front end panel, a host composite rear cartridge receiver front connecting flange is arranged and fixed on the outer ring outer side surface of the composite rear cartridge receiver front end panel, and a host composite rear cartridge receiver rear connecting flange is arranged and fixed on the outer ring outer side surface of the composite rear cartridge receiver rear end panel; connecting and reinforcing the composite rear casing rear end panel and the composite rear casing front end panel into a whole by a plurality of composite rear casing support connecting rods, wherein the composite rear casing rear end panel and the composite rear casing front end panel are arranged on the same circumferential surface; an additional shell which shares the same central axis with the composite rear cartridge receiver shell is arranged outside the composite rear cartridge receiver shell and between the composite rear cartridge receiver rear end panel and the composite rear cartridge receiver front end panel, 4 parts of the additional shell, the composite rear cartridge receiver front end panel and the composite rear cartridge receiver rear end panel are enclosed to form a closed space, namely a fuel heat exchange chamber, two ends of the fuel heat exchange chamber are respectively fixed on a circumferential surface on the inner side of the additional shell and a plurality of fuel heat exchange chamber heat exchange reinforcing ribs on a circumferential surface on the outer side of the composite rear cartridge receiver shell, a plurality of fuel heat exchange chamber heat exchange reinforcing rib overflowing holes are formed in the fuel heat exchange chamber heat exchange reinforcing ribs, and the integral central symmetrical plane of all the fuel heat exchange chamber heat exchange reinforcing ribs passes through the central axis of the; two openings which are separated by the circumference and are opposite are arranged between the walls of the additional shell, a fuel heat exchange rear output flange interface and a fuel heat exchange front input flange interface are respectively and fixedly arranged on the two openings on the outer surface of the additional shell, and the two flange interfaces are directly communicated with the inside of the fuel heat exchange chamber; the composite rear case bearing sleeve is positioned in the center of the composite rear case shell and has the same central axis with the composite rear case shell, the composite rear case bearing sleeve and the composite rear case shell are connected by a plurality of composite rear case supporting spokes with two ends respectively fixed on the inner wall surface of the composite rear case shell and the circumferential outer surface of the composite rear case bearing sleeve, a plurality of composite rear case bearing sleeve through holes are arranged in the hollow cylindrical composite rear case bearing sleeve body along the direction parallel to the central axis of the composite rear case bearing sleeve, the central axes of all the composite rear case bearing sleeve through holes are on the same circumferential surface with the central axis of the composite rear case bearing sleeve as the central axis, the two side end surfaces of the composite rear case bearing sleeve are respectively in the plane extension plane of the respective outer side end surfaces of the composite rear case end plate and the composite rear case front end plate, and the central symmetry plane parallel to the surface with a larger area on the flat strip composite rear case supporting spokes pass through the composite rear case bearing sleeve and the composite rear case shell Closing the central axis of the bearing sleeve of the casing.
The thrust jet engine is characterized in that the basic structure of the tail nozzle is as follows: the tail nozzle comprises a tail nozzle mounting end face plate, a tail nozzle air flow channel and a circular truncated cone shell, wherein a tail nozzle connecting flange is fixedly mounted on the outer end circumferential side face of the annular disc-shaped tail nozzle mounting end face plate, the inner end circumferential side face of the annular disc-shaped tail nozzle mounting end face plate is fixed with the outer circumferential face of one end of the tail nozzle circumferential inner wall, the bottom face of a large circumferential port of the circular truncated cone shell is fixedly mounted at the position, close to the tail nozzle connecting flange, of the tail nozzle mounting end face plate, close to the outer side of the end face of the tail nozzle circumferential inner wall, the inner side of a small circumferential port of the circular truncated cone shell is fixed with the outer circumferential face of the other end.
The thrust jet engine is characterized in that the main shaft and the auxiliary part surrounding the main shaft are basically structurally characterized in that: the main shaft and the auxiliary part surrounding the main shaft comprise a main shaft, a front bearing and a rear bearing, the front bearing is installed in a front casing bearing sleeve, the rear bearing is installed in a composite rear casing bearing sleeve, the front part and the rear end of the main shaft are respectively installed and fixed between the front bearing and the rear bearing, a front bearing front cover and a front bearing rear cover are respectively covered on the front end surface and the rear end surface of the front bearing, the front bearing front cover and the front bearing rear cover are fixed on the two end surfaces of the front casing bearing sleeve through front bearing cover fixing bolt nuts, a rear bearing front cover and a rear bearing rear cover are respectively covered on the front end surface and the rear end surface of the rear bearing, the rear bearing front cover and the rear bearing rear cover are fixed on the two end surfaces of the composite rear casing bearing sleeve through rear bearing cover fixing bolt nuts, and the root of a tail spray fairing is installed and fixed on the; a 1 st pin key is arranged between the power generation turbofan chassis in front of the front bearing and the main shaft to ensure that the power generation turbofan chassis rotates synchronously with the main shaft, and a shaft head shunting cover is fixed on a main shaft head in front of the power generation turbofan chassis; a2 nd pin key is arranged between the power turbine disc behind the front bearing and the main shaft to ensure that the power turbine disc rotates synchronously with the main shaft, and a 3 rd pin key is arranged between the additional turbofan and the main shaft to ensure that the additional turbofan rotates synchronously with the main shaft.
The thrust jet engine, wherein the parts related to the thrust jet engine are characterized by the following positions and structures: a high-pressure gas output port of the combustion unit in the combustion unit is communicated with a high-pressure gas input port of the power unit in the power unit; a mixed raw material input port of the combustion unit in the combustion unit is communicated with a mixed raw material output port of the raw material preparation unit in the raw material preparation unit; the fuel nozzle in the fuel preparation unit extends into the fuel mixing chamber in the raw material preparation unit through the fuel nozzle insertion hole in the raw material preparation unit, and sealing gaskets are padded around the fuel nozzle and between the raw material preparation unit and the combustion unit; the inner wall surfaces of the circumference of 9 parts including a small straight cylinder air inlet pipe in a thrust air inlet pipe, a pressure tip disc in a power generation unit, a front casing shell in a front casing, a power ring in a power unit, a lining heat insulation layer in a combustion unit, a circumference inner wall of a raw material preparation unit in a raw material preparation unit, a circumference inner wall of a fuel preparation unit in a fuel preparation unit, a composite rear casing shell of a composite rear casing and a circumference inner wall of a tail nozzle pipe in the tail nozzle pipe are basically on the same circumference surface with the central axis of a main shaft as the central axis, and a space formed in the common circumference surface is an air duct arranged in a thrust air jet.
The invention has the beneficial effects that:
compared with the prior gas turbine aviation jet engine, the invention has more comprehensive, outstanding and obvious scientific reasonability and progress, and is represented as follows:
first, the thermal conversion efficiency with ultra-high efficiency. The gas jet-spinning power device is scientific and reasonable compared with a gas turbine power device obviously in mechanical analysis, the heat conversion efficiency of the gas jet-spinning power device is estimated to be improved from about 30 percent of the current power turbine to about 90 percent of the current power turbine, and the gas jet-spinning power device is a huge leap of quality. Specifically, for the whole of the invention, the obvious energy loss is only a small amount of waste heat and thermal radiation caused by the tail gas which is mixed in the tail-jet high-speed airflow and almost does not have kinetic energy originally, the part of the waste heat of the small amount of waste heat is still partially recycled through the heat exchange of the fuel, the energy loss caused by the thermal radiation is also prevented by heat insulation and preservation measures, the heat energy which is really lost is little, and therefore, the heat efficiency of the whole machine is preliminarily estimated to be about 90 percent, which is an inexplicable number.
Secondly, the stamping device is reasonably used, the defect that the flight speed of the existing gas turbine aviation jet engine cannot be improved due to the existence of the air compressor is overcome, and full-speed unlimited free flight of an aircraft can be realized.
Thirdly, the combustion air quantity is variable and circulated, and the controllability and the transient response are excellent. The air intake of the combustion chamber of the invention can be adjusted and controlled by adjusting the relevant air adjusting valve, thereby achieving the purpose of freely controlling the output power of the engine, and completely avoiding the fatal defect of the prior turbine aeroengine in this respect.
And fourthly, full adaptation. The good and free adjustment and control of the air inflow of the combustion air of the invention determines that the invention can be completely adapted in an optimal state to various engine conditions and requirements, and can cope with various changes in a good and reasonable working condition at every moment.
Fifth, full speed. The invention has flight control under two modes, so that the flight speed of the aircraft can be automatically adjusted to the optimal working state to deal with and adapt no matter the flight speed is low speed, subsonic speed or supersonic speed.
Sixth, manufacturing is relatively easy. Compared with the existing aircraft engine, the unique core structure of the invention can completely avoid the nearly harsh manufacturing requirements of the existing turbine aircraft engine on the key components such as turbine blades, turbine discs and the like.
Seventh, the noise is smaller. The noise is closely related to various unreasonable stress conditions, and is an outstanding expression of meaningless energy consumption, and from the physical stress analysis and the thermal efficiency, the stress conditions of the invention are more scientific and reasonable in all aspects than the existing gas turbine aviation jet engine, the thermal efficiency is ultrahigh, and the noise generated by unreasonable stress is less naturally.
Eighth, stability and safety are further ensured. The air inlet mode of the invention adopts a plurality of parallel electric centrifugal turbines for pressurization, even if one of the electric centrifugal turbines is damaged and stops working, the normal work of other electric centrifugal turbines is not influenced, the air inlet of the engine can still be carried out, and compared with the existing air compressor series air inlet mode, the safety guarantee coefficient of the invention is increased by several times.
Ninth, the random power generation is scientific and reasonable. The conventional aero-engine is very difficult to randomly generate electricity, the traditional mechanical modes of a worm, a speed reducer, a generator and the like are adopted to randomly generate electricity, the air inlet smoothness is damaged, and mechanical abrasion, energy loss, noise and the like are very serious.
Tenth, the equipment starts more scientifically, rationally. The invention utilizes the stored compressed air to directly supply combustion air when starting, which is novel than the common starting mode of the motor, and the effect, the cost, the energy consumption and the like are scientific and reasonable.
Eleventh, the infrared stealth function is prominent. Obviously, the jet generating thrust of the invention contains little heat, so the heat radiation is extremely low, and the important infrared stealth performance is far from being compared with that of the prior gas turbine aviation jet engine.
Twelfth, the engine is more convenient and flexible to install and arrange. The invention has the advantages of standard and regular appearance, relatively smaller occupied space and volume, capability of realizing series connection use and double-engine (single-duct) arrangement, which cannot be realized by the existing aeroengine.
Thirteenth, the comprehensive cost performance is not superior. The invention can not only generate the forward thrust required by the aviation jet engine, but also scientifically and reasonably supply electric energy and compressed air energy to the equipment conveniently and reasonably, which is far inferior to the prior gas turbine aviation jet engine.
In a word, the invention is a revolutionary, incomprehensible and ultimate aviation jet engine which is sought by mankind.
Drawings
The invention is further described with reference to the following figures and detailed description.
FIG. 1 is a schematic diagram of the main structural components and the working principle of the technical scheme of the invention;
FIG. 2 is a front view of the thrust jet 1 showing the structural components and appearance of the basic units;
FIG. 3 is a schematic view of the principal structural components and operating principles of the bimodal air supercharger of the present invention;
FIG. 4 is a sectional view taken along line E-E in FIG. 3;
FIG. 5 is a front half-sectional view of the basic structure of the thrust air inlet duct 15 according to the present invention;
FIG. 6 is a top plan view of FIG. 5;
FIG. 7 is a schematic diagram of the main structure, composition and operation principle of the power generation unit 19 according to the present invention;
FIG. 8 is a schematic view in full section taken along line E-E in FIG. 7;
FIG. 9 is a front full sectional view of the main structure of the front casing 21 according to the present invention;
FIG. 10 is a schematic view in full section taken along line E-E in FIG. 9;
FIG. 11 is a front full sectional view of the main structure of the power unit 23 of the present invention;
FIG. 12 is a schematic view in full section taken along line E-E in FIG. 11;
FIG. 13 is a front full sectional view of the main structure of the combustion unit 25 of the present invention;
FIG. 14 is a top plan view of FIG. 13;
FIG. 15 is a schematic view in full section taken along line E-E of FIG. 13;
FIG. 16 is a front full sectional view of the main structure of the raw material preparation unit 27 according to the present invention;
FIG. 17 is a schematic view in half section taken along line E-E in FIG. 16;
FIG. 18 is a front full sectional view of the main structural components of the fuel preparation unit 29 according to the present invention;
FIG. 19 is a top plan view of FIG. 18;
FIG. 20 is a front fully sectional view of the main structural components of the composite aft case 32 of the present invention;
FIG. 21 is a schematic view in full section taken along line E-E of FIG. 20;
FIG. 22 is a front half-sectional view of the main structural components of the jet nozzle 33 of the present invention;
FIG. 23 is a top plan view of FIG. 22;
fig. 24 is a schematic view of the internal structure of the thrust jet 1 and its operating principle according to the present invention.
In the figure: 1. a thrust jet engine, 1a, a combustion air input 1 st flange interface, 1b, a fuel heat exchange front input flange interface, 1c, a fuel heat exchange rear output flange interface, 1d, a combustion air input 2 nd flange interface, 1e, a fuel heat exchange rear input flange interface, 2, a non-heat exchange fuel delivery pipe, 3, a fuel delivery pump, 4, a fuel storage tank, 4a, a fuel output flange interface, 5, a fuel delivery regulating valve, 6, a heat exchange rear fuel delivery pipe, 7, a 2 nd air delivery pipe, 8, a 1 st air delivery pipe, 9, a bimodal air supercharger, 9a, a high pressure air output 1 st flange interface, 9b, a high pressure air output 2 nd flange interface, 10, a combustion air 1 st regulating valve, 11, a combustion air 2 nd regulating valve, 12, a storage battery, 15, a thrust air inlet pipe, 15a thrust air inlet pipe connecting flange, 16, a thrust jet engine 1 st bolt nut, 17. a penetrating rod fastening nut, 18 a penetrating rod, 19a power generation unit front connecting flange, 19b a power generation unit rear connecting flange, 20 a thrust jet machine 2 nd set of bolt nuts, 21a front casing front connecting flange, 21b a front casing rear connecting flange, 22 a thrust jet machine 3 rd set of bolt nuts, 23a power unit front connecting flange, 23b power unit rear connecting flange, 24 a thrust jet machine 4 th set of bolt nuts, 25a combustion unit front connecting flange, 25b combustion unit rear connecting flange, 26 a thrust jet machine 5 th set of bolt nuts, 27a raw material preparation unit front connecting flange, 27b raw material preparation unit rear connecting flange, 28 a thrust jet machine 6 th set of bolt nuts, 29a fuel preparation unit, 29a fuel unit preparation unit front connecting flange, 29b. fuel preparation unit rear connecting flange, 30. thrust jet 7 th set of bolt and nut, 31. thrust jet 8 th set of bolt and nut, 32. composite rear casing, 32a. composite rear casing front connecting flange, 32b. composite rear casing rear connecting flange, 33. tail nozzle, 33a. tail nozzle connecting flange, 34. main shaft and surrounding main shaft auxiliary, 34a. main shaft, 35. additional turbofan, 36. 4 th electric centrifugal air supercharger, 36a. 4 th electric centrifugal air supercharger outlet flange interface, 36b. 4 th electric centrifugal air supercharger inlet flange interface, 37. 4 th branch check valve, 38. 2 nd branch check valve, 39. 2 nd electric centrifugal air supercharger, 39a. 2 nd electric centrifugal air supercharger outlet flange interface, 39b. 2 nd electric centrifugal air supercharger inlet flange interface, 40. supercharger 1 st set of bolt and nut, 41. a supporting protective sleeve, 41a, an inspection window, 42, a supercharger 2 nd set of bolt and nut, 43, a 1 st electric centrifugal air supercharger, 43a, a 1 st electric centrifugal air supercharger outlet flange interface, 43b, a 1 st electric centrifugal air supercharger inlet flange interface, 44, a 1 st branch one-way valve, 45, an air collecting hopper, 45a, an air collecting hopper outlet flange interface, 45b, an air collecting hopper inlet straight cylinder part, 46, a spherical communication, 46a, a spherical communication 1 st branch outlet flange interface, 46b, a spherical communication 2 nd branch outlet flange interface, 46c, a spherical communication 3 rd branch outlet flange interface, 46d, a spherical communication 4 th branch outlet flange interface, 46e, a spherical communication total inlet flange interface, 46f, a spherical communication total inlet flange interface, 47, a total inlet one-way valve, 48, a high-pressure air storage tank, 48a high-pressure air storage tank 1 st branch inlet flange interface, 48b. high-pressure air storage tank 2 nd branch inlet flange interface, 48c. high-pressure air storage tank 3 rd branch inlet flange interface, 48d. high-pressure air storage tank 4 th branch inlet flange interface, 48e. high-pressure air storage tank total inlet flange interface, 48f. high-pressure air storage tank fastening flange, 49. 3 rd branch check valve, 50. 3 rd electric centrifugal air supercharger, 50a. 3 rd electric centrifugal air supercharger outlet flange interface, 50b. 3 rd electric centrifugal air supercharger inlet flange interface, 51. electromagnetic coil stator, 52. permanent magnet rotor, 53. rotor support chassis, 54. adjustable spoke support, 55. pressure tip disk, 56. power generation turbofan chassis, 56a. power generation turbofan chassis keyway, 57. power generation turbofan leaf, 58. power generation unit housing, 59. front casing rear end panel, 60. front casing front end panel, 61. front casing housing, 62. front casing supporting spokes 63, a front casing bearing sleeve 63a, a front casing bearing sleeve through hole 64, a supporting connecting rod 65, a power turbine disc 65a, a power turbine disc key groove 66, a power turbofan blade 67, a power ring 67a, power ring saw teeth 67b, power ring tooth groove protecting edges 67c, power ring tooth grooves 67d, a power ring base 68, a spray ring 68a, a spray channel 68b, a spray cavity 68c, a spray channel cut-off 69, a power unit high-pressure gas inlet, a power unit outer casing 70a, an outer casing heat insulation layer 70a, an annular combustion chamber rear end face 71, an annular combustion chamber front end face 72, an annular combustion chamber inner wall face 73a on the circumferential side, a lining heat insulation layer 73a, a combustion unit mixed raw material inlet 74, an annular combustion chamber 75, an annular combustion chamber 76, combustion unit high-pressure gas outlet 77, an ignition device 78, an air preparation chamber, 79. a separating ring, 79a, air distribution holes, 80, a raw material preparation unit mixed raw material output port, 81, a raw material mixing chamber, 82, a fuel nozzle insertion hole, 83, a raw material preparation unit rear end panel, 84, a raw material preparation unit circumferential inner wall, 85, a raw material preparation unit front end panel, 86, a raw material preparation unit circumferential housing, 87, a fuel nozzle, 88, a fuel preparation chamber, 89, a fuel preparation unit circumferential inner wall, 90, a fuel heat exchange reinforcing rib, 90a, a fuel heat exchange reinforcing rib overflow hole, 91, a fuel preparation unit circumferential housing, 92, a fuel preparation unit front end panel, 93, a fuel preparation unit rear end panel, 94, a fuel heat exchange chamber, 95, a composite rear casing rear end panel, 96, a composite rear casing bearing housing, 96a composite rear casing bearing housing perforation 97, composite rear casing housing, 98, a fuel preparation chamber heat exchange reinforcing rib, 98a fuel heat exchange chamber heat exchange reinforcing rib overflow hole, 99. the composite rear casing supporting connecting rod comprises 100 parts of a composite rear casing front end panel, 101 parts of an additional shell, 102 parts of composite rear casing supporting spokes, 103 parts of a tail spray pipe air flow passage, 104 parts of a tail spray pipe mounting end panel, 105 parts of a circular table shell, 106 parts of a tail spray pipe circumferential inner wall, 107 parts of a tail spray fairing, 108 parts of a rear bearing cover fixing bolt nut, 109 parts of a rear bearing rear cover, 110 parts of a rear bearing, 111 parts of a rear bearing front cover, 112 parts of a sealing gasket, 113 parts of a front bearing cover fixing bolt nut, 114 parts of a front bearing rear cover, 115 parts of a front bearing, 116 parts of a front bearing front cover, 117 parts of a 1 st pin key, 118 parts of a shaft head flow splitting cover, 119 parts of a 2 nd pin key, 120 parts of a 3 rd pin key, 121 parts of a large straight cylinder, 122 parts of a circular table-shaped air inlet pipe and 123 parts of a.
Detailed Description
[ examples ] A method for producing a compound
Referring to the attached figure 1, the bimodal full-speed fully-adaptive variable-circulation rotary jet type aviation jet engine comprises a thrust jet engine 1, a bimodal air supercharger 9, a fuel storage tank 4, a storage battery pack 12 and a fuel delivery pump 3, wherein the fuel storage tank 4 is provided with a fuel output flange interface 4a, 5 external connecting parts including a combustion air input 1 st flange interface 1a, a fuel heat exchange front input flange interface 1b, a fuel heat exchange rear output flange interface 1c, a combustion air input 2 nd flange interface 1d and a fuel heat exchange rear input flange interface 1e are arranged on the thrust jet engine 1, and the upper surface of the fuel heat exchange rear input flange interface 1e is fixedly connected with a flange at the outlet end of a fuel delivery regulating valve 5 through bolts and nuts; a plurality of (2 mapping examples) high-pressure air output flange interfaces are arranged on the dual-mode air supercharger 9, namely 2 positions of the high-pressure air output 1 st flange interface 9a and the high-pressure air output 2 nd flange interface 9b are externally connected with the flange interfaces, and the high-pressure air output 1 st flange interface 9a and the high-pressure air output 2 nd flange interface 9b are fixedly connected with the inlet end flanges of 2 valves of the combustion air 1 st regulating valve 10 and the combustion air 2 nd regulating valve 11 respectively through bolts and nuts; a fuel output flange interface 4a on a fuel storage box 4 is fixedly connected with an inlet end flange of a fuel delivery pump 3, an outlet end flange of the fuel delivery pump 3 is communicated with a fuel heat exchange front input flange interface 1b through a fuel delivery pipe 2 without heat exchange, a fuel heat exchange rear output flange interface 1c is communicated with an inlet end of a fuel delivery regulating valve 5 through a fuel delivery pipe 6 after heat exchange, an outlet end of a combustion air 2 nd regulating valve 11 is communicated with a combustion air input 1 st flange interface 1a through a 2 nd air delivery pipe 7, an outlet end of a combustion air 1 st regulating valve 10 is communicated with a combustion air input 2 nd flange interface 1d through a 1 st air delivery pipe 8, and a storage battery pack 12 is connected with the fuel delivery pump 3, a thrust jet 1 and a bimodal air supercharger 9 through electric wires.
Referring to fig. 2, the thrust jet 1 comprises a thrust air inlet pipe 15 and a tail jet pipe 33, wherein the thrust air inlet pipe 15 positioned at the foremost end of the thrust jet 1 is provided with a thrust air inlet pipe connecting flange 15a, a power generation unit 19 is arranged behind the thrust air inlet pipe 15 and is abutted against the thrust air inlet pipe 15, the power generation unit 19 is provided with a power generation unit front connecting flange 19a and a power generation unit rear connecting flange 19b, and the power generation unit front connecting flange 19a and the thrust air inlet pipe connecting flange 15a are fixedly connected together through a plurality of thrust jet 1 st set bolt nuts 16; behind the power generation unit 19 and leaning against the power generation unit 19, a front case 21 is provided with a front case front connecting flange 21a and a front case rear connecting flange 21b, and the front case front connecting flange 21a and the power generation unit rear connecting flange 19b are fixedly connected together by a plurality of thrust jet machine 2 nd set bolt nuts 20; behind the front case 21 and leaning against it are the power unit 23 with the power unit front connecting flange 23a and the power unit rear connecting flange 23b on it, the power unit front connecting flange 23a and the front case rear connecting flange 21b are fixedly connected together by a plurality of thrust jet 3 rd set bolt and nut 22; behind the power unit 23 and leaning against the power unit, the combustion unit 25 is provided with a combustion unit front connecting flange 25a and a combustion unit rear connecting flange 25b, and the combustion unit front connecting flange 25a and the power unit rear connecting flange 23b are fixedly connected together by a plurality of 4 th sets of bolt and nuts 24 of the thrust jet; behind and abutting against the combustion unit 25 are arranged a material preparation unit front connecting flange 27a, a material preparation unit rear connecting flange 27b and a plurality of (here, 2 drawing examples) combustion air input flange interfaces, namely a combustion air input 1 st flange interface 1a and a combustion air input 2 nd flange interface 1d, on the upper side thereof, the material preparation unit front connecting flange 27a and the combustion unit rear connecting flange 25b are fixedly connected together by a plurality of thrust jet 5 th sets of bolt and nuts 26; behind and against the raw material preparation unit 27 is a fuel preparation unit 29 on which a fuel preparation unit front connecting flange 29a, a fuel preparation unit rear connecting flange 29b and a fuel heat exchange rear input flange interface 1e are arranged, the fuel preparation unit front connecting flange 29a and the raw material preparation unit rear connecting flange 27b are fixedly connected together by a plurality of thrust jet 6 th set bolt and nuts 28; behind the fuel preparation unit 29 and leaning against it is a composite rear case 32 with 4 accessories on it, namely a composite rear case front connecting flange 32a, a composite rear case rear connecting flange 32b, a fuel heat exchange front input flange interface 1b and a fuel heat exchange rear output flange interface 1c, the composite rear case front connecting flange 32a and the fuel preparation unit rear connecting flange 29b are fixedly connected together by a plurality of thrust jet engine 7 th set bolt nuts 30; behind and against the composite rear case 32 is a tail nozzle 33 with a tail nozzle connecting flange 33a arranged thereon, and the tail nozzle connecting flange 33a and the composite rear case rear connecting flange 32b are fixedly connected together by a plurality of 8 th sets of bolt and nuts 31; a main shaft including a main shaft 34a and an auxiliary part 34 surrounding the main shaft are arranged in the thrust jet 1 main body, and an additional turbofan 35 is fixedly arranged on the main shaft 34a and positioned in the raw material preparation unit 27; several (3 drawing examples are used here) penetrating rods 18 respectively penetrate through corresponding flange holes on 16 flanges of a thrust air inlet pipe connecting flange 15a, a front connecting flange 19a, a power generation unit rear connecting flange 19b, a front casing front connecting flange 21a, a front casing rear connecting flange 21b, a power unit front connecting flange 23a, a power unit rear connecting flange 23b, a combustion unit front connecting flange 25a, a combustion unit rear connecting flange 25b, a raw material preparation unit front connecting flange 27a, a raw material preparation unit rear connecting flange 27b, a fuel preparation unit front connecting flange 29a, a fuel preparation unit rear connecting flange 29b, a composite rear casing front connecting flange 32a, a composite rear casing rear connecting flange 32b and a tail nozzle connecting flange 33a, and then the 16 flanges are locked at two ends of each penetrating rod 18 through penetrating rod fastening nuts 17, the penetrating rod 18 is arranged in a staggered and spaced mode from a straight line formed by 8 parts including a thrust jet machine 1 set of bolt and nut 16, a thrust jet machine 2 set of bolt and nut 20, a thrust jet machine 3 set of bolt and nut 22, a thrust jet machine 4 set of bolt and nut 24, a thrust jet machine 5 set of bolt and nut 26, a thrust jet machine 6 set of bolt and nut 28, a thrust jet machine 7 set of bolt and nut 30 and a thrust jet machine 8 set of bolt and nut 31.
Referring to fig. 3 and 4, the dual-mode air supercharger 9 includes a high-pressure air storage tank 48, a spherical communication 46, and a wind-gathering bucket 45, where the spherical communication 46 includes a spherical communication main inlet flange interface 46e and a spherical communication main outlet flange interface 46f that are located at opposite directions and have center lines on one diameter, and a plurality of (here, 4 mapping examples) branch outlet interfaces having center lines on the same plane perpendicular to the diameter, that is, a 1 st branch outlet flange interface 46a is spherically communicated with a 2 nd branch outlet flange interface 46b, a 3 rd branch outlet flange interface 46c is spherically communicated with a 4 th branch outlet flange interface 46d, which are 4 branch outlet interfaces, the wind-gathering bucket 45 includes a wind-gathering bucket outlet flange interface 45a and a wind-gathering bucket inlet straight cylinder portion 45b, a main body in the middle portion of the wind-gathering bucket 45 is a conical bucket body, the bottom of the conical hopper body is provided with an air outlet flange interface 45a of the air collecting hopper, and the open end of the conical hopper body is fixed with an air inlet straight cylinder part 45b of the air collecting hopper; the closed high-pressure air storage tank 48 is provided with two end faces which are an air inlet end face and an air outlet end face respectively, the air outlet end face is provided with a plurality of (2 mapping examples) high-pressure air output interfaces, namely a high-pressure air output 1 st flange interface 9a and a high-pressure air output 2 nd flange interface 9b, the periphery of the air inlet end face is provided with a high-pressure air storage tank fastening flange 48f along the circumferential side face of the high-pressure air storage tank 48, the central part of the upper surface of the air inlet end face is provided with a high-pressure air storage tank main air inlet flange interface 48e, the upper surface of the high-pressure air storage tank main air inlet flange interface 48e is provided with an outlet end of a main air inlet one-way valve 47, and an inlet end flange of the main air; a plurality of branch air inlet ports are arranged around a main air inlet flange port 48e of the high-pressure air storage tank, namely, a 1 st branch air inlet flange port 48a of the high-pressure air storage tank, a 2 nd branch air inlet flange port 48b of the high-pressure air storage tank, a 3 rd branch air inlet flange port 48c of the high-pressure air storage tank and a 4 th branch air inlet flange port 48d of the high-pressure air storage tank are 4 branch air inlet flange ports, wherein a 1 st electric centrifugal air supercharger air outlet flange port 43a, a 2 nd electric centrifugal air supercharger air outlet flange port 39a, a 3 rd electric centrifugal air supercharger air outlet flange port 50a and a 4 th electric centrifugal air supercharger air outlet flange port 37a are respectively arranged and fixed on the 4 th branch air inlet flange ports through bolts and nuts, and the 1 st electric centrifugal air supercharger air inlet flange port 43b and the 2 nd electric centrifugal air supercharger air inlet flange port 39b, The 1 st branch check valve 44, the 2 nd branch check valve 38, the 3 rd branch check valve 49 and the 4 th branch check valve 37, which are all 4 branch check valve outlet end flanges, are respectively fixed on the 4 th electric centrifugal air supercharger inlet flange interface 50b and the 4 th electric centrifugal air supercharger inlet flange interface 37b through bolt and nut mounting, and the 4 th branch check valve inlet end flanges are respectively fixedly connected with the 1 st branch outlet flange interface 46a, the 2 nd branch outlet flange interface 46b, the 3 rd branch outlet flange interface 46c and the 4 th branch outlet flange interface 46d which are all 4 branch outlet flanges through bolt and nut; the spherical communicating main air inlet flange interface 46e is fixed with the air outlet flange interface 45a of the air gathering hopper through bolts and nuts; the supporting and protecting sleeve 41 with a plurality of inspection windows 41a arranged between the circumferential side walls is cylindrical in shape, one end of the supporting and protecting sleeve is fixed with the straight cylinder part 45b of the air inlet of the air gathering hopper through a 2 nd set bolt and nut 42 of the supercharger, and the other end of the supporting and protecting sleeve is fixed with the fastening flange 48f of the high-pressure air storage tank through a 1 st set bolt and nut 40 of the supercharger.
Referring to fig. 5 and 6, the thrust air inlet pipe 15 of the present invention is composed of 4 parts including a large straight cylinder air inlet pipe 121, a circular truncated cone shaped air inlet pipe 122, a small straight cylinder air inlet pipe 123 and a thrust air inlet pipe special connecting flange 15a, wherein the large opening end of the circular truncated cone shaped air inlet pipe 122 is fixedly connected with the outlet end of the large straight cylinder air inlet pipe 121, the small opening end of the air inlet pipe is fixedly connected with the inlet end of the small straight cylinder air inlet pipe 123, a thrust air inlet pipe special connecting flange 15a is arranged and fixed near the outlet end port of the small straight cylinder air inlet pipe 123, the special connecting flange 15a, the large straight cylinder air inlet pipe 121, the circular truncated cone-shaped air inlet pipe 122 and the small straight cylinder air inlet pipe 123 share the same central axis, and the thrust air inlet pipe air inlet channel is formed by the inner spaces of 3 parts of the large straight cylinder air inlet pipe 121, the circular truncated cone-shaped air inlet pipe 122 and the small straight cylinder air inlet pipe 123.
Referring to fig. 7 and 8, in the power generation unit 19 of the present invention, a power generation unit front connection flange 19a and a power generation unit rear connection flange 19b are respectively installed and fixed at two ends of a cylindrical power generation unit housing 58 of the power generation unit 19, an annular electromagnetic coil stator 51 with a concave groove in the middle is installed and fixed on the inner wall surface of the power generation unit housing 58 inside the power generation unit housing 58, three sides of the concave groove in the electromagnetic coil stator 51 surround an annular permanent magnet rotor 52, the permanent magnet rotor 52 is fixed on a rotor support base plate 53, a certain gap is reserved between the electromagnetic coil stator 51 and the permanent magnet rotor 52, and when the permanent magnet rotor 52 rotates in the electromagnetic coil stator 51, an electromagnetic coil in the electromagnetic coil stator 51 always cuts the magnetic force line of the magnetic field where the permanent magnet; a pressure tip disc 55 and a plurality of adjustable spoke supports 54 are arranged in the rotor support chassis 53, two ends of each adjustable spoke support 54 positioned between the pressure tip disc 55 and the rotor support chassis 53 are respectively fixed on the inner wall surface of the rotor support chassis 53 and the outer wall surface of the pressure tip disc 55, a power generation turbofan chassis 56 and a plurality of power generation turbofan blades 57 are arranged in the pressure tip disc 55, the head part of each power generation turbofan blade 57 is fixed on the inner wall surface of the pressure tip disc 55, the root part of each power generation turbofan blade is fixed on the outer surface of the power generation turbofan chassis 56, a key slot, namely a power generation turbofan chassis key slot 56a is arranged on the inner circumferential wall surface of the hollow cylindrical power generation turbofan chassis 56 along the direction parallel to the central axis of the power generation turbofan chassis 56, the power generation unit shell 58, the electromagnetic coil stator 51, the permanent magnet rotor 52, the rotor support chassis 53, the pressure tip disc 55 and the power generation turbofan chassis 56 share a common central axis, the central symmetry plane of the flat strip-shaped adjustable spoke support 54, which is parallel to its larger-area surface, passes all through the common central axis.
Referring to fig. 9 and 10, the basic structure of the front casing 21 of the present invention includes a front casing housing 61 and a front casing bearing housing 63, wherein inner sides of inner rings of a front casing rear end plate 59 and a front casing front end plate 60, which are annular sheets, are respectively mounted and fixed on two ports of an outer side surface of the front casing housing 61, and a front casing front connecting flange 21a and a front casing rear connecting flange 21b are respectively mounted and fixed on outer sides of outer rings of the front casing front end plate 60 and the front casing rear end plate 59; the front casing rear end panel 59 and the front casing front end panel 60 are connected and reinforced into a whole between the respective outer ends and two opposite inner end surfaces of the front casing rear end panel 59 and the front casing front end panel 60 near the respective connecting flanges by a plurality of supporting connecting rods 64 of which two ends are respectively fixed on the two inner end surface parts, and the plurality of supporting connecting rods 64 are arranged on the same circumferential surface; the front casing shell 61 and the front casing bearing sleeve 63 having the same central axis are supported and connected by a plurality of casing support spokes 62 (4 drawing examples in this case) fixed at both ends to the inner wall surface of the front casing shell 61 and the outer surface of the front casing bearing sleeve 63 on the circumferential side, a plurality of (in this example, 4 drawing figures) front casing bearing sleeve through holes 63a are formed in the hollow cylindrical front casing bearing sleeve 63 along a direction parallel to the central axis of the front casing bearing sleeve 63, the central axes of all the front casing bearing sleeve through holes 63a are located on the same circumferential surface with the central axis of the front casing bearing sleeve 63 as the central axis, the end surfaces of both sides of the front casing bearing sleeve 63 are respectively located in the plane extension plane of the outer end surfaces of the front casing rear end panel 59 and the front casing front end panel 60, and the central symmetry plane parallel to the large-area surface of the flat strip-shaped front casing supporting spoke 62 is located on the front casing bearing sleeve 63.
Referring to fig. 11 and 12, the basic structure of the power unit 23 of the present invention includes a power turbine disk 65, a spray ring 68, and a power ring 67, wherein the power turbine disk 65 with a power turbine disk key slot 65a is located at the center of the power unit 23, the outer surface of the circumference of the power turbine disk 65 is fixed with the root of a plurality of power turbine blades 66, the top of the power turbine blade 66 is fixed on the inner wall surface of the circumference of a power ring base 67d on the power ring 67, the power ring base 67d is provided with a plurality of power ring saw teeth 67a and power ring tooth slots 67c with the same rotation direction, a power ring tooth slot 67c is formed between two adjacent power ring saw teeth 67a, the power ring tooth slot 67c is composed of a plane passing through the central axis of the power ring 67 and another plane perpendicular to the plane, two sides of the power ring tooth slot 67c are power ring tooth slot protecting edges 67b, the power ring spline guard 67b is a remaining portion of the cylindrical ring body of the power ring 67 in which the space volume of the power ring spline 67c is removed into the outer surface on the circumferential side of the cylindrical ring body of the power ring 67 in a range of less than the width of the outer surface on the circumferential side of the power ring 67, and both side end surfaces of the cylindrical body are not removed; the outer surface of the power ring 67 surrounds the spray ring 68, the power ring 67 and the spray ring 68 share a central axis, a certain gap is reserved between the two, the spray ring 68 is in a hollow circular ring shape, one end of the outer surface of the circumference side of the spray ring is provided with a power unit rear connecting flange 23b in a fixed mode, and the other end of the outer surface of the circumference side of the spray ring is provided with a power unit front connecting flange 23a in a fixed mode; the spray ring 68 comprises a spray ring spray cavity 68b and a spray ring spray passage 68a, the closed space inside the hollow spray ring 68 is the spray ring spray cavity 68b, a plurality of power unit high-pressure gas input ports 69 which are annularly arranged are arranged on the end surface of the connecting flange 14b after the power unit is installed and fixed, and the power unit high-pressure gas input ports 69 enable the space inside the spray ring spray cavity 68b to be communicated with the space outside the end surface of the spray ring 68 where the spray ring spray cavity 68b is located; a plurality of spray ring spray channels 68a are formed between the thicker ring body walls of the radial inner layers of the spray ring spray cavities 68b, the spray ring spray channels 68a enable the inner space of the spray ring spray cavities 68b to be communicated with the space inside the inner surface of the circumferential side of the spray rings 68, and the pointing directions of all the spray ring spray channels 68a are consistent according to the same clockwise rotation direction; the spray ring spray channel 68a is composed of two parallel planes which are parallel to the central axis of the spray ring 68 and two opposite transitional arc surfaces between the two parallel planes, and the shape of the section of the spray ring spray channel in the section passing through the central axis of the spray ring 68 is the spray ring spray channel section 68 c; a sectional line of the plane of the inner wall of the nozzle ring nozzle passage 68a farthest from the center axis of the nozzle ring 68 in a section perpendicular to the center axis of the nozzle ring 68 is tangential to a circumferential line of the inner surface of the inner circumferential side of the nozzle ring 68 in the section.
Referring to fig. 13, 14 and 15, the combustion unit 25 of the present invention comprises an annular combustion chamber housing 70, an inner wall surface 73 on the circumferential side of the annular combustion chamber, and an ignition device 77, wherein the inner wall surface 73 on the circumferential side of the annular combustion chamber is covered with a lining heat insulating layer 73a, the outer surface of the annular combustion chamber housing 70 is covered with a housing heat insulating layer 70a, one end of which is fixedly provided with a combustion unit front connecting flange 25a, and the other end of which is fixedly provided with a combustion unit rear connecting flange 25 b; the annular combustion chamber housing 70, the inner wall surface 73 of the annular combustion chamber on the inner side of the annular combustion chamber, the front end panel 72 of the annular combustion chamber and the rear end panel 71 of the annular combustion chamber together form an enclosed inner space, namely an annular combustion chamber 75, a plurality of ignition devices 77 (shown by 4 drawing examples) arranged on the same circumferential surface are fixedly arranged between the walls of the middle part of the annular combustion chamber housing 70, and the ignition devices 77 extend into the annular combustion chamber 75; a plurality of high-pressure gas output ports 76 distributed in a ring shape are formed in the front end panel 72 of the annular combustion chamber, a plurality of (4 drawing examples are used here) mixed raw material input ports 74 arranged in a ring shape are formed in the rear end panel 71 of the annular combustion chamber, the outward end plane of the front connecting flange 25a of the combustion unit and the outer end face of the front end panel 72 of the annular combustion chamber are in the same plane, and the outward end plane of the rear connecting flange 25b of the combustion unit and the outer end face of the rear end panel 113 of the annular combustion chamber are in the same plane.
Referring to fig. 16 and 17, the basic structure of the material preparation unit 27 of the present invention includes a material preparation unit peripheral housing 86, an air preparation chamber 78, the material preparation unit peripheral housing 86 having a plurality of openings (here, 2 drawing examples) between its walls, a combustion air input flange port mounted on each opening, i.e., a combustion air input 1 st flange port 1a and a combustion air input 2 nd flange port 1d, a material preparation unit front connecting flange 27a mounted on one end of its outer surface, a material preparation unit rear connecting flange 27b mounted on the other end of its outer surface, and a material preparation unit peripheral inner wall 84 and a material preparation unit rear end plate 83 and a material preparation unit front end plate 85 having the same central axis, which together form a hollow ring body partitioned by a partition ring 79 having the same central axis as the material preparation unit peripheral inner wall 84 into opposite parts The air preparation chamber 78 and the raw material mixing chamber 81 are independent, two ends of a separating ring 79 are respectively fixed on the inner wall surfaces of a raw material preparation unit rear end panel 83 and a raw material preparation unit front end panel 85, the air preparation chamber 78 surrounds the raw material mixing chamber 81, a plurality of air distribution holes 79a arranged in a mesh shape are arranged on the separating ring 79, a plurality of (in 4 drawing examples) fuel nozzle insertion holes 82 with central axes on the same circumferential surface are arranged on the raw material preparation unit rear end panel 83 at the raw material mixing chamber 81, and a plurality of (in 4 drawing examples) raw material preparation unit mixed raw material output holes 80 arranged in a ring shape are arranged on the raw material preparation unit front end panel 85 at the raw material mixing chamber 81.
Referring to fig. 18 and 19, the fuel preparation unit 29 of the present invention includes a material preparation unit circumferential housing 91, a fuel preparation chamber 88, and a fuel nozzle 87, wherein the fuel preparation chamber 88 is a space enclosed by four components, namely, the material preparation unit circumferential housing 91, a fuel preparation unit circumferential inner wall 89 having the same central axis as the material preparation unit circumferential housing 91, and a fuel preparation unit front end plate 92 and a fuel preparation unit rear end plate 93, a plurality of fuel heat exchange ribs 90 having both ends fixed to the inner surface of the material preparation unit circumferential housing 91 and the outer surface of the fuel preparation unit circumferential inner wall 89 are disposed in the fuel preparation chamber 88, a plurality of fuel heat exchange rib through-holes 90a are disposed on the fuel heat exchange ribs 90, and the central symmetry plane of the whole fuel heat exchange ribs 90 passes through the central axis of the fuel preparation unit; the fuel preparation unit circumference shell 91 is provided with an opening between the walls, the outer surface of the opening is provided with a fuel heat exchange rear input flange interface 1e which is directly communicated with the inside of the fuel preparation chamber 88, the outer surface of the opening is provided with a fuel preparation unit front connecting flange 29a on the circumferential surface of one side surface close to the fuel preparation unit front end panel 92, and the outer surface of the opening is provided with a fuel preparation unit rear connecting flange 29b on the circumferential surface of one side surface close to the fuel preparation unit rear end panel 93; a plurality of fuel nozzles 87 (4 drawing examples here) having the same circumferential axis are fixed to the front end plate 92 of the fuel preparation unit between the walls thereof, and the fuel nozzles 87 communicate the inside and outside of the fuel preparation chamber 88.
Referring to fig. 21 and 22, the basic mechanism of the composite rear casing 32 of the present invention includes a composite rear casing housing 97 and a composite rear casing bearing housing 96, two ports on the outer surface of the composite rear casing housing 97 are respectively fixed with a ring-shaped composite rear casing rear end panel 95 and inner side surfaces of respective inner rings of a composite rear casing front end panel 100, a main engine composite rear casing front connecting flange 32a is fixed on the outer side surface of the outer ring of the composite rear casing front end panel 100, and a main engine composite rear casing rear connecting flange 32b is fixed on the outer side surface of the outer ring of the composite rear casing rear end panel 95; the composite rear casing rear end panel 95 and the composite rear casing front end panel 100 are connected and reinforced into a whole between the composite rear casing rear end panel 95 and the composite rear casing front end panel 100 by a plurality of composite rear casing support connecting rods 99, the two ends of which are respectively fixed on the opposite inner side end parts, between the respective outer ends and opposite inner side end surfaces of the composite rear casing rear end panel 95 and the composite rear casing front end panel 100 near the respective connecting flanges, and the plurality of composite rear casing support connecting rods 99 are arranged on the same circumferential surface; an additional shell 101 which shares the same central axis with the composite rear casing shell 97 is arranged outside the composite rear casing shell 97 and between the composite rear casing rear end panel 95 and the composite rear casing front end panel 100, 4 parts of the additional shell 101, the composite rear casing shell 97, the composite rear casing front end panel 100 and the composite rear casing rear end panel 95 are surrounded to form a closed space, namely a fuel heat exchange chamber 94, two ends of the fuel heat exchange chamber 94 are respectively fixed on the inner side circumferential surface of the additional shell 101 and a plurality of fuel heat exchange chamber heat exchange reinforcing ribs 98 on the outer side circumferential surface of the composite rear casing shell 97, a plurality of fuel heat exchange chamber heat exchange reinforcing rib overflowing holes 98a are formed in the fuel heat exchange chamber heat exchange reinforcing ribs 98, and the integral central symmetrical plane of all the fuel heat exchange chamber heat exchanging reinforcing ribs 98 passes through the central axis of the composite rear casing shell 97; two opposite openings separated by the circumference are arranged between the walls of the additional shell 101, a fuel heat exchange rear output flange interface 1c and a fuel heat exchange front input flange interface 1b are respectively and fixedly arranged on the two openings on the outer surface of the additional shell, and the two flange interfaces are directly communicated with the inside of the fuel heat exchange chamber 94; a composite rear casing bearing sleeve 96 which is located at the center of the composite rear casing shell 97 and has the same central axis with the composite rear casing shell 97 is supported and connected with the composite rear casing shell 97 by a plurality of composite rear casing support spokes 102 (4 drawing examples are used herein) which are fixed on the inner wall surface of the composite rear casing shell 97 and on the outer surface of the composite rear casing bearing sleeve 96 on the circumferential side at two ends respectively, a plurality of composite rear casing bearing sleeve through holes 96a (4 drawing examples are used herein) are arranged in the hollow cylindrical composite rear casing bearing sleeve 96 along the direction parallel to the central axis of the composite rear casing bearing sleeve 96, the central axes of all the composite rear casing bearing sleeve through holes 96a are all on the same circumferential surface with the central axis of the composite rear casing bearing sleeve 96 as the central axis, the end surfaces on two sides of the composite rear casing bearing sleeve 96 are respectively in the plane extension surfaces of the outer end surfaces of the composite rear casing rear end plate 95 and the composite rear casing front end plate 100, the central symmetry plane of the flat strip of composite rear case support spokes 102, which is parallel to the larger surface area thereof, passes through the central axis of the composite rear case bearing housing 96.
Referring to fig. 22 and 23, the exhaust nozzle 33 of the present invention includes an exhaust nozzle mounting end plate 104, an exhaust nozzle air flow passage 103, and a circular truncated cone housing 105, wherein an exhaust nozzle connecting flange 33a is fixedly mounted on an outer circumferential side of the annular disk-shaped exhaust nozzle mounting end plate 104, an inner circumferential side of the annular disk-shaped exhaust nozzle mounting end plate is fixed to an outer circumferential side of one end of an exhaust nozzle circumferential inner wall 106, a bottom surface of a large circumferential port of the circular truncated cone housing 105 is fixedly mounted on a position of the exhaust nozzle mounting end plate 104, which is close to the exhaust nozzle connecting flange 33a, on an outer circumferential side of an end surface of the exhaust nozzle circumferential inner wall 106, an inner side of a small circumferential port of the circular truncated cone housing is fixed to an outer circumferential side of the other end of the exhaust nozzle circumferential inner.
Referring to fig. 24, the main shaft and surrounding main shaft auxiliary member 34 of the present invention includes a main shaft 34a, a front bearing 115, and a rear bearing 110, the front casing bearing housing 63 is provided with the front bearing 115, the composite rear casing bearing housing 96 is provided with the rear bearing 110, the front and rear ends of the main shaft 34a are respectively fixed between the front bearing 115 and the rear bearing 110, the front and rear end surfaces of the front bearing 115 are respectively covered with a front bearing front cover 116 and a front bearing rear cover 114, and a front bearing front cover 116 and a front bearing rear cover 114 are fixed on two end faces of the front casing bearing sleeve 63 through front bearing cover fixing bolts and nuts 113, a rear bearing front cover 111 and a rear bearing rear cover 109 are respectively covered on the front and rear end faces of the rear bearing 110, a rear bearing front cover 111 and a rear bearing rear cover 109 are fixed on two end faces of the composite rear casing bearing sleeve 96 through rear bearing cover fixing bolts and nuts 108, and the root of a tail spray fairing 107 is fixedly arranged on the rear bearing rear cover 109; a 1 st pin 117 is arranged between the power generation turbofan chassis 56 in front of the front bearing 115 and the main shaft 34a to ensure that the power generation turbofan chassis 56 rotates synchronously with the main shaft 34a, and a shaft head shunt cover 118 is fixed on a shaft head of the main shaft 34a in front of the power generation turbofan chassis 56; a 2 nd pin 119 is arranged between the power turbine disk 65 behind the front bearing 115 and the main shaft 34a to ensure that the power turbine disk 65 rotates synchronously with the main shaft 34a, and a 3 rd pin 120 is arranged between the additional turbofan 35 and the main shaft 34a to ensure that the additional turbofan 31 rotates synchronously with the main shaft 34a.
Referring to fig. 24, the combustion unit high pressure gas outlet 76 and the power unit high pressure gas inlet 69 are connected to each other, the combustion unit mixed material inlet 74 and the material preparation unit mixed material outlet 80 are connected to each other, the fuel nozzle 87 is inserted into the fuel mixing chamber 81 through the fuel nozzle insertion hole 82, and the fuel nozzle 87 is provided with a sealing gasket 112 around and between the material preparation unit 27 and the combustion unit 25; the inner wall surfaces of the respective circumferences of 9 parts including the small straight-tube air inlet pipe 123, the pressure tip disc 55, the front casing shell 61, the power ring 67, the lining heat insulation layer 73a, the raw material preparation unit circumferential inner wall 84, the fuel preparation unit circumferential inner wall 89, the composite rear casing shell 97 and the tail nozzle circumferential inner wall 106 are basically on a common circumferential surface taking the central axis of the main shaft 34a as the central axis, and the space formed in the common circumferential surface is an air duct arranged in the thrust jet 1.
The overall working principle and the operation of the operation process of the device are explained as follows:
referring to FIG. 4, the operation of the dual mode air supercharger 9 will be described. When the aircraft driven by the device of the invention is at a starting state or below a certain speed, the air ram pressure generated by the inner air hopper 45 of the dual-mode air supercharger 9 is insufficient due to the fact that the flying speed of the aircraft is not high, namely the air pressure in the spherical communication 46 is not high, at the moment, the 1 st electric centrifugal air supercharger 43, the 2 nd electric centrifugal air supercharger 39, the 3 rd electric centrifugal air supercharger 50 and the 4 th electric centrifugal air supercharger 36 start to work simultaneously, the air pressure in the spherical communication 46 is rapidly reduced, the air pressure in the high-pressure air storage tank 48 is rapidly increased, the outside air is rapidly reduced due to the air pressure in the spherical communication 46 to enter the spherical communication 46 from the air hopper 45, at the moment, the air pressure in the high-pressure air storage tank 48 is rapidly increased and obviously exceeds the air pressure in the spherical communication 46, and the total air inlet one-way valve 47 is caused to increase the reverse differential pressure at the inlet and the outlet ends to realize the non-, the air in the spherical communication 46 can not directly pass through the main air inlet check valve 47 to enter the high-pressure air storage tank 48, obviously, the ram air inlet mode in the dual-mode air supercharger 9 can not work, and the air in the spherical communication 46 can only enter the high-pressure air storage tank 48 by virtue of the electric centrifugal supercharger. Needless to say, the air charging pressure collected and generated in the air collecting hopper 45 is directly related to the flight speed of the aircraft, the higher the flight speed of the aircraft is, the higher the air pressure in the air collecting hopper 45 and the spherical communication 46 is, when the flight speed of the aircraft is faster and exceeds a certain speed, the air pressure in the spherical communication 46 finally exceeds the air pressure generated by the front electric centrifugal supercharger in the high-pressure air storage tank 48, at this time, the non-return function of the main air inlet check valve 47 fails to be opened, the ram air in the air collecting hopper 45 and the spherical communication 46 directly enters the high-pressure air storage tank 48 through the main air inlet check valve 47, and the physical law of fluid motion tells us that: the pressure is small at the place with fast flow speed, obviously, the air pressure at the inlet ends of the 1 st branch check valve 44, the 2 nd branch check valve 38, the 3 rd branch check valve 49 and the 4 th branch check valve 37 is all reduced, and at the same time, the opposite situation is just opposite, the outlet ends of the four branch check valves are increased along with the increase of the air pressure in the high-pressure air storage tank 48, the reverse pressure difference between the inlet end and the outlet end of the four branch check valves is increased, so that the four branch check valves start to exert the non-return function, the high-pressure air in the high-pressure air storage tank 48 is not leaked while the air intake is stopped, correspondingly, all the electric dual-mode centrifugal superchargers stop working, and at this time, the electric dual-mode air supercharger 9 is automatically switched to the ram air intake mode from the former electric dual. When the flying speed of the aircraft is reduced, the dual-mode air supercharger 9 can be restored to the previous working state at the initial starting, in short, under the condition that the dual-mode air supercharger is held in turn and switched automatically, the high-pressure air which is not lower than a certain set air pressure value can be always and automatically maintained in the high-pressure air storage tank 48 in the dual-mode air supercharger 9.
Referring to fig. 1, after a certain air pressure is stored and maintained in the high-pressure air storage tank 48, the combustion air 1-adjusting valve 10 and the combustion air 2-adjusting valve 11 are first opened and adjusted, and the high-pressure air previously stored in the dual-mode air supercharger 9 enters the interior of the thrust jet 1 through the 1 st air delivery pipe 8 and the 2 nd air delivery pipe 7, the combustion air 1-adjusting valve 10 and the combustion air 2-adjusting valve 11, and the combustion air input 2 nd flange port 1d and the combustion air input 1 st flange port 1a, respectively.
Referring to fig. 24, high pressure air enters the air preparation chamber 78 and then enters the raw material mixing chamber 81 through the air distribution holes 79a.
Referring to the attached drawing 1, when a combustion air 1-th regulating valve 10 and a combustion air 2-th regulating valve 11 are started, a fuel delivery pump 3 is started and a fuel delivery regulating valve 5 is opened at the same time, fuel stored in a fuel storage tank 4 enters the thrust jet 1 for heat exchange through a fuel delivery pump 3 → a fuel delivery pipe 2 → a fuel input flange interface 1b before heat exchange, and the fuel with certain temperature rise flows out of the thrust jet 1 from a fuel heat exchange output flange interface 1c and then enters the thrust jet 1 again through a heat exchange fuel delivery pipe 6, the fuel delivery regulating valve 5 and a fuel heat exchange input flange interface 1 e;
referring to fig. 24, after heat exchange, fuel enters the flange interface 1e into the fuel preparation chamber 88, then enters the raw material mixing chamber 81 through the fuel nozzle 87, and then fully mixes with high-pressure air therein to form high-pressure mixed fuel, the high-pressure mixed fuel continues to enter the annular combustion chamber 75 through the raw material preparation unit mixed raw material outlet 80 and the combustion unit mixed raw material inlet 74, the high-pressure mixed fuel is combusted under ignition of the ignition device 77 to form high-pressure gas, the high-pressure gas enters the injection chamber 68b through the combustion unit high-pressure gas outlet 76 and the power unit high-pressure gas inlet 69, the high-pressure gas in the injection chamber 68b is sprayed out through the injection passage 68c, and the high-pressure gas sprayed out through rotary spraying causes the power ring 67 to rotate around its central axis by impacting saw-shaped teeth on the power ring 67, the rotating power ring 67 drives the power turbofan blade 66 to surround and drive the main shaft 34a of the device to rotate together, the rotating main shaft 34a drives the power generating turbofan blade 57 and the additional turbofan 35 to rotate synchronously to work, after external air enters the front end of an air duct formed in the main body part of the engine from the thrust air inlet pipe 15, three-way turbofan including the power generating turbofan blade 57, the power turbofan blade 66 and the additional turbofan 35 in the air duct continuously accelerate the air entering the air duct under the driving of the rotating main shaft 34a, and finally the pressurized air is accelerated and ejected from the tail end of the air duct, so that the thrust of the device is generated, and meanwhile, the external air is sucked into the air duct in the main body part of the engine from the thrust air inlet pipe 15 in front of the device, so that the external air is circulated continuously. The rotating power generating turbofan blades 57, while ensuring accelerated input of outside air into the apparatus of the present invention, simultaneously drive the permanent magnet rotor 52 to rotate within the electromagnetic coil stator 51, which generates current in the electromagnetic coil stator 51 according to the electromagnetic power generating principle in the general knowledge of physics.
Referring to fig. 1, the electric energy generated by the power generation unit 19 in the thrust jet 1 is delivered to the battery pack 12 for storage, and the electric energy in the battery pack 12 is delivered to the electric centrifugal superchargers in the dual-mode air supercharger 9 and the fuel delivery pump 4 to ensure that the electric centrifugal superchargers operate and deliver air and fuel to participate in combustion, release chemical energy and ensure that the device operates continuously.
Claims (11)
1. Bimodal full-speed full-adaptive variable-cycle jet aero-jet engine, including storage battery (12), fuel storage box (4), fuel delivery pump (3), be equipped with fuel output flange interface (4a), its characterized in that on fuel storage box (4): the main body part of the device comprises a thrust jet (1) and a bimodal air supercharger (9), wherein 5 outward connecting parts including a combustion air input 1 st flange interface (1a), a fuel heat exchange front input flange interface (1b), a fuel heat exchange rear output flange interface (1c), a combustion air input 2 nd flange interface (1d) and a fuel heat exchange rear input flange interface (1e) are arranged on the thrust jet (1), and the fuel heat exchange rear input flange interface (1e) is fixedly connected with an outlet end flange of a fuel conveying regulating valve (5) through bolts and nuts; a plurality of high-pressure air output flange interfaces are arranged on the bimodal air supercharger (9), namely 2 positions of the high-pressure air output 1 st flange interface (9a) and the high-pressure air output 2 nd flange interface (9b) are externally connected with the flange interfaces, and the 2 positions of the high-pressure air output 1 st flange interface (9a) and the high-pressure air output 2 nd flange interface (9b) are respectively and fixedly connected with the inlet end flanges of 2 valves including a combustion air 1 st regulating valve (10) and a combustion air 2 nd regulating valve (11) through bolts and nuts; a fuel output flange interface (4a) on the fuel storage box (4) is fixedly connected with an inlet end flange of a fuel delivery pump (3), an outlet end flange of the fuel delivery pump (3) is communicated with an input flange interface (1b) before fuel heat exchange by a fuel delivery pipe (2) without heat exchange, an output flange interface (1c) after fuel heat exchange is communicated with an inlet end of a fuel delivery regulating valve (5) by a fuel delivery pipe (6) after heat exchange, an outlet end of a combustion air 2 regulating valve (11) is communicated with an input flange interface (1a) of combustion air 1 by a 2 nd air delivery pipe (7), an outlet end of a combustion air 1 st regulating valve (10) is communicated with an input flange interface (1d) of combustion air 2 by a 1 st air delivery pipe (8), a storage battery pack (12) is provided with a conductive wire and the fuel delivery pump (3), the thrust jet (1) is connected with the bimodal air supercharger (9).
2. The bi-modal full-speed fully adaptive variable cycle jet aero-jet engine of claim 1 wherein: the thrust jet engine (1) comprises a thrust air inlet pipe (15) and a tail jet pipe (33), wherein a thrust air inlet pipe connecting flange (15a) is arranged on the thrust air inlet pipe (15) positioned at the foremost end of the thrust jet engine (1), a power generation unit (19) provided with a power generation unit front connecting flange (19 a') and a power generation unit rear connecting flange (19b) is arranged behind the thrust air inlet pipe (15) and is abutted against the thrust air inlet pipe, and the power generation unit front connecting flange (19a) and the thrust air inlet pipe connecting flange (15a) are fixedly connected together through a plurality of thrust jet engine 1-th set bolt nuts (16); the front casing (21) is provided with a front casing front connecting flange (21a) and a front casing rear connecting flange (21b) on the front casing, and the front casing front connecting flange (21a) and the power generation unit rear connecting flange (19b) are fixedly connected together by a plurality of thrust jet machine 2 nd set bolt nuts (20); the power unit (23) is arranged behind the front case (21) and is abutted against the front case, a front power unit connecting flange (23a) and a rear power unit connecting flange (23b) are arranged on the power unit (23), and the front power unit connecting flange (23a) and the rear front case connecting flange (21b) are fixedly connected together through a plurality of 3 rd sets of bolt and nuts (22) of the thrust jet; the combustion unit (25) is provided with a combustion unit front connecting flange (25a) and a combustion unit rear connecting flange (25b) on the upper surface, and the combustion unit front connecting flange (25a) and the combustion unit rear connecting flange (23b) are fixedly connected together by a plurality of 4 th sets of bolt nuts (24) of the thrust jet; a raw material preparation unit front connecting flange (27a), a raw material preparation unit rear connecting flange (27b) and a plurality of combustion air input flange interfaces are arranged on the rear surface of the combustion unit (25) and are abutted against the combustion unit, namely a combustion air input 1 st flange interface (1a) and a combustion air input 2 nd flange interface (1d), and the raw material preparation unit front connecting flange (27a) and the combustion unit rear connecting flange (25b) are fixedly connected together by a plurality of thrust jet machine 5 th set bolt nuts (26); behind and against the raw material preparation unit (27) is a fuel preparation unit (29) provided with a fuel preparation unit front connecting flange (29a), a fuel preparation unit rear connecting flange (29b) and a fuel heat exchange rear input flange interface (1e), the fuel preparation unit front connecting flange (29a) and the raw material preparation unit rear connecting flange (27b) are fixedly connected together by a plurality of thrust jet 6 th set bolt nuts (28); the composite rear case (32) is provided with 4 accessories including a composite rear case front connecting flange (32a), a composite rear case rear connecting flange (32b), a fuel heat exchange front input flange interface (1b) and a fuel heat exchange rear output flange interface (1c) on the rear surface of the fuel preparation unit (29) and is abutted against the fuel preparation unit, and the composite rear case front connecting flange (32a) and the fuel preparation unit rear connecting flange (29b) are fixedly connected together by a plurality of thrust jet machine 7 th set bolt nuts (30); the rear part of the composite rear casing (32) is abutted against the rear part of the composite rear casing, the rear nozzle (33) is provided with a rear nozzle connecting flange (33a), and the rear nozzle connecting flange (33a) and the rear connecting flange (32b) of the composite rear casing are fixedly connected together by a plurality of 8 th sets of bolt and nuts (31); a main shaft including a main shaft (34a) and an auxiliary part (34) surrounding the main shaft are arranged in the thrust jet main body part, and an additional turbofan (35) is fixedly arranged on the upper surface of the main shaft (34a) at the position inside the raw material preparation unit (27); a plurality of through rods (18) respectively pass through corresponding flange holes on 16 flanges, namely a thrust air inlet pipe connecting flange (15a), a power generation unit front connecting flange (19a), a power generation unit rear connecting flange (19b), a front casing front connecting flange (21a), a front casing rear connecting flange (21b), a power unit front connecting flange (23a), a power unit rear connecting flange (23b), a combustion unit front connecting flange (25a), a combustion unit rear connecting flange (25b), a raw material preparation unit front connecting flange (27a), a raw material preparation unit rear connecting flange (27b), a fuel preparation unit front connecting flange (29a), a fuel preparation unit rear connecting flange (29b), a composite rear casing front connecting flange (32a), a composite rear casing rear connecting flange (32b) and a tail spray pipe connecting flange (33a), and then the 16 flanges are locked at two ends of each through rod (18) through rod-fastening nuts (17), the penetrating rod (18) is arranged in a staggered and spaced mode together with a straight line formed by 8 parts of a thrust jet machine 1 st set of bolt and nut (16), a thrust jet machine 2 nd set of bolt and nut (20), a thrust jet machine 3 rd set of bolt and nut (22), a thrust jet machine 4 th set of bolt and nut (24), a thrust jet machine 5 th set of bolt and nut (26), a thrust jet machine 6 th set of bolt and nut (28), a thrust jet machine 7 th set of bolt and nut (30) and a thrust jet machine 8 th set of bolt and nut (31).
3. The bi-modal full-speed fully adaptive variable cycle jet aero-jet engine of claim 1 wherein: the dual-mode air supercharger (9) comprises a high-pressure air storage tank (48), a spherical communication (46) and an air gathering hopper (45), wherein the spherical communication (46) comprises a spherical communication total air inlet flange interface (46e) and a spherical communication total air outlet flange interface (46f) which are opposite and have center lines on one diameter, and a plurality of branch air outlet interfaces of which the center lines are vertical to the diameter in the same plane, namely a 1 st branch air outlet flange interface (46a) is in spherical communication, a 2 nd branch air outlet flange interface (46b) is in spherical communication, a 3 rd branch air outlet flange interface (46c) is in spherical communication, a 4 th branch air outlet flange interface (46d) is in spherical communication, the air gathering hopper (45) comprises an air gathering hopper air outlet flange interface (45a) and an air gathering hopper air inlet straight cylinder part (45b), the main body in the middle of the air gathering hopper (45) is a conical hopper body, the bottom of the conical hopper body is provided with an air outlet flange interface (45a) of the air gathering hopper, and the open end of the conical hopper body is fixed with an air inlet straight cylinder part (45b) of the air gathering hopper; the high-pressure air storage tank (48) is closed, two end faces of the high-pressure air storage tank are an air inlet end face and an air outlet end face respectively, the air outlet end face is provided with a plurality of high-pressure air output interfaces, namely a high-pressure air output 1 st flange interface (9a) and a high-pressure air output 2 nd flange interface (9b), a high-pressure air storage tank fastening flange (48f) is arranged on the periphery of the air inlet end face along the circumferential side face of the high-pressure air storage tank (48), the central part of the upper surface of the air inlet end face is provided with a high-pressure air storage tank main air inlet flange interface (48e), the upper surface of the high-pressure air storage tank main air inlet flange interface (48e) is provided with an outlet end of a main air inlet one-way valve (47), and an inlet end flange; around high-pressure air storage jar general flange interface that admits air (48e) arranged several branch interface that admits air, this be 1 branch of high-pressure air storage jar flange interface that admits air (48a), 2 branch flange interface that admits air (48b) of high-pressure air storage jar, 3 branch flange interface that admits air (48c) of high-pressure air storage jar 4 branch flange interface that admits air (48d) total 4 branch flange interfaces that admit air, install through bolt and nut respectively above this 4 branch flange interfaces that admits air and be fixed with 1 electronic centrifugal air booster flange interface (43a), 2 electronic centrifugal air booster flange interface that admits air (39a), 3 electronic centrifugal air booster flange interface that admits air (50a), 4 electronic centrifugal air booster flange interface that admits air (37a), and 1 electronic centrifugal air booster admit air flange interface (43b) that admits air, Outlet end flanges of 4 branch check valves including a 1 st branch check valve (44), a 2 nd branch check valve (38), a 3 rd branch check valve (49) and a 4 th branch check valve (37) are respectively and fixedly arranged on the 4 th electric centrifugal air supercharger inlet flange interface (39b), the 3 rd electric centrifugal air supercharger inlet flange interface (50b) and the 4 th electric centrifugal air supercharger inlet flange interface (37b) through bolts and nuts, the inlet end flanges of the 4 branch check valves are fixedly connected with 4 branch outlet flanges including a spherical communicated 1 st branch air outlet flange interface (46a), a spherical communicated 2 nd branch air outlet flange interface (46b), a spherical communicated 3 rd branch air outlet flange interface (46c) and a spherical communicated 4 th branch air outlet flange interface (46d) through bolts and nuts respectively; the spherical communicating main air inlet flange interface (46e) is fixed with the gathering air hopper air outlet flange interface (45a) through bolts and nuts; a supporting and protecting sleeve (41) with a plurality of inspection windows (41a) is arranged between the circumferential side walls, the shape of the supporting and protecting sleeve is cylindrical, one end of the supporting and protecting sleeve is fixed with a straight cylinder part (45b) of an air inlet of the air gathering hopper through a 2 nd set of bolt and nut (42) of the supercharger, and the other end of the supporting and protecting sleeve is fixed with a fastening flange (48f) of a high-pressure air storage tank through a 1 st set of bolt and nut (40) of the supercharger.
4. The bi-modal full-speed fully adaptive variable cycle jet aero-jet engine of claim 1 wherein: the two ends of a cylindrical power generation unit shell (58) of a power generation unit (19) in the thrust jet (1) are respectively provided with a power generation unit front connecting flange (19a) and a power generation unit rear connecting flange (19b), an annular electromagnetic coil stator (51) which is provided with a concave groove in the middle and is arranged and fixed on the inner wall surface of the power generation unit shell (58) is arranged in the power generation unit shell (58), three sides of the concave groove in the electromagnetic coil stator (51) surround an annular permanent magnet rotor (52), the permanent magnet rotor (52) is fixed on a rotor support chassis (53), a certain gap is reserved between the electromagnetic coil stator (51) and the permanent magnet rotor (52), when the permanent magnet rotor (52) rotates in the electromagnetic coil stator (51), the electromagnetic coil in the electromagnetic coil stator (51) cuts the magnetic line of force of the magnetic field where the permanent magnet rotor (52) is located all the time; a pressure tip disk (55) and a plurality of adjustable spoke supports (54) are arranged in the rotor support chassis (53), two ends of each adjustable spoke support (54) positioned between the pressure tip disk (55) and the rotor support chassis (53) are respectively fixed on the inner wall surface of the rotor support chassis (53) and the outer wall surface of the pressure tip disk (55), a power generation turbofan chassis (56) and a plurality of power generation turbofan blades (57) are arranged in the pressure tip disk (55), the head part of each power generation turbofan blade (57) is fixedly arranged on the inner wall surface of the pressure tip disk (55), the root part of each blade is fixedly arranged on the cylindrical outer surface of the power generation turbofan chassis (56), a key slot, namely a power generation turbofan chassis key slot (56a), is arranged on the inner circumferential wall surface of the hollow power generation turbofan chassis (56) along the direction parallel to the central axis of the power generation turbofan chassis (56), and a power generation unit shell (58), The 6 parts of the electromagnetic coil stator (51), the permanent magnet rotor (52), the rotor support base plate (53), the pressure tip disc (55) and the power generation turbofan base plate (56) share a common central axis, and the central symmetry plane on the flat strip-shaped adjustable spoke support (54) parallel to the surface with a larger area of the flat strip-shaped adjustable spoke support passes through the common central axis.
5. The bi-modal full-speed fully adaptive variable cycle jet aero-jet engine of claim 1 wherein: the basic structure of the front casing (21) in the thrust jet (1) comprises a front casing shell (61) and a front casing bearing sleeve (63), wherein the two ports on the outer side surface of the front casing shell (61) are respectively provided with and fixed with the inner side surfaces of the inner rings of a front casing rear end panel (59) and a front casing front end panel (60) which are annular sheets, the outer side surfaces of the outer rings of the front casing front end panel (60) and the front casing rear end panel (59) are respectively provided with and fixed with a front casing front connecting flange (21a) and a front casing rear connecting flange (21b), the front casing rear end panel (59) and the front casing front end panel (60) near the respective connecting flanges are connected and reinforced into a whole by a plurality of supporting connecting rods (64) with two ends respectively fixed on the two inner end surface parts between the outer ends and the opposite inner side surfaces, the plurality of supporting connecting rods (64) are arranged on the same circumferential surface, a front casing shell (61) with the same central axis is connected with a front casing bearing sleeve (63) in a supporting way through a plurality of casing supporting spokes (62) which are respectively fixed on the inner wall surface of the front casing shell (61) by two ends and are arranged on the circumferential outer surface of the front casing bearing sleeve (63), a plurality of front casing bearing sleeve through holes (63a) are arranged in the hollow cylindrical front casing bearing sleeve (63) along the direction parallel to the central axis of the front casing bearing sleeve (63), the central axes of all the front casing bearing sleeve through holes (63a) are arranged on the same circumferential surface with the central axis of the front casing bearing sleeve (63) as the central axis, the end surfaces of two sides of the front casing bearing sleeve (63) are respectively arranged in the plane extension surfaces of the respective outer end surfaces of a front casing rear end panel (59) and a front casing front end panel (60), the central symmetry plane on the flat strip-shaped front casing supporting spoke (62) parallel to the surface with larger area completely passes through the central axis of the front casing bearing sleeve (63); the basic mechanism of the composite rear casing (32) comprises a composite rear casing shell (97) and a composite rear casing bearing sleeve (96), wherein two ports on the outer side surface of the composite rear casing shell (97) are respectively provided with and fixed with inner side surfaces of respective inner rings of an annular sheet-shaped composite rear casing rear end panel (95) and a composite rear casing front end panel (100), an outer side surface of the outer ring of the composite rear casing front end panel (100) is provided with and fixed with a host composite rear casing front connecting flange (32a), an outer side surface of the outer ring of the composite rear casing rear end panel (95) is provided with and fixed with a host composite rear casing rear connecting flange (32b), a plurality of composite rear casing supporting connecting rods (99) respectively fixed on the relative inner side end surfaces between the outer ends and the relative inner side end surfaces of the composite rear casing rear end panel (95) and the composite rear casing front end panel (100) near the respective connecting flanges are used for supporting the composite rear casing rear end panel (95) and the composite rear casing front end panel (100) by a plurality of composite rear casing supporting connecting rods (99) The front end panel (100) of the cartridge receiver is connected and reinforced into a whole, the plurality of composite rear cartridge receiver supporting connecting rods (99) are arranged on the same circumferential surface, an additional shell (101) which shares the same central axis with the composite rear cartridge receiver shell (97) is arranged outside the composite rear cartridge receiver shell (97) and between the composite rear cartridge receiver rear end panel (95) and the composite rear cartridge receiver front end panel (100), the additional shell (101), the composite rear cartridge receiver shell (97), the composite rear cartridge receiver front end panel (100) and the composite rear cartridge receiver rear end panel (95) are enclosed by 4 parts, namely a fuel heat exchange chamber (94), a plurality of fuel chamber heat exchange reinforcing ribs (98) are arranged in the fuel heat exchange chamber (94), two ends of the fuel chamber heat exchange reinforcing ribs are respectively fixed on the inner circumferential surface of the additional shell (101) and the outer circumferential surface of the composite rear cartridge receiver shell (97), a plurality of fuel chamber heat exchange reinforcing ribs are arranged on the heat exchange chamber heat exchange reinforcing ribs (98), and a plurality of fuel chamber heat exchange ) All the integral central symmetry planes of the heat exchange reinforcing ribs (98) of the fuel heat exchange chamber pass through the central axis of the composite rear casing shell (97), two openings which are separated by the circumference and are opposite to each other are arranged between the walls of the additional shell (101), a fuel heat exchange rear output flange interface (1c) and a fuel heat exchange front input flange interface (1b) are respectively arranged and fixed on the two openings on the outer surface of the additional shell, the two flange interfaces are directly communicated with the inside of the fuel heat exchange chamber (94), a composite rear casing bearing sleeve (96) which is positioned in the center of the composite rear casing shell (97) and has the same central axis with the composite rear casing shell (97) is in supporting connection with a plurality of composite rear casing supporting spokes (102) on the outer surface of the side of the composite rear casing bearing sleeve (96) by fixing the two ends on the inner wall surface of the composite rear casing shell (97) respectively, a plurality of composite rear case bearing sleeve through holes (96a) are formed in a sleeve body of the hollow cylindrical composite rear case bearing sleeve (96) along the direction parallel to the central axis of the composite rear case bearing sleeve (96), the central axes of all the composite rear case bearing sleeve through holes (96a) are arranged on the same circumferential surface with the central axis of the composite rear case bearing sleeve (96) as the central axis, the end surfaces of the two sides of the composite rear case bearing sleeve (96) are respectively arranged in the plane extension surfaces of the outer end surfaces of the composite rear case rear end panel (95) and the composite rear case front end panel (100), and the central symmetry surface parallel to the large-area surface of the composite rear case support spoke (102) in a flat strip shape passes through the central axis of the composite rear case bearing sleeve (96).
6. The bi-modal full-speed fully adaptive variable cycle jet aero-jet engine of claim 1 wherein: the power unit (23) in the thrust jet (1) comprises a power turbine disk (65), a jet ring (68) and a power ring (67), wherein the power turbine disk (65) with a power turbine disk key groove (65a) is positioned at the center of the power unit (23), the outer surface of the circumference side of the power turbine disk (65) is provided with a plurality of roots of power turbofan blades (66), the tops of the power turbofan blades (66) are fixedly arranged on the inner wall surface of the circumference side of a power ring base (67d) on the power ring (67), the power ring base (67d) is provided with a plurality of power ring saw-shaped teeth (67a) and power ring tooth grooves (67c) with the same rotating direction, a power ring tooth groove (67c) is formed between two adjacent power ring saw-shaped teeth (67a), and the power ring tooth groove (67c) consists of a plane passing through the central axis of the power ring (67) and another plane vertical to the plane, the two sides of the power ring tooth groove (67c) are power ring tooth groove protecting edges (67b), and the power ring tooth groove protecting edges (67b) are the remaining parts which are not removed and remain after the space volume of the power ring tooth groove (67c) is removed to the outer surface of the circumference side of the cylindrical ring body of the power ring (67) in the range of being less than the width of the outer surface of the circumference side of the power ring (67); the spraying ring (68) is surrounded outside the power ring (67), the power ring (67) and the spraying ring (68) share a central axis, a certain gap is reserved between the power ring and the spraying ring, the spraying ring (68) is in a hollow circular ring shape, one end of the outer surface of the circumference side of the spraying ring is fixedly provided with a power unit rear connecting flange (23b), and the other end of the outer surface of the circumference side of the spraying ring is fixedly provided with a power unit front connecting flange (23 a); the spray ring (68) comprises a spray ring spray cavity (68b) and a spray ring spray channel (68a), the closed space inside the hollow spray ring (68) is the spray ring spray cavity (68b), a plurality of power unit high-pressure gas input ports (69) which are annularly arranged are formed in the end surface of the connecting flange (23b) after the power unit is installed and fixed on the hollow spray ring (68), and the power unit high-pressure gas input ports (69) enable the inner space where the spray ring spray cavity (68b) is located to be communicated with the space outside the end surface of the spray ring (68) where the spray ring spray cavity is located; a plurality of spray ring spray channels (68a) are arranged between the thicker ring body walls of the radial inner layers of the spray ring spray cavities (68b), the spray ring spray channels (68a) enable the inner space of the spray ring spray cavities (68b) to be communicated with the space inside the inner surface of the circumferential side of the spray rings (68), and the pointing directions of all the spray ring spray channels (68a) are consistent according to the same clockwise rotation direction; the spray ring spray channel (68a) consists of two parallel planes which are parallel to the central axis of the spray ring (68) and two opposite transitional arc surfaces between the two parallel planes, and the shape of the section of the spray ring spray channel in the section passing through the central axis of the spray ring (68) is the section (68c) of the spray ring spray channel; a sectional line of the plane of the inner wall of the spray channel (68a) of the spray ring, which is farthest from the central axis of the spray ring (68), in a sectional plane perpendicular to the central axis of the spray ring (68), is tangential to a circumferential line of the inner surface of the inner circumference of the spray ring (68) in the sectional plane.
7. The bi-modal full-speed fully adaptive variable cycle jet aero-jet engine of claim 1 wherein: the combustion unit (25) in the thrust jet (1) comprises an annular combustion chamber shell (70), an inner wall surface (73) on the circumferential side of the annular combustion chamber and an ignition device (77), wherein the surface of the inner wall surface (73) on the circumferential side of the annular combustion chamber is covered by a lining heat insulation layer (73a), the outer surface of the annular combustion chamber shell (70) is covered by a shell heat insulation layer (70a), one end of the annular combustion chamber shell is fixedly provided with a combustion unit front connecting flange (25a), and the other end of the annular combustion chamber shell is fixedly provided with a combustion unit rear connecting flange (25 b); the annular combustion chamber shell (70) and the inner wall surface (73) at the circumferential side of the annular combustion chamber, the front end panel (72) of the annular combustion chamber and the rear end panel (71) of the annular combustion chamber form an enclosed inner space, namely an annular combustion chamber (75), a plurality of ignition devices (77) which are arranged on the same circumferential surface are installed and fixed between the walls of the middle part of the annular combustion chamber shell (70), and the ignition devices (77) extend into the annular combustion chamber (75); a plurality of high-pressure gas output ports (76) which are distributed annularly are formed in the front end panel (72) of the annular combustion chamber, a plurality of mixed raw material input ports (74) which are arranged annularly are formed in the rear end panel (71) of the annular combustion chamber, the outward end plane of the front connecting flange (25a) of the combustion unit and the outer end face of the front end panel (72) of the annular combustion chamber are in the same plane, and the outward end plane of the rear connecting flange (25b) of the combustion unit and the outer end face of the rear end panel (113) of the annular combustion chamber are in the same plane.
8. The bi-modal full-speed fully adaptive variable cycle jet aero-jet engine of claim 1 wherein: the raw material preparation unit (27) in the thrust jet (1) comprises a raw material preparation unit circumferential shell (86) and an air preparation chamber (78), wherein a plurality of openings are formed among the walls of the raw material preparation unit circumferential shell (86), a combustion air input flange interface is correspondingly arranged and fixed on each opening on the outer surface of the raw material preparation unit circumferential shell, namely a combustion air input 1 st flange interface (1a) and a combustion air input 2 nd flange interface (1d), a raw material preparation unit front connecting flange (27a) is arranged and fixed at one end of the outer surface of the raw material preparation unit circumferential shell, a raw material preparation unit rear connecting flange (27b) is arranged and fixed at the other end of the outer surface of the raw material preparation unit circumferential shell, a raw material preparation unit circumferential inner wall (84) with the same central axis as the raw material preparation unit circumferential shell, a raw material preparation unit rear end panel (83) and a raw material preparation unit front, the middle of the ring body is divided into an air preparation chamber (78) and a raw material mixing chamber (81) which are relatively independent by a separating ring (79) which is coaxial with the circumferential inner wall (84) of the raw material preparation unit, two ends of a separating ring (79) are respectively fixed on the inner wall surfaces of a rear end panel (83) of the raw material preparation unit and a front end panel (85) of the raw material preparation unit, an air preparation chamber (78) surrounds a raw material mixing chamber (81), a plurality of air distribution holes (79a) which are arranged in a sieve mesh shape are arranged on the separating ring (79), a plurality of fuel nozzle insertion holes (82) with the central axis on the same circumferential surface are arranged on the rear end panel (83) of the raw material preparation unit at the raw material mixing chamber (81), a plurality of raw material preparation unit mixed raw material output ports (80) which are arranged in a ring shape are arranged on a front panel (85) of the raw material preparation unit at the raw material mixing chamber (81).
9. The bi-modal full-speed fully adaptive variable cycle jet aero-jet engine of claim 1 wherein: the fuel preparation unit (29) in the thrust jet (1) comprises a raw material preparation unit circumferential shell (91), a fuel preparation chamber (88) and a fuel nozzle (87), the fuel preparation chamber (88) is a space which is formed by sealing a raw material preparation unit circumferential shell (91), a fuel preparation unit circumferential inner wall (89) which has the same central axis with the raw material preparation unit circumferential shell, a fuel preparation unit front end panel (92) and a fuel preparation unit rear end panel (93) together, a plurality of fuel heat exchange reinforcing ribs (90) are arranged in the fuel preparation chamber (88), two ends of the fuel heat exchange reinforcing ribs are respectively fixed on the inner surface of the raw material preparation unit circumferential shell (91) and the outer surface of the fuel preparation unit circumferential inner wall (89), a plurality of fuel heat exchange reinforcing rib overflowing holes (90a) are formed in the fuel heat exchange reinforcing ribs (90), and the integral central symmetrical plane of the fuel heat exchange reinforcing ribs (90) passes through the central axis of the; the circumferential shell (91) of the fuel preparation unit is provided with an opening between the walls, the outer surface of the circumferential shell is fixedly provided with a fuel heat exchange rear input flange interface (1e) which is directly communicated with the interior of the fuel preparation chamber (88), the circumferential surface of one side surface of the outer surface of the circumferential shell, which is close to the front end panel (92) of the fuel preparation unit, is fixedly provided with a fuel preparation unit front connecting flange (29a), and the circumferential surface of one side surface of the outer surface of the circumferential shell, which is close to the rear end panel (93) of the fuel preparation unit, is fixedly provided with a fuel preparation unit rear connecting flange (; a plurality of fuel nozzles (87) having the same circumferential axis are fixed between the walls of the front end plate (92) of the fuel preparation unit, and the fuel nozzles (87) communicate the inside and outside of the fuel preparation chamber (88).
10. The bi-modal full-speed fully adaptive variable cycle jet aero-jet engine of claim 1 wherein: the main shaft in the thrust jet (1) and the auxiliary part (34) surrounding the main shaft comprise a main shaft (34a), a front bearing (115) and a rear bearing (110), the front bearing (115) is installed in a front casing bearing sleeve (63), the rear bearing (110) is installed in a composite rear casing bearing sleeve (96), the front part and the rear end of the main shaft (34a) are respectively installed and fixed between the front bearing (115) and the rear bearing (110), the front end face and the rear end face of the front bearing (115) are respectively covered with a front bearing front cover (116) and a front bearing rear cover (114), the front bearing front cover (116) and the front bearing rear cover (114) are fixed on the two end faces of the front casing bearing sleeve (63) through front bearing cover fixing bolt nuts (113), the front end face and the rear end face of the rear bearing (110) are respectively covered with a rear bearing front cover (111) and a rear bearing rear cover (109), and the rear bearing front cover (111) and the rear bearing rear cover (109) are fixed on the composite rear casing bearing through rear bearing cover fixing bolt nuts (108) The root part of a tail spray fairing (107) is fixedly arranged on the two end surfaces of the sleeve (96) and the upper surface of a rear bearing rear cover (109); a 1 st pin key (117) is arranged between the power generation turbofan chassis (56) in front of the front bearing (115) and the main shaft (34a) to ensure that the power generation turbofan chassis (56) synchronously rotates along with the main shaft (34a), and a shaft head shunt cover (118) is fixed on a shaft head of the main shaft (34a) in front of the power generation turbofan chassis (56); a2 nd pin key (119) is arranged between the power turbine disc (65) behind the front bearing (115) and the main shaft (34a) to ensure that the power turbine disc (65) rotates synchronously with the main shaft (34a), and a 3 rd pin key (120) is arranged between the additional turbofan (35) and the main shaft (34a) to ensure that the additional turbofan (35) rotates synchronously with the main shaft (34 a).
11. The bi-modal full-speed fully adaptive variable cycle jet aero-jet engine of claim 1 wherein: the thrust jet (1) is characterized in that a combustion unit high-pressure gas output port (76) in a combustion unit (25) of the thrust jet is communicated with a power unit high-pressure gas input port (69) in a power unit (23); a combustion unit mixed raw material input port (74) in the combustion unit (25) and a raw material preparation unit mixed raw material output port (80) in the raw material preparation unit (27) are communicated with each other; the fuel nozzle (87) in the fuel preparation unit (29) extends into the fuel mixing chamber (81) in the raw material preparation unit (27) through the fuel nozzle insertion hole (82) in the raw material preparation unit (27), and sealing gaskets (112) are padded around the fuel nozzle (87) and between the raw material preparation unit (27) and the combustion unit (25); the inner wall surfaces of the circumference of 9 parts in total, namely a small straight cylinder air inlet pipe (123) in a thrust air inlet pipe (15), a pressure sharp disk (55) in a power generation unit (19), a front casing shell (61) in a front casing (21), a power ring (67) in a power unit (23), a lining heat insulation layer (73a) in a combustion unit (25), a raw material preparation unit circumference inner wall (84) in a raw material preparation unit (27), a fuel preparation unit circumference inner wall (89) in a fuel preparation unit (29), a composite rear casing shell (97) in a composite rear casing (32) and a tail nozzle circumference inner wall (106) in a tail nozzle (33) are basically on the same circumference surface with the central axis of a main shaft (34a) as the central axis, and a space formed in the common circumference surface is an air duct arranged in the thrust air jet (1).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011075279.1A CN112160847A (en) | 2020-10-10 | 2020-10-10 | Bimodal full-speed full-adaptive variable-cycle rotary jet type aviation jet engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011075279.1A CN112160847A (en) | 2020-10-10 | 2020-10-10 | Bimodal full-speed full-adaptive variable-cycle rotary jet type aviation jet engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114934857A (en) * | 2022-07-21 | 2022-08-23 | 中国航发四川燃气涡轮研究院 | Variable-cycle turbine engine |
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2020
- 2020-10-10 CN CN202011075279.1A patent/CN112160847A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114934857A (en) * | 2022-07-21 | 2022-08-23 | 中国航发四川燃气涡轮研究院 | Variable-cycle turbine engine |
| CN114934857B (en) * | 2022-07-21 | 2022-12-20 | 中国航发四川燃气涡轮研究院 | Variable-cycle turbine engine |
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