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Due to the limitation of space and workload, only the summary information of the first 10 technologies will be displayed on each page, and more information and detailed full-text materials will be provided in the form of CD-ROM. This CD contains "143 pieces of patented technology" at a charge of 198 yuan.
[kj6290-0087-000 1] shaped charge engine
[Abstract] A shaped charge engine includes an annular combustion chamber (3) consisting of an inner shell (1) and an outer shell (2). The central through hole in the inner shell (1) allows exhaust gas to be discharged. The housing includes a generally circular disk having an inner conical groove and a through hole for inserting a fuel injector and an igniter. The jet forming the combustion chamber is preferably conical, and as it gradually rises to the top, the bottom becomes wider and the cross section becomes smaller. This structure forms a circular narrow point or throat toward the top, which forms the main compression zone. The second compression zone is formed at the top of the outer shell, just outside the throat. When the roughly opposite exhaust streams collide with each other and are forced to discharge the through hole in the inner shell, hypersonic gas is generated. Shaped charge engines can be used in different applications, such as pulse direct propulsion devices, eddy current drives or various tools and equipment.
[kj6290-0052-0002] Nozzle control lock in case of hydraulic failure
[Abstract] A method for locking the position of the exhaust nozzle of a jet engine in a hydraulic system uses a nozzle driver (1 16) connected by a synchronous cable. The synchronous cable (1 16) is engaged with the conical brake locking mechanism (120) to prevent the cable from rotating in case of hydraulic failure. Nozzle (126) is locked in place to prevent hydraulic failure. This prevents the effective thrust from being significantly reduced.
[kj6290-00 15-0003] powder engine
The invention relates to a gunpowder engine, which converts the energy generated after gunpowder deflagration into mechanical energy and outputs it to do work. It can be used as a fixed power source and other power sources. The invention consists of an engine body and a transmitter body. For safety reasons, the engine block is equipped with a safety valve. Different from the internal combustion engine, the invention does not complete the work cycle of loading, pressing, blasting and unloading, but uses the flywheel inertia to receive the energy output generated by the explosion of gunpowder after firing in the launcher to do work. Power engine has the advantages of simple structure, small volume, large output power, low power loss and high efficiency, and can be used as power source for power generation, irrigation and drainage, and also as special power source.
Scramjet
The invention relates to an engine, in particular to a scramjet engine for aerospace. It comprises a shell, a support plate, an inner nozzle and a spark plug. The inner cavity wrapped by the shell is divided into three parts: air inlet, combustion chamber and nozzle. The connection between the air inlet and the combustion chamber is very thin, forming a throat. Characterized in that an outer nozzle is installed in front of the throat, so that the gas entering the combustion chamber from the air inlet behind the outer nozzle is a combustible mixture of air and fuel. It has the characteristics of simple structure, low cost and high fuel combustion efficiency, which can reduce the length of the combustion chamber and improve the mixing efficiency of fuel and high-speed airflow entering the combustion chamber.
【 kj6290-00 18-0005 】 Adjustable area thrust reverse cascade with drooping regulating blades.
[Abstract] A plurality of cascade blades (28, 29, 30) for turning the flow (20) are equipped with at least one flow regulating blade (36), which turns in the opposite direction relative to the cascade blades within the reverse rotation range of the turning air flow. When the cascade blades (28, 29, 30) and the flow regulating blades (36) try to obtain a device for blocking the airflow in the stowed position,
[kj6290-0053-0006] jet engine
In a jet engine with a conventional propeller (9), the second combustion chamber (5) is arranged downstream of the turbine (4), and the second turbine (6) operates downstream of the second combustion chamber (5). The hot gas (16) is partially expanded in the first turbine (4) and then reheated in the second combustion chamber (5). At lower absolute hot gas temperature, the engine can output more power.
Replacement method of abradable parts on turbojet fan casing.
Abstract: The present invention provides a simple and low-cost method to replace the abradable parts on the fan casing of turbojet engine. This method has a remarkable effect, because the internal heating belt (100) and the fan-shaped brackets (1 10) are placed close to the rubable part (80), and each fan-shaped bracket includes an inflatable soft shell (120). The rubable part (80) and the internal heating belt (100) are completely sandwiched between the fan casing (60) and the soft casing (120), and the fan bracket (1 10) is composed of a plurality of belts (125).
[kj6290-0040-0008] Oxygen/oil swirl burner
The liquid burner (10) is provided with a central fuel outlet (18) and a plurality of oxygen outlets (22), the shape and position of which can be used to generate a convergent and rotating oxygen flow, which can be combined with any liquid fuel injected from the fuel outlet (18). This oxygen/fuel interaction will produce two combustion zones and recirculation effect, which will contribute to the complete or almost complete combustion of undesirable exhaust gas components. Oxygen and fuel are preferably supply such that their speeds are approximately equal at that point where the two combustion zone meet.
【 kj6290-0098-0009 】 Controllable hot fish scale adjusting plate for axisymmetric nozzle of turbojet engine.
[Abstract] The controllable hot fish scale adjusting plate can reduce the wear on the friction surface of the fish scale adjusting plate with nozzle sealing structure and improve the adhesion degree here. The friction surface (24) of the controlled hot fish scale adjusting plate is made of metal, just like the nozzle sealing structure, so it can be combined together in the process of casting the bracket (29) of the hot fish scale adjusting plate or added by mechanical means. The friction surface (24) includes an upright side surface (25) which can reduce the gap between each controlled hot fish scale adjuster and its adjacent subsequent fish scale adjuster. The invention can be applied to a nozzle of a turbojet engine.
[kj6290-0059-00 10] fuel atomizing nozzle
[Abstract] A fuel atomizing nozzle comprises a nozzle sleeve, a nozzle body and a needle valve. The nozzle body is installed in the nozzle sleeve, the needle valve is installed in the inner hole of the nozzle body, and the end flanges of the nozzle body and the needle valve are respectively provided with oil holes. An oil passage is formed between the nozzle sleeve and the front conical surface of the nozzle body, and another oil passage is formed between the nozzle body and the needle valve. Spiral oil grooves are formed on the outer circumferential surface of the flange of the nozzle body and also on the outer circumferential surface of the flange of the needle valve. It can be used in aero-turbine, turbojet, turbofan, turboprop, turboshaft, ramjet and other engines.
[kj 6290-0070-0011] a jet rotor engine.
High overload solid rocket motor for cannonball
[KJ6290-0126-0013] Jet Vortex Aircraft
[kj 6290-0135-0014] diffuser with tornado dune combined stabilizer
Mixed pressure pulse detonation injection device
[kj6290-0043-00 16] multi-rotor bypass turbofan engine
[kj6290-0035-00 17] Method and device for automatically providing rated thrust of jet engine for avionics system.
[KJ6290-0100-0018] Method and device for reducing the stress of turbine engine nozzle bottom plate.
[kj 6290-0016-0019] binary exhaust nozzle diffuser drive system.
Thrust-controllable jet supercharged pulse detonation engine and the method of improving its thrust.
[kj6290-0102-0021] Engine based on fuel injector.
[kj6290-0088-0022] jet engine accessories
Model mega launch propeller
[kj6290-0 129-0024] rocket engine accessories
[kj6290-0027-0025] Winding forming method of fiber winding shell of solid rocket motor with reverse nozzle joint.
[kj6290-0084-0026] Micro turbojet engine
[kj6290-0089-0027] Engine with main force and reaction force doing work
[kj 6290-0115-0028] gas turbine with variable compression ratio fan system
[kj6290-000 1-0029] liquid fuel rocket engine
[kj6290-0 128-0030] atomized carburetor for jet engine
[kj6290-0064-003 1] Ablative material of rocket assembly based on cellulose staple fiber and its thermal insulation and protection. ...
[kj6290-0 109-0032] Elastomer phenolic resin ablative thermal insulation material for rocket engine.
[kj6290-00 19-0033] Rotating Power Machinery Structure and Series Engines
[kj6290-0078-0034] Pressure-driven joint system
[kj6290-0 137-0035] Combined turbofan ramjet engine
[kj6290-0118-0036] metal plate, including the device for fixing it to the supporting device and the sealing washer.
[kj6290-0086-0037] rocket engine accessories
[kj6290-0033-0038] impact jet engine
[kj6290-0057-0039] Vector nozzle calibration
Ramjet engine for power generation
[kj6290-0054-004 1] direct power machine
High energy jet engine.
[kj6290-0028-0043] Material and structure of combustible rocket shell and nozzle.
[kj6290-0009-0044] Multi-propellant aircraft and propulsion system
[kj6290-0030-0045] Marine jet engine
【 kj6290-0 1 13-0046 】 Dual counter-rotating fan turbojet engine.
Spacecraft low pressure reaction control propulsion system.
【 kj6290-0005-0048 】 Tangential lift channel turbofan engine.
[kj6290-0048-0049] rocket engine nozzle
[kj6290-006 1-0050] composite heat exchanger and its manufacturing method
Manufacturing method of rocket engine outlet nozzle [kj6290-0067-005 1]
From [kj6290-0042-0052] convertible jet cooling nozzle.
Source [kj6290-0 1 12-0053] Turbojet engine structure with two fans at the front end.
: [kj6290-00 12-0054] Thrust-guided exhaust nozzle device
【 kj6290-0 133-0055 】 Water-oil mixed combustion high-efficiency and energy-saving infrared silencing flight marine submersible engine.
Thermal insulation method of solid propellant rocket engine shell [kj6290-009 1-0056]
Double-door thrust commutator device with [kj6290-0039-0057].
[kj6290-0046-0058] Nozzle hollow actuating ring
Operate [kj6290-0 105-0059] multi-rotor ducted turbofan engine.
Low power arc jet propellant supply system
Technology [kj6290-005 1-006 1] Gas turbine nozzles, power generation gas turbines, cobalt-based alloys and welding materials.
Net [kj6290-0093-0062] new fuel atomizing nozzle
【 kj6290-0 127-0063 】 Jet engine tail nozzle device capable of changing thrust direction in all directions.
W [kj6290-004 1-0064] temperature-controlled rocket nozzle
W [kj6290-0077-0065] plug nozzle
Jet Air-breathing Engine and Its Application in Aircraft
[kj6290-0007-0067] Nozzle adjuster support device
S [kj6290-008 1-0068] Recoil Rotor Engine
Y [kj6290-0 142-0069] superman flying motorcycle
Direct injection engine
S [kj6290-0073-007 1] Hypersonic Vortex Turbocharged Propulsion Engine
Axisymmetric controllable exhaust nozzle
J [kj6290-0072-0073] Device for controlling heat transfer to nozzle sidewall in expander cycle rocket engine.
Manufacturing method of model rocket engine
C [kj6290-0045-0075] Operation method of supersonic jet engine hybrid power plant
O [kj 6290-0116-0076] turbojet engine, including subsystem connecting arm and subsystem connecting arm.
M [kj6290-0038-0077] double-flow tangential inlet nozzle
[kj6290-0076-0078] gas turbine and its combustion chamber
Electromagnetic propulsion gas injection engine
System [KJ6290-0110-0080] is a method and device for assembling gas turbine engines.
Electric [KJ 6290-0104-0081] A device for reducing exhaust noise of jet engine by oscillating fuel injector.
[kj6290-00 17-0082] Connecting Rod Thrust Reversing Cascade with Adjustable Area
: [kj6290-0095-0083] Nozzle with intensifier conduit
0 [kj 6290-0011-0084] gas nozzle with cooling air converter
7 [kj6290-0 132-0085] Multistage Intake Jet Engine
5 [kj6290-0 123-0086] Jet Walking Shoes
5 Coolable metal plate
| [kj6290-0063-0088] Modular solid fuel rocket propellant charge with jacket, charging and discharging system, cooling device and pylon.
8 [kj6290-0 103-0089] Compact fixing ring and pin for connecting nozzle bushing wall and its fixing method
8 [kj6290-00 14-0090] thrust reverse cascade with adjustable area
5 [KJ 6290-0124-0091] Constant Volume Combustion Jet Propulsion
8 [kj6290-0020-0092] Gas * * * vibration device
6 [kj6290-0094-0093] Herringbone jet and configurable heat shield are used to reduce jet noise.
1 [kj6290-0079-0094] thrust control valve with reduced gain
5 [kj6290-00 13-0095] Cooling Bushing of Nozzle Lug
3 [kj6290-0024-0096] Device and method for reducing differential pressure load of afterburner gas turbine engine
[kj 6290-0114-0097] turbine engine device and method
[kj6290-0025-0098] annular jet engine
[kj6290-0047-0099] Axisymmetric directional nozzle actuation system with multiple power control circuits.
[kj6290-0066-0 100] Nozzle structure of rocket nozzle with cooling nozzle wall.
[kj 6290-0032-0101] jet rotor engine
[kj 6290-0121-0102] annular jet engine
[kj 6290-0141-0103] compound ramjet turbofan engine
[kj6290-0002-0 104] pulsating sonic jet burner
[kj 6290-0134-0105] gas turbine gas generator bleed valve
【 kj6290-0008-0 106 】 Positioning method of convergence adjusting plate and coaxial arc disk and connecting rod system.
Frequency adaptive control method and device for pulse engine.
[kj6290-0097-0 108] Micro chemical propeller with pressure sensor
【 KJ6290-011-0109 】 Three-axis bypass turbojet engine with high bypass ratio.
[kj 6290-0060-0110] nozzle ramjet engine
Long-life nozzle guide plate for aviation turbojet engine
Hydrogen-oxygen rocket engine commercial launch vehicle
[KJ6290-0130-01KLOC-0/3] Assembled rocket engine for artificial precipitation enhancement and hail suppression
[kj 6290-0139-0114] turbofan-assisted ramjet engine
[kj 6290-0003-0115] differential pressure propeller
[kj 6290-0125-0116] jet rotor engine
[kj 6290-0056-0117] vector nozzle control system
[kj 6290-0101-0118] tail flade engine
[KJ6290-0074-0119] Ablative material for rocket components made of solution-spun cellulose matrix and rocket components using this material for thermal insulation or thermal protection. ...
[kj6290-0034-0 120] detachable super fan engine
[kj 6290-0122-0121] gas-phase pulse shock wave generator
[kj 6290-0131-0122] counter-rotating gear jet engine
[kj6290-0050-0 123] combined jet engine
[kj 6290-0117-0124] rocket engine
[kj 6290-0119-0125] turbine ring
[kj 6290-0031-0126] centrifugal gas injection tube
[kj6290-0026-0 127] air compression reflection engine with wind wheel flight
Method and device for operating a gas turbine engine
[KJ6290-0021-0129] Symmetric axis steering exhaust nozzle sealing device.
【 kj6290-007 1-0 130 】 Device for controlling air separation line in rocket engine nozzle.
Elastomer phenolic resin ablative thermal insulation material for rocket engine
[kj6290-0023-0 132] yaw thrust steering nozzle
[kj6290-0049-0 133] Large-capacity pilot pump shunt device
[kj6290-0069-0 134] rocket engine
Multi-propellant aircraft and propulsion system
【 kj6290-0082-0 136 】 Method of burning combustible gas underwater and marine engine.
[kj6290-0036-0 137] Synchronous shaft locking mechanism of reverse thrust device.
[kj6290-0096-0 138] Method for preparing composite attitude and orbit control thrust chamber by precursor impregnation and pyrolysis process.
【 kj6290-0 108-0 139 】 Pulse deflagration power system and equipment with fuel pretreatment.
【 kj6290-0065-0 140 】 The nozzle profile of rocket engine is used to control airflow diffusion and reduce lateral load.
Electronic injection valve adaptive pulse jet engine device and control method
[kj6290-0055-0 142] rotary combustion chamber jet engine
[kj 6290-0143-0143] new fuel atomizing nozzle
Due to the limitation of space and workload, only the summary information of the first 10 technologies will be displayed on each page, and more information and detailed full-text materials will be provided in the form of CD-ROM. This CD contains "143 pieces of patented technology" at a charge of 198 yuan. [Online Order] [Subject Description]
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