CN105952538A - Micro turbojet engine - Google Patents
Micro turbojet engine Download PDFInfo
- Publication number
- CN105952538A CN105952538A CN201610259496.3A CN201610259496A CN105952538A CN 105952538 A CN105952538 A CN 105952538A CN 201610259496 A CN201610259496 A CN 201610259496A CN 105952538 A CN105952538 A CN 105952538A
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- China
- Prior art keywords
- jet engine
- turbine jet
- micro turbine
- motor
- diffuser
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000001914 calming effect Effects 0.000 claims description 15
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 5
- 239000002828 fuel tank Substances 0.000 claims description 5
- 229910052744 lithium Inorganic materials 0.000 claims description 5
- 238000009792 diffusion process Methods 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims 1
- 238000002485 combustion reaction Methods 0.000 abstract description 3
- 239000003921 oil Substances 0.000 description 34
- 230000005611 electricity Effects 0.000 description 5
- 238000009434 installation Methods 0.000 description 4
- 239000003350 kerosene Substances 0.000 description 4
- 239000007789 gas Substances 0.000 description 3
- 206010037660 Pyrexia Diseases 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008450 motivation Effects 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- FGRBYDKOBBBPOI-UHFFFAOYSA-N 10,10-dioxo-2-[4-(N-phenylanilino)phenyl]thioxanthen-9-one Chemical compound O=C1c2ccccc2S(=O)(=O)c2ccc(cc12)-c1ccc(cc1)N(c1ccccc1)c1ccccc1 FGRBYDKOBBBPOI-UHFFFAOYSA-N 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 239000000443 aerosol Substances 0.000 description 1
- 238000004378 air conditioning Methods 0.000 description 1
- 230000001174 ascending effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 238000005286 illumination Methods 0.000 description 1
- 230000005389 magnetism Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000010899 nucleation Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000005413 snowmelt Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
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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
- F02C7/26—Starting; Ignition
-
- 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
-
- 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
-
- 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
- F02C7/12—Cooling of plants
-
- 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
-
- 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
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
-
- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K5/00—Casings; Enclosures; Supports
- H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
- H02K5/16—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields
- H02K5/167—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields using sliding-contact or spherical cap bearings
- H02K5/1677—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields using sliding-contact or spherical cap bearings radially supporting the rotor around a fixed spindle; radially supporting the rotor directly
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention discloses a micro turbojet engine. The micro turbojet engine comprises a compressor box, a cowling, a housing and a shaft. The cowling is disposed on the end of the housing, and the compressor box is disposed on the center position of the cowling. The shaft is disposed rotationally on the axis position of the housing, a compressor impeller is disposed on the end closed to the compressor box of the shaft, and a turbine is disposed on the other end. A combustion chamber is disposed between the compressor impeller and the turbine, and a diffuser is disposed between the compressor impeller and the combustion chamber. A motor is disposed between the compressor impeller and the diffuser, and the compressor impeller comprises a blade fixed face. The blades are fixed uniformly on the blade fixed face. The design can reduce the loss of air pressure impact, and the motor is disposed between the compressor impeller and the diffuser, so that the motor is used as a starting motor and a generator. The micro turbojet engine is convenient to start, and the started motor changes to be the generator, so that the micro turbojet engine can be used as two ways.
Description
Technical field
The present invention relates to whirlpool eruption motor, erupt motor particularly to a kind of miniature whirlpool.
Background technology
Micro Turbine Jet Engine refers to thrust turbojet below 100 kilograms, and jet turbine is sent out
Motivation is with air as medium, mixes combining combustion with fuel oil and produce High Temperature High Pressure after overcompression in combustor
Combustion gas, converts chemical energy into the power set into mechanical energy by turbine.By the Land use systems to its energy
It is divided into turbojet, turbofan, turboprop, turboaxle motor.
Micro Turbine Jet Engine is applied widely in ground force field, specific as follows, 1. as middle-size and small-size aircraft
Power, such as unmanned plane, target drone, target, guided missile, bait bullet, paraglider etc..2. as naval vessel, tank,
Auxiliary power on large aircraft, such as air conditioning power, naval vessel local dynamic effect, speedboat or the power of small-sized vessel.
3. as heating power, hot gas source.Such as ice-melt snow melt, aerostatics qi of chong channel ascending adversely, power supply heating etc. of camping.4. as little
Type generation driving force such as mobile radar generates electricity, emergent charging, the power of the electromotors such as illumination；The most various minicomputers
The power of tool, the infrared first generator of target, military aerosol generator, electronic countermeasure chaff seeding device etc..
Existing Micro Turbine Jet Engine include calming the anger casing, trousers, compressor impeller, diffuser, axle,
Combustor, turbine and housing, existing Micro Turbine Jet Engine is pneumatic startup, without motor, during startup not
Convenient, and not there is generating function, and also the design of its compressor impeller is unreasonable, to gas in work process
Stream impact loss is bigger.Existing Micro Turbine Jet Engine and electronic control system (ECU) and oil supply system knot
Conjunction is operated, and it mainly includes that temperature sensor, velocity sensor, Micro Turbine Jet Engine master are mechanical, electrical
Magnet valve, fuel tank, oil pipe, oil pump, display, lithium battery, control system module (ECU), electric wire.By
More than can be seen that automatically controlled part and oil supply system connect complex, some parts such as oil pump, control system
Module (ECU) etc. has Heavy Weight and volume relatively big, adds production cost, and causes the eruption of miniature whirlpool dynamic
Machine performance reduces, and bad installation.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of startup conveniently, can generate electricity after startup, lightweight,
Compressor impeller is reasonable in design little to gas shock loss, and is applied in combination the miniature whirlpool spray taking up room little
Electromotor.
In order to solve above-mentioned technical problem, the technical scheme is that a kind of Micro Turbine Jet Engine, bag
Including casing of calming the anger, trousers, housing and axle, described shell one end arranges trousers, described trousers
Center arranges casing of calming the anger, and what described housing axial location can rotate arranges axle, and described axle is close
Calm the anger one end of casing is provided with compressor impeller, and the other end is provided with turbine, described compressor impeller and whirlpool
Be provided with combustor between wheel, between described compressor impeller and combustor, be provided with diffuser, described in calm the anger
Being provided with motor between machine impeller and diffuser, described compressor impeller includes blade stationary plane, described
Being fixed with blade on blade stationary plane uniformly, described blade includes primary blades and time blade.
Further, described motor includes that rotor and motor stator, described rotor are permanent magnetism
DC motor rotor, described motor stator is permanent magnet DC motor stator.
Further, described axle is fixed by the bearing chamber being fixed on housing, described rotor
Being fixed on axle, described motor stator is fixed on described bearing chamber.
Further, described diffuser is collar plate shape, and it is sleeved on described bearing chamber.
Further, described diffuser is provided with the projection for diffusion near the side of motor stator.
Further, described protruding inclination is uniformly arranged multiple, and its side is linear type, and opposite side is
Circular arc type, described projection is arranged on diffuser edge near internal position.
Further, described housing is provided with blast cap, described blast cap inside the one end away from casing of calming the anger
For cone.
Further, described calming the anger is provided with receiving space, described receiving between casing and described trousers
Electromagnetic valve, oil pump and control system module, described control system module and described electricity it is provided with in space
Magnet valve and oil pump electrical connection.
Further, being connected with the fuel tank being arranged on outside by oil pipe of described oil pump, described electricity
Magnet valve is connected on the oil-out of oil pump by oil pipe, described control system module be arranged on hull outside
Lithium battery and display electrical connection.
Further, described control system module is provided with the capillary oil pipe drawn from oil pump oil-out.
The blade having the beneficial effect that described compressor impeller obtained by the technique scheme present invention is fixed
Be fixed with primary blades and time blade on face uniformly, this design can well the loss of less air pressure impact,
The bigger overall performance that improve whole product, described Micro Turbine Jet Engine changes into pneumatic startup brushless
Permanent magnet DC motor starts, and the installation site of permanent magnet DC motor be placed on compressor impeller and diffuser it
Between, make motor double as starting motor and electromotor, not only facilitate Micro Turbine Jet Engine to start, and start
After motor become electromotor so that it is dual-use, the most no longer work after solving electric motor starting waste
The problem of resource, makes generated energy increase, and the present invention can make generated output reach 400W.The present invention by diameter and
Length is little, the suitable oil pump of flow, electromagnetic valve, control system module be integrated into trousers and calm the anger casing it
Between position, both reduced turbojet engine complete machine weight, and improve Micro Turbine Jet Engine performance.Control
System module processed is integrated into inside Micro Turbine Jet Engine, uses an aviation plug to replace various connection electric wires
With external connection, not only decrease the volume and weight of Micro Turbine Jet Engine, and facilitate miniature whirlpool to erupt
Motivation and outside connection and installation.Trousers and calming the anger between casing during the work of this Micro Turbine Jet Engine
Cavity temperature is between 70 DEG C-85 DEG C, and control system module can be normal in the temperature within 150 DEG C
Work.During work, it is contemplated that control system module operationally self there will be fever phenomenon, therefore,
Full capillary oil pipe in control system module, allows from oil pump kerosene out through this capillary oil pipe, both can drop
Low control system module temperature, can improve again oil temperature, makes kerosene be easier to light and burn more fully, fall
Low oil consumption.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the structural representation after connection control system of the present invention；
Fig. 3 is the structural representation of turbine in the present invention；
Fig. 4 is the plan structure schematic diagram of turbine in the present invention；
1. calm the anger casing, 2. trousers, 3. compressor impeller, 3-1. blade stationary plane, 3-2. primary blades,
3-3. blade, 4. rotor, 5. motor stator, 6. diffuser, 7. combustor, 8. turbine, 9. shell
Body, 10. axle, 11. electromagnetic valves, 12. oil pumps, 13. fuel tanks, 14. display, 15. lithium batteries, 16. controls
System module.
Detailed description of the invention
Below in conjunction with the accompanying drawings the detailed description of the invention of the present invention is described further.At this it should be noted that
The explanation of these embodiments is adapted to assist in and understands the present invention, but be not intended that limitation of the invention.
As long as additionally, technical characteristic involved in each embodiment of invention described below is the most not
The conflict of composition just can be mutually combined.
In conjunction with accompanying drawing, 1,2,3,4 couples of present invention further describe, and make those skilled in the art preferably implement
The application, Micro Turbine Jet Engine, including casing 1 of calming the anger, trousers 2, housing 9 and axle 10, described
Housing 9 one end arranges trousers 2, and the center of described trousers 2 arranges casing 1 of calming the anger, described shell
What body 9 axial location can rotate arranges axle 10, and described axle 10 is provided with pressure near the one end of casing 1 of calming the anger
Compressor wheel 3, the other end is provided with turbine 8, is provided with burning between described compressor impeller 3 and turbine 8
Room 7, is provided with diffuser 6, described compressor impeller 3 He between described compressor impeller 3 and combustor 7
Being provided with motor between diffuser 6, described motor is brushless permanent magnet DC motor.Brushless permanent-magnet direct-current electricity
Machine either structure or control mode and traditional dc motor have a lot of similarity: but brushless forever
The advantages such as magnetic direct current generator has a simple in construction, reliable, easy to maintenance, be provided simultaneously with operational efficiency high,
The advantage such as cheap, durable.Described motor includes rotor 4 and motor stator 5, described
Rotor 4 is permanent-magnet DC electric motor rotor, and described motor stator 5 is permanent magnet DC motor stator, institute
The axle 10 stated is fixed by the bearing chamber being fixed on housing 9, and described rotor 4 is fixed on axle 10
On, described motor stator 5 is fixed on described bearing chamber.Described compressor impeller 3 includes blade
Stationary plane 3-1, described blade stationary plane 3-1 is fixed with blade uniformly, and described blade includes main lobe
Sheet 3-2 and time blade 3-3.
Diffuser 6 of the present invention is collar plate shape, and described diffuser 6 is near permanent magnet DC motor stator 5
Side be provided with the projection for diffusion, described protruding tilt arrange multiple, its side is straight line
Type, opposite side is circular arc；Described projection is arranged on position in the inner part, diffuser 6 edge uniformly；
Described diffuser 6 is sleeved on described axle 10 by the centre bore that middle part is offered and holds on room.
Housing 9 of the present invention is provided with blast cap, described blast cap inside one end away from casing 1 of calming the anger
For cone, be the present invention when working aerofluxus more smooth.
Of the present invention calming the anger is provided with receiving space, described receiving between casing 1 and described trousers 2
Electromagnetic valve 11, oil pump 12 and control system module 16, described control system module 16 it is provided with in space
Electrically connecting with described electromagnetic valve 11 and oil pump 12, described oil pump 12 passes through oil pipe and is arranged on housing 9
Outside fuel tank 13 connects, and described electromagnetic valve 11 is connected on the oil-out of oil pump 12 by oil pipe, institute
The control system module 16 stated electrically connects with the lithium battery 15 being arranged on outside housing 9 and display 14, institute
The capillary oil pipe drawn from oil pump 12 oil-out it is provided with in the control system module 16 stated.
Primary blades and time blade it is fixed with uniformly on the blade stationary plane of compressor impeller 3 of the present invention,
This design can well less air pressure impact loss, the bigger overall performance that improve whole product,
Described Micro Turbine Jet Engine changes pneumatic startup as brushless permanent magnet DC motor into and starts, and permanent direct-current electric
The installation site of machine is placed between compressor impeller 3 and diffuser 6, makes motor double as starting motor and generating
Machine, not only facilitates Micro Turbine Jet Engine to start, and the motor after starting becomes electromotor so that it is
Dual-use, the problem of the waste resource that the most no longer works after solving electric motor starting, make generated energy increase, this
Invention can make generated output reach 400W.The present invention by little to diameter and length, the suitable oil pump of flow 12,
Electromagnetic valve 11, control system module 16 is integrated into trousers 2 and position between casing 1 of calming the anger, both reduced
Turbojet engine complete machine weight, and improve Micro Turbine Jet Engine performance.Control system module 16 is integrated
Inside Micro Turbine Jet Engine, an aviation plug is used to replace various connection electric wires and external connection, no
But decrease the volume and weight of Micro Turbine Jet Engine, and facilitate Micro Turbine Jet Engine and outside company
Connect and install.During the work of this Micro Turbine Jet Engine, trousers 2 and the cavity temperature calmed the anger between casing 1 exist
Between 70 DEG C-85 DEG C, and control system module 16 normally can work in the temperature within 150 DEG C.Work
When making, it is contemplated that control system module 16 operationally self there will be fever phenomenon, therefore, controlling system
Full capillary oil pipe in system module 16, allows from oil pump 12 kerosene out through this capillary oil pipe, both can drop
Low control system module 16 temperature, can improve again oil temperature, makes kerosene be easier to light and burn more fully,
Reduce oil consumption.
Above in association with accompanying drawing, embodiments of the present invention are explained in detail, but the invention is not restricted to described
Embodiment.For a person skilled in the art, in the situation without departing from the principle of the invention and spirit
Under, these embodiments are carried out multiple change, revises, replace and modification, still fall within the protection of the present invention
In the range of.
Claims (10)
1. a Micro Turbine Jet Engine, it is characterised in that: include calm the anger casing, trousers, housing and axle,
Described shell one end arranges trousers, and the center of described trousers arranges casing of calming the anger, described shell
What body axis position can rotate arranges axle, and described axle is provided with compressor impeller near the one end of casing of calming the anger,
The other end is provided with turbine, is provided with combustor, described gas compressor blade between described compressor impeller and turbine
It is provided with diffuser between wheel and combustor, between described compressor impeller and diffuser, is provided with motor, institute
The compressor impeller stated includes blade stationary plane, and described blade stationary plane is fixed with blade, institute uniformly
The blade stated includes primary blades and time blade.
Micro Turbine Jet Engine the most according to claim 1, it is characterised in that: described motor includes
Rotor and motor stator, described rotor is permanent-magnet DC electric motor rotor, described motor stator
For permanent magnet DC motor stator.
Micro Turbine Jet Engine the most according to claim 2, it is characterised in that: described axle is by solid
The bearing chamber being scheduled on housing is fixed, and described rotor is fixed on axle, and described motor stator is fixed
On described bearing chamber.
Micro Turbine Jet Engine the most according to claim 3, it is characterised in that: described diffuser is
Collar plate shape, it is sleeved on described bearing chamber.
Micro Turbine Jet Engine the most according to claim 4, it is characterised in that: described diffuser leans on
The side of nearly motor stator is provided with the projection for diffusion.
Micro Turbine Jet Engine the most according to claim 5, it is characterised in that: described protruding inclination
Being uniformly arranged multiple, its side is linear type, and opposite side is circular arc type, and described projection is arranged on diffuser
Edge is near internal position.
7. according to the Micro Turbine Jet Engine described in peace claim 1, it is characterised in that: described housing is remote
Being provided with blast cap inside one end of tripping mechanism of qi casket, described blast cap is cone.
Micro Turbine Jet Engine the most according to claim 1, it is characterised in that: described casing of calming the anger
And between described trousers, it is provided with receiving space, it is provided with electromagnetic valve, oil pump and control in described receiving space
System module processed, described control system module electrically connects with described electromagnetic valve and oil pump.
Micro Turbine Jet Engine the most according to claim 8, it is characterised in that: leading to of described oil pump
The fuel tank crossing oil pipe and be arranged on outside is connected, and described electromagnetic valve is connected to the oil-out of oil pump by oil pipe
On, described control system module electrically connects with the lithium battery being arranged on hull outside and display.
Micro Turbine Jet Engine the most according to claim 9, it is characterised in that: described control system
The capillary oil pipe drawn from oil pump oil-out it is provided with in module.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610259496.3A CN105952538A (en) | 2016-04-22 | 2016-04-22 | Micro turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610259496.3A CN105952538A (en) | 2016-04-22 | 2016-04-22 | Micro turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105952538A true CN105952538A (en) | 2016-09-21 |
Family
ID=56915980
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610259496.3A Pending CN105952538A (en) | 2016-04-22 | 2016-04-22 | Micro turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105952538A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109268168A (en) * | 2018-11-26 | 2019-01-25 | 北京金朋达航空科技有限公司 | Height pushes away the small-size turbojet engine of ratio |
| CN110985215A (en) * | 2019-12-27 | 2020-04-10 | 西北工业大学 | Starting and launching integrated system for micro turbojet engine |
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|---|---|---|---|---|
| US6066898A (en) * | 1998-08-14 | 2000-05-23 | Alliedsignal Inc. | Microturbine power generating system including variable-speed gas compressor |
| US20040083733A1 (en) * | 2002-11-05 | 2004-05-06 | Ingram Joe Britt | Fuel splashplate for microturbine combustor |
| CN201053353Y (en) * | 2006-12-29 | 2008-04-30 | 深圳市康铖机械设备有限公司 | Mini turbine jet engine |
| CN102388224A (en) * | 2009-04-06 | 2012-03-21 | 涡轮梅坎公司 | Air bleed having an inertial filter in the tandem rotor of a compressor |
| CN202328366U (en) * | 2011-08-29 | 2012-07-11 | 佟宪良 | Turbine burner capable of re-generating electric energy |
| CN102691529A (en) * | 2011-08-26 | 2012-09-26 | 佟宪良 | Starting-generating device for miniature turbojet engine or turbocharger |
| CN104500268A (en) * | 2014-12-12 | 2015-04-08 | 常州环能涡轮动力股份有限公司 | Micro turbine jet engine with two-sided centrifugal pressure roller |
-
2016
- 2016-04-22 CN CN201610259496.3A patent/CN105952538A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6066898A (en) * | 1998-08-14 | 2000-05-23 | Alliedsignal Inc. | Microturbine power generating system including variable-speed gas compressor |
| US20040083733A1 (en) * | 2002-11-05 | 2004-05-06 | Ingram Joe Britt | Fuel splashplate for microturbine combustor |
| CN201053353Y (en) * | 2006-12-29 | 2008-04-30 | 深圳市康铖机械设备有限公司 | Mini turbine jet engine |
| CN102388224A (en) * | 2009-04-06 | 2012-03-21 | 涡轮梅坎公司 | Air bleed having an inertial filter in the tandem rotor of a compressor |
| CN102691529A (en) * | 2011-08-26 | 2012-09-26 | 佟宪良 | Starting-generating device for miniature turbojet engine or turbocharger |
| CN202328366U (en) * | 2011-08-29 | 2012-07-11 | 佟宪良 | Turbine burner capable of re-generating electric energy |
| CN104500268A (en) * | 2014-12-12 | 2015-04-08 | 常州环能涡轮动力股份有限公司 | Micro turbine jet engine with two-sided centrifugal pressure roller |
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| CN109268168A (en) * | 2018-11-26 | 2019-01-25 | 北京金朋达航空科技有限公司 | Height pushes away the small-size turbojet engine of ratio |
| CN110985215A (en) * | 2019-12-27 | 2020-04-10 | 西北工业大学 | Starting and launching integrated system for micro turbojet engine |
| CN110985215B (en) * | 2019-12-27 | 2024-05-24 | 西安觉天动力科技有限责任公司 | Integrated system for starting of micro turbojet engine |
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