CN105952539A - Micro turbojet engine - Google Patents
Micro turbojet engine Download PDFInfo
- Publication number
- CN105952539A CN105952539A CN201610259497.8A CN201610259497A CN105952539A CN 105952539 A CN105952539 A CN 105952539A CN 201610259497 A CN201610259497 A CN 201610259497A CN 105952539 A CN105952539 A CN 105952539A
- Authority
- CN
- China
- Prior art keywords
- jet engine
- diffuser
- turbine jet
- micro turbine
- housing
- 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 11
- 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
- 230000007246 mechanism Effects 0.000 claims description 2
- 238000002485 combustion reaction Methods 0.000 abstract description 2
- 239000003921 oil Substances 0.000 description 35
- 238000009434 installation Methods 0.000 description 5
- 239000003350 kerosene Substances 0.000 description 4
- 230000005611 electricity Effects 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
- 239000002699 waste material Substances 0.000 description 2
- 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
- 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
- 239000007789 gas Substances 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
- 238000000034 method 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
- 230000008450 motivation Effects 0.000 description 1
- 238000010899 nucleation Methods 0.000 description 1
- 239000005413 snowmelt Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
-
- 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
- F04D29/40—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)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a micro turbojet engine. The micro turbojet engine comprises a compressor box, a cowling, a compressor impeller, a diffuser, a combustion chamber, a turbine, a housing and a shaft. The cowling is disposed on the end of the housing, and the compressor box is disposed on the central section of the cowling. The shaft is disposed rotationally on the axis position of the housing, the compressor impeller is disposed on the end closed to the compressor box of the shaft, and the turbine is disposed on the other end. The diffuser is disposed between the compressor impeller and the turbine and closed to the compressor impeller, and a motor rotor and a motor stator are disposed between the compressor impeller and the diffuser. The micro turbojet engine changes the pneumatic starting into direct current motor starting, and the permanent magnet direct current 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 turbojet engine technical field, particularly to a kind of Micro Turbine Jet Engine.
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.Existing Micro Turbine Jet Engine and electronic control system (ECU) and
Oil supply system combines and is operated, and it mainly includes that temperature sensor, velocity sensor, the eruption of miniature whirlpool are moved
Machine host, electromagnetic valve, fuel tank, oil pipe, oil pump, display, lithium battery, control system module (ECU),
Electric wire.By can be seen that automatically controlled part and oil supply system connect complex above, some parts such as oil pump,
Control system module (ECU) etc. has Heavy Weight and volume relatively big, adds production cost, and causes miniature
Turbojet engine 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, and can generate electricity after starting, and
And the miniature whirlpool eruption motor that service weight is light is combined with oil pump, control system module.
In order to solve above-mentioned technical problem, the technical scheme is that Micro Turbine Jet Engine, including pressure
Mechanism of qi casket, trousers, compressor impeller, diffuser, combustor, turbine, housing and axle, described shell
Body one end arranges trousers, and the middle part of described trousers arranges casing of calming the anger, described housing axial location energy
Enough rotate arranges axle, and described axle arranges compressor impeller near one end of trousers, and the other end arranges turbine,
Between described compressor impeller and turbine, diffuser, described enclosure interior position are set near compressor impeller
Combustor is set between diffuser and turbine, is provided with motor between described compressor impeller and diffuser and turns
Son and motor stator.
Further, described rotor is permanent-magnet DC electric motor rotor, and described motor stator is permanent magnetism
DC motor stator.
Further, described axle is fixed by the bearing chamber being fixed on housing, and described rotor is solid
Being scheduled on axle, described motor stator is fixed on housing or bearing chamber.
Further, described diffuser is collar plate shape, is sleeved on described bearing chamber.
Further, described diffuser is provided with for diffusion near the side of permanent magnet DC motor stator
Projection, described projection is obliquely installed, and its side is linear type, and opposite side is circular arc.
Further, described projection arranges multiple, is arranged on described diffuser edge uniformly in the inner part
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, described oil pump is connected with the fuel tank being arranged on hull outside by oil pipe, described
Electromagnetic valve is connected on the oil-out of oil pump by oil pipe, described control system module be arranged on outside housing
The lithium battery in portion and display electrical connection.
Further, described control system module is provided with the capillary oil pipe drawn from oil pump oil-out.
Have the beneficial effect that described Micro Turbine Jet Engine opens pneumatic with what the technique scheme present invention obtained
The dynamic permanent magnet DC motor that changes into starts, and the installation site of permanent magnet DC motor is placed on compressor impeller and expansion
Between depressor, make motor double as starting motor and electromotor, not only facilitate Micro Turbine Jet Engine to start, and
And the motor after starting becomes electromotor so that it is dual-use, solve after electric motor starting the most no longer work
The problem making waste resource.The present invention can make generated output reach 200W.The present invention by little to diameter and length,
The suitable oil pump of flow, electromagnetic valve, control system module is integrated into trousers and position between casing of calming the anger,
Both reduce turbojet engine complete machine weight, and improve Micro Turbine Jet Engine performance.Control system mould
Block is integrated into inside Micro Turbine Jet Engine, uses an aviation plug to replace various connection electric wires to connect with outside
Connect, not only decrease the volume and weight of Micro Turbine Jet Engine, and facilitate Micro Turbine Jet Engine with outer
The connection in portion and installation.Trousers and the cavity temperature calmed the anger between casing during the work of this Micro Turbine Jet Engine
Between 70 DEG C-85 DEG C, and control system module normally can work in the temperature within 150 DEG C.Work
When making, it is contemplated that control system module operationally self there will be fever phenomenon, therefore, control system
Full capillary oil pipe in module, allows from oil pump kerosene out through this capillary oil pipe, both can reduce control system
System module temperature, can improve again oil temperature, makes kerosene be easier to light and burn more fully, reduces 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；
In figure: 1. calm the anger casing, 2. trousers, 3. diffuser, 4. housing, 5. combustor, 6. bearing chamber,
7. accommodate space, 8. compressor impeller, 9. rotor, 10. motor stator, 11. axles, 12. turbines, 13.
Electromagnetic valve, 14. oil pumps, 15. fuel tanks, 16. display, 17. lithium batteries, 18. control system modules.
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 couples of present invention further describe, and make those skilled in the art preferably implement the present invention,
Micro Turbine Jet Engine, including casing 1 of calming the anger, trousers 2, compressor impeller 8, diffuser 3, burning
Room 5, turbine 12, housing 4 and axle 11；Described housing 4 one end arranges trousers 2, described trousers 2
Middle part arrange and calm the anger casing 1, what described housing 4 axial location can rotate arranges axle 11, described axle
11 arrange compressor impeller 8 near one end of trousers 2, and the other end arranges turbine 12, at described compressor
Between impeller 8 and turbine 12, arranging diffuser 3 near compressor impeller 8, described housing 4 is internally located at
Combustor 5 is set between diffuser 3 and turbine 12, arranges between described compressor impeller 8 and diffuser 3
Having rotor 9 and motor stator 10, described axle 11 is fixed by the bearing chamber 6 being fixed on housing 4,
In order to provide the power rotated for rotor 9, described rotor 9 is fixed on axle 11, described
Motor stator 10 is fixed on the rotor 9 on housing 4 or bearing chamber 6, in this miniature turbine 12 electromotor
Being preferably permanent-magnet DC electric motor rotor, described motor stator 10 is preferably permanent magnet DC motor stator.Preferably
, rotor 9 and motor stator 10 constitute brushless permanent magnet DC motor.Brushless permanent magnet DC motor no matter
It is structure or control mode and traditional dc motor has a lot of similarity: but brushless permanent-magnet direct-current
The advantages such as motor has a simple in construction, reliable, easy to maintenance, are provided simultaneously with that operational efficiency is high, price
The advantage such as cheap, durable.
Diffuser 3 of the present invention is collar plate shape, is provided with near the side of permanent magnet DC motor stator 10
For the projection of diffusion, described projection is that the angle of 20 ° to 60 ° is obliquely installed, its inclined side
One side is linear type, and another side is circular arc, and described projection is multiple to be arranged on institute uniformly
Stating position in the inner part, diffuser 3 edge, described diffuser 3 is sleeved on by being arranged on the centre bore at middle part
On described bearing chamber 6.
In order to make aerofluxus of the present invention more smooth, described housing 4 sets inside the one end away from casing 1 of calming the anger
Being equipped with blast cap, described blast cap is cone.
Micro Turbine Jet Engine of the present invention changes pneumatic startup as brushless permanent magnet DC motor into and starts, and handle
The installation site of permanent magnet DC motor is placed between compressor impeller 8 and diffuser 3, makes motor double as starting
Motor and electromotor, not only facilitate Micro Turbine Jet Engine to start, and the motor after starting becomes and sends out
Motor so that it is dual-use, the problem of the waste resource that the most no longer works after solving electric motor starting.The present invention
Generated output can be made to reach 200W.
Of the present invention calming the anger is provided with receiving space 7, described receiving between casing 1 and described trousers 2
Electromagnetic valve 13, oil pump 14 and control system module 18, described control system module it is provided with in space 7
18 electrically connect with described electromagnetic valve 13 and oil pump 14, and described oil pump 14 passes through oil pipe and is arranged on housing
Fuel tank 15 outside 4 connects, and described electromagnetic valve 13 is connected on the oil-out of oil pump 14 by oil pipe,
Described control system module 18 electrically connects with the lithium battery 17 being arranged on outside housing 4 and display 16,
The capillary oil pipe drawn from oil pump 14 oil-out it is provided with in described control system module 18.
The present invention is by little to diameter and length, the suitable oil pump of flow 14, electromagnetic valve 13, control system module 18
It is integrated into trousers 2 and position between casing 1 of calming the anger, both reduces turbojet engine complete machine weight, and
Improve Micro Turbine Jet Engine performance.Control system module 18 is integrated into inside Micro Turbine Jet Engine, adopts
Replace various connection electric wires and external connection with an aviation plug, not only decrease Micro Turbine Jet Engine
Volume and weight, and facilitate Micro Turbine Jet Engine and outside connection and installation.This miniature whirlpool eruption is dynamic
During machine work, trousers 2 and the cavity temperature calmed the anger between casing 1 are between 70 DEG C-85 DEG C, and control
System module 18 normally can work in the temperature within 150 DEG C.During work, it is contemplated that control system mould
Block 18 operationally self there will be fever phenomenon, therefore, capillary oil pipe full in control system module 18,
Allow from oil pump 14 kerosene out through this capillary oil pipe, both can reduce control system module 18 temperature,
Oil temperature can be improved again, make 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, gas compressor blade
Wheel, diffuser, combustor, turbine, housing and axle, described shell one end arranges trousers, described whole
The middle part of stream cover arranges casing of calming the anger, and what described housing axial location can rotate arranges axle, and described axle leans on
One end of nearly trousers arranges compressor impeller, and the other end arranges turbine, at described compressor impeller and turbine
Between, near compressor impeller, diffuser is set, described enclosure interior is arranged between diffuser and turbine
Combustor, is provided with rotor and motor stator between described compressor impeller and diffuser.
Micro Turbine Jet Engine the most according to claim 1, it is characterised in that: described rotor
For permanent-magnet DC electric motor rotor, described motor stator is permanent magnet DC motor stator.
Micro Turbine Jet Engine the most according to claim 1 and 2, it is characterised in that: described axle leads to
Crossing the bearing chamber being fixed on housing to fix, described rotor is fixed on axle, described motor stator
It is fixed on housing or bearing chamber.
Micro Turbine Jet Engine the most according to claim 3, it is characterised in that: described diffuser is
Collar plate shape, 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 permanent magnet DC motor stator is provided with the projection for diffusion, and described projection is obliquely installed,
Its side is linear type, and opposite side is circular arc.
Micro Turbine Jet Engine the most according to claim 5, it is characterised in that: described protruding setting
Multiple, it is arranged on position in the inner part, described diffuser edge uniformly.
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: described oil pump passes through
Oil pipe is connected with the fuel tank being arranged on hull outside, and described electromagnetic valve is connected to the fuel-displaced of oil pump by oil pipe
On mouth, 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 |
|---|---|---|---|
| CN201610259497.8A CN105952539A (en) | 2016-04-22 | 2016-04-22 | Micro turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610259497.8A CN105952539A (en) | 2016-04-22 | 2016-04-22 | Micro turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105952539A true CN105952539A (en) | 2016-09-21 |
Family
ID=56915950
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610259497.8A Pending CN105952539A (en) | 2016-04-22 | 2016-04-22 | Micro turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105952539A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108590862A (en) * | 2018-05-29 | 2018-09-28 | 张敏 | Diameter formula turbojet power plant after a kind of microminiature |
| CN110985215A (en) * | 2019-12-27 | 2020-04-10 | 西北工业大学 | Starting and launching integrated system for micro turbojet engine |
| CN113615672A (en) * | 2021-08-30 | 2021-11-09 | 山东元一动力科技有限公司 | Jet-propelled plant protection atomizing machine |
| CN114033553A (en) * | 2021-09-22 | 2022-02-11 | 浙江意动科技股份有限公司 | Turbojet engine rotor transmission shaft and axial locking device thereof |
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| 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 |
| 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 CN201610259497.8A patent/CN105952539A/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 |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108590862A (en) * | 2018-05-29 | 2018-09-28 | 张敏 | Diameter formula turbojet power plant after a kind of microminiature |
| 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 |
| CN113615672A (en) * | 2021-08-30 | 2021-11-09 | 山东元一动力科技有限公司 | Jet-propelled plant protection atomizing machine |
| CN114033553A (en) * | 2021-09-22 | 2022-02-11 | 浙江意动科技股份有限公司 | Turbojet engine rotor transmission shaft and axial locking device thereof |
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Application publication date: 20160921 |