CN105952537A - Micro turbojet engine - Google Patents
Micro turbojet engine Download PDFInfo
- Publication number
- CN105952537A CN105952537A CN201610257860.2A CN201610257860A CN105952537A CN 105952537 A CN105952537 A CN 105952537A CN 201610257860 A CN201610257860 A CN 201610257860A CN 105952537 A CN105952537 A CN 105952537A
- Authority
- CN
- China
- Prior art keywords
- jet engine
- turbine jet
- compressor impeller
- 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
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
Abstract
The invention discloses a micro turbojet engine. The engine comprises a housing. A shaft is disposed rotationally on the axis position of the housing, a compressor impeller is disposed on the end placing on an air inlet of the housing of the shaft, and a turbine is disposed on the other end. A combustion chamber is disposed between the compressor impeller and the turbine in the housing, and a motor is disposed between the compressor impeller and the combustion chamber. 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 combustion chamber, 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, 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 is pneumatic startup, without motor, inconvenient during startup, and does not has
Generating function.Existing Micro Turbine Jet Engine is combined with electronic control system (ECU) and oil supply system and carries out
Work, its mainly include temperature sensor, velocity sensor, Micro Turbine Jet Engine main frame, electromagnetic valve,
Fuel tank, oil pipe, oil pump, display, lithium battery, control system module (ECU), electric wire.By above may be used
To find out that automatically controlled part and oil supply system connect complex, some parts such as oil pump, control system module
Etc. (ECU) there are Heavy Weight and volume relatively big, add production cost, and cause Micro Turbine Jet Engine
Can reduce, and bad installation.
Summary of the invention
This technical problem to be solved in the present invention is to provide a kind of startup conveniently, and can generate electricity after starting,
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 a kind of Micro Turbine Jet Engine, bag
Including housing, what described housing axial location can rotate arranges axle, and described axle is positioned at the one of shell air inlet
End arranges compressor impeller, and the other end arranges turbine, described enclosure interior be positioned at compressor impeller and turbine it
Between combustor is set, be provided with motor between described compressor impeller and combustor.
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 bearing chamber.
Further, also including that diffuser, described diffuser are collar plate shape, it is sleeved on described axle
Hold one end near compressor impeller, room.
Further, it is convex that described diffuser is provided with for diffusion near the side of compressor impeller
Rise.
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, in described housing, the one end being positioned at turbine is provided with blast cap, and described blast cap is circle
Taper.
Further, the one end being provided with compressor impeller in described housing is provided with receiving space, described
Being provided with electromagnetic valve, oil pump and control system module in accommodating space, described control system module is with described
Electromagnetic valve and oil pump electrical connection.
Further, being connected with the fuel tank being arranged on hull outside by oil pipe of described oil pump, described
Electromagnetic valve be connected on the oil-out of oil pump by oil pipe, described control system module be arranged on housing
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.
Have the beneficial effect that described Micro Turbine Jet Engine opens pneumatic with what the technique scheme present invention obtained
The dynamic direct current generator that changes into starts, and the installation site of permanent magnet DC motor is placed on compressor impeller and combustor
Between, make motor double as starting motor and electromotor, not only facilitate Micro Turbine Jet Engine to start, Er Qieqi
Motor after Dong becomes electromotor so that it is dual-use, and the most no longer work after solving electric motor starting wave
The problem taking resource, makes generated energy increase, and the present invention can make generated output reach 800W.The present invention is by diameter
, flow suitable oil pump little with length, electromagnetic valve, control system module is integrated into trousers and casing of calming the anger
Between position, both reduced turbojet engine complete machine weight, and improve Micro Turbine Jet Engine performance.
Control system module is integrated into inside Micro Turbine Jet Engine, uses an aviation plug to replace various connection electricity
Line and external connection, not only decrease the volume and weight of Micro Turbine Jet Engine, and facilitate miniature whirlpool to spray
Electromotor and outside connection and installation.Trousers and calming the anger between casing during the work of this Micro Turbine Jet Engine
Cavity temperature between 70 DEG C-85 DEG C, and control system module can in the temperature within 150 DEG C just
Often work.During work, it is contemplated that control system module operationally self there will be fever phenomenon, therefore,
Capillary oil pipe full in control system module, allow from oil pump kerosene out through this capillary oil pipe, the most permissible
Reduce control system module temperature, oil temperature can be improved again, make kerosene be easier to light and burn more fully,
Reduce 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 diffuser in the present invention；
Fig. 4 is the structural representation of middle (center) bearing room of the present invention；
In figure: 1. accommodate space, 2. compressor impeller, 3. rotor, 4. motor stator, 5. diffuser,
6. combustor, 7. turbine, 8. axle, 9. housing, 10. electromagnetic valve, 11. oil pumps, 12. fuel tanks, 13. displays
Device, 14. lithium batteries, 15. 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, 1,2,3,4 couples of present invention further describe, and make those skilled in the art preferably implement
The present invention, Micro Turbine Jet Engine of the present invention, including housing 9, described housing 9 axial location can rotate
Axle 8 is set, described axle 8 is positioned at one end of housing 9 air inlet and arranges compressor impeller 2, and the other end is arranged
Turbine 7, described housing 9 is internally located between compressor impeller 2 and turbine 7 and arranges combustor 6, described pressure
Being provided with motor between compressor wheel 2 and combustor 6, described motor includes that rotor 3 and motor are fixed
Son 4, described rotor 3 is permanent-magnet DC electric motor rotor, and described motor stator 4 is permanent direct-current electric
Machine stator；Described axle 8 is fixed by the bearing chamber being fixed on housing 9, and described rotor 3 is solid
Being scheduled on axle 8, described motor stator 4 is fixed on bearing chamber or housing 9.
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 2 and combustor 6, makes motor double as starting
Motor and electromotor, not only facilitate Micro Turbine Jet Engine to start, and the motor after starting becomes generating
Machine 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
Increasing, the present invention can make generated output reach 800W.
Present invention additionally comprises diffuser 5, described diffuser 5 is collar plate shape, and it is sleeved on described bearing chamber
Near one end of compressor impeller 2, described diffuser 5 is provided with use near the side of compressor impeller 2
In the projection of diffusion, described projection is 20 °--and the angle of 60 ° is obliquely installed, the one of its inclined side
Individual side is linear type, and another side is circular arc, described projection be multiple be arranged on uniformly described
Position in the inner part, diffuser 5 edge, described diffuser 5 is sleeved on institute by being arranged on the centre bore at middle part
On the bearing chamber stated.
In order to make aerofluxus of the present invention more smooth, described housing 9 is arranged away from inside the one end of casing of calming the anger
Having blast cap, described blast cap is cone.
The one end being provided with compressor impeller 2 in housing 9 of the present invention is provided with receiving space 1, described
It is provided with electromagnetic valve 10, oil pump 11 and control system module 15, described control system in accommodating space 1
Module 15 electrically connects with described electromagnetic valve 10 and oil pump 11, described oil pump 11 by oil pipe with set
Putting and connect at the fuel tank 12 outside housing 9, described electromagnetic valve 10 is connected to going out of oil pump 11 by oil pipe
On hydraulic fluid port, described control system module 15 electrically connects with the lithium battery being arranged on outside housing 9 and display,
The capillary oil pipe drawn from oil pump 11 oil-out it is provided with in described control system module 15.
The present invention is by little to diameter and length, the suitable oil pump of flow 11, electromagnetic valve 10, control system module 15
It is integrated into trousers and position between casing of calming the anger, had both reduced turbojet engine complete machine weight, and improved
Micro Turbine Jet Engine performance.Control system module 15 is integrated into inside Micro Turbine Jet Engine, uses one
Individual aviation plug replaces various connection electric wires and external connection, not only decreases the volume of Micro Turbine Jet Engine
And weight, and facilitate Micro Turbine Jet Engine and outside connection and installation.This Micro Turbine Jet Engine work
When making, trousers and the cavity temperature calmed the anger between casing are between 70 DEG C-85 DEG C, and control system module
15 normally can work in the temperature within 150 DEG C.During work, it is contemplated that control system module 15 is in work
When making, self there will be fever phenomenon, therefore, capillary oil pipe full in control system module 15, allows from oil pump
11 kerosene out, through this capillary oil pipe, both can reduce control system module 15 temperature, can improve again
Oil temperature, makes kerosene be easier to light and burn more fully, reduces 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 housing, described housing axial location energy
Enough rotate arranges axle, and described axle is positioned at one end of shell air inlet and arranges compressor impeller, and the other end is arranged
Turbine, described enclosure interior arranges combustor, described compressor impeller between compressor impeller and turbine
And between combustor, it is provided with motor.
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 bearing chamber.
Micro Turbine Jet Engine the most according to claim 3, it is characterised in that: also include diffuser,
Described diffuser is collar plate shape, and it is sleeved on described bearing chamber one end near compressor impeller.
Micro Turbine Jet Engine the most according to claim 4, it is characterised in that: described diffuser leans on
The side of nearly compressor impeller 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: in described housing,
The one end being positioned at turbine is provided with blast cap, and described blast cap is cone.
Micro Turbine Jet Engine the most according to claim 1, it is characterised in that: set in described housing
The one end being equipped with compressor impeller is provided with receiving space, is provided with electromagnetic valve, oil pump in described receiving space
With control system module, 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 hull outside is connected, and described electromagnetic valve is connected to going out of oil pump by oil pipe
On hydraulic fluid port, 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 |
|---|---|---|---|
| CN201610257860.2A CN105952537A (en) | 2016-04-22 | 2016-04-22 | Micro turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610257860.2A CN105952537A (en) | 2016-04-22 | 2016-04-22 | Micro turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105952537A true CN105952537A (en) | 2016-09-21 |
Family
ID=56916081
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610257860.2A Pending CN105952537A (en) | 2016-04-22 | 2016-04-22 | Micro turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105952537A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108869038A (en) * | 2018-07-02 | 2018-11-23 | 重庆交通大学 | Micro gas turbine electricity generation system |
| CN109026389A (en) * | 2018-09-14 | 2018-12-18 | 青岛云深动力科技有限公司 | Gas turbine engine systems and its control method |
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 |
| 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 CN201610257860.2A patent/CN105952537A/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 (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108869038A (en) * | 2018-07-02 | 2018-11-23 | 重庆交通大学 | Micro gas turbine electricity generation system |
| CN109026389A (en) * | 2018-09-14 | 2018-12-18 | 青岛云深动力科技有限公司 | Gas turbine engine systems and its control method |
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| PB01 | Publication | ||
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Application publication date: 20160921 |