CN108194227A - A kind of momentum thrust aerojet formula engine - Google Patents
A kind of momentum thrust aerojet formula engine Download PDFInfo
- Publication number
- CN108194227A CN108194227A CN201810310779.5A CN201810310779A CN108194227A CN 108194227 A CN108194227 A CN 108194227A CN 201810310779 A CN201810310779 A CN 201810310779A CN 108194227 A CN108194227 A CN 108194227A
- Authority
- CN
- China
- Prior art keywords
- hollow
- aerojet
- thrust
- hollow driving
- formula engine
- 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
- 238000002485 combustion reaction Methods 0.000 claims abstract description 20
- 239000007789 gas Substances 0.000 claims abstract description 8
- 238000005507 spraying Methods 0.000 claims abstract 2
- 238000007789 sealing Methods 0.000 claims description 10
- 239000000567 combustion gas Substances 0.000 claims description 5
- 238000012856 packing Methods 0.000 claims description 3
- 239000002737 fuel gas Substances 0.000 abstract description 10
- 239000000446 fuel Substances 0.000 abstract description 7
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 230000015556 catabolic process Effects 0.000 abstract description 3
- 238000013461 design Methods 0.000 abstract description 3
- 238000012423 maintenance Methods 0.000 abstract description 3
- 238000001816 cooling Methods 0.000 description 6
- 239000000463 material Substances 0.000 description 5
- 238000006243 chemical reaction Methods 0.000 description 4
- 238000002347 injection Methods 0.000 description 4
- 239000007924 injection Substances 0.000 description 4
- 239000007921 spray Substances 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- TVEXGJYMHHTVKP-UHFFFAOYSA-N 6-oxabicyclo[3.2.1]oct-3-en-7-one Chemical compound C1C2C(=O)OC1C=CC2 TVEXGJYMHHTVKP-UHFFFAOYSA-N 0.000 description 1
- 230000001914 calming effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000010437 gem Substances 0.000 description 1
- 229910001751 gemstone Inorganic materials 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/005—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the engine comprising a rotor rotating under the actions of jets issuing from this rotor
Abstract
The invention discloses a kind of momentum thrust aerojet formula engines, air intake duct, compressor, combustion chamber and engine power output shaft including housing, in housing, the hollow driving wheel being connect with engine power output shaft and compressor spindle drive, the hollow driving rod on hollow drive wheel circumferences face are further included, the inner cavity of the hollow driving wheel is connected with the gas outlet of the inner cavity of hollow driving rod and combustion chamber；The blind hole being connected with hollow driving rod inner cavity is offered on the hollow driving rod, the driving nozzle for spraying gas booster speedup along hollow drive wheel circumferences tangential direction is equipped in the blind hole.The present invention can be substantially reduced engine design requirement, and manufacturing process is relatively easy, easy to maintenance, easily worn part significantly reduces, and reduce R＆D cycle, R＆D costs and the rate of breakdown of engine；There is no axial thrust load, fuel gas alternative efficiency is up to 100%, significantly improves fuel availability.
Description
Technical field
The present invention relates to a kind of momentum thrust aerojet formula engines, belong to field of aerospace technology.
Background technology
Existing aerojet formula engine is mainly made of housing, air intake duct, compressor, combustion chamber and turbine, through calming the anger
The compressed pressure-air of machine and fuel mixture enter burning Indoor Combustion, and the high-temperature high-pressure fuel gas generated after burning pushes whirlpool
Wheel operating, and sprayed from housing tail portion so as to generate thrust at a high speed.Obviously, turbine can be in high temperature, high pressure and the condition that runs at high speed
Lower steady operation is exactly the most basic requirement that modern Aviation turbogenerator proposes turbine performance.Thus turbine manufacture uses
Complex process, material expensive, development cost and the lead time proportion in reseach of engine are big, become aeroplane engine
The concentrated reflection of Major Difficulties and aero-engine advance and complexity during machine is developed.
In the prior art in order to reduce failure rate, ensure that turbine material is not melted by high-temperature fuel gas, will usually take
Complicated cooling way carries out turbine cooling, such as：Gaseous film control, impinging cooling and convection current cooling etc..These cooling ways are all
It is the cooling media implementation released by hollow turbine interior.However cast out the turbine leaf of hollow complex aerodynamic configuration
This technology of piece is referred to as " jewel on industrial crown " so far by people, it has also become the hang-up of challenge various countries' aircraft industry.I
The two aspects of the difficult material for being also mainly reflected in power turbine blade and technique of state's aviation reseach of engine.
In addition original aero-engine power turbine acting area is that the air-flow entrance of the high temperature and pressure sprayed from combustion chamber is dynamic
Power turbine do work area, impulse turbine blade, make it rotate drive engine power output shaft rotation acting, high-temperature high-pressure air flow into
The direction for entering turbine acting area's operation is identical with the direction that power turbine rotates, and the linear velocity of power output shaft rotation is impact gas
The 50% of flow velocity degree, for power turbine, its effective speed is the 50% of intake velocity with, so that the profit of effective speed
With rate 50%, while air inlet generates power turbine and has big impact force, and it is zero that impact force axial force, which is done work, is not worked,
The acting of radial load is worked, and entire impact force carries out force resolution, and radial load is theoretically the 70% of entire impact force,
The actually active power in acting area in this way is equal to 35% for 50%*70%, and combustion gas utilization rate is not high.
Invention content
It is an object of the invention to overcome deficiency of the prior art, a kind of momentum thrust aerojet formula is provided and is started
Machine, solving aerojet formula engine in the prior art, as power drive, there are turbine manufacturing process complexity, materials using turbine
The technical issues of material is expensive, R＆D costs and period accounting are big, combustion gas utilization rate is not high.
In order to solve the above technical problems, the technical solution adopted in the present invention is：A kind of momentum thrust aerojet formula hair
Motivation, air intake duct, compressor, combustion chamber and engine power output shaft including housing, in housing, further includes and starts
Acc power output shaft and the hollow driving wheel of compressor spindle drive connection, the hollow driving on hollow drive wheel circumferences face
Bar, the inner cavity of the hollow driving wheel are connected with the gas outlet of the inner cavity of hollow driving rod and combustion chamber；The hollow drive
It offers the blind hole being connected with hollow driving rod inner cavity in lever, is equipped in the blind hole by gas booster speedup along hollow drive
The driving nozzle that pulley periphery tangential direction sprays.
Further, the tail portion of the housing is additionally provided with after-burner, and step-up jet is equipped in the afterbunring room.
Preferably, the driving nozzle and/or step-up jet are Laval nozzle.
Further, the engine further includes the jet pipe accelerated for combustion gas expansion set on housing tail portion.
Further, it is additionally provided with flameholder in the jet pipe.
Further, the jet pipe uses direction adjustable nozzles.
Further, fixed set thrust plate is additionally provided between the combustion chamber and hollow driving wheel.
Further, it is connected between the combustion chamber and hollow driving wheel by mechanical sealing member, the mechanical sealing member
In fixed set thrust plate.
Preferably, the mechanical sealing member includes the tooth-like packing part in side.
Compared with prior art, the advantageous effect that is reached of the present invention is：It is set using hollow driving wheel, hollow driving rod
It counts structure and replaces turbine design structure of the prior art, avoid the difficult point in turbine manufacture craft, hollow driving wheel and sky
The manufacturing process of heart drive rod is relatively easy, easy to maintenance, easily worn part significantly reduces, reduce engine R＆D cycle,
R＆D costs and rate of breakdown；High-temperature high-pressure fuel gas is through driving nozzle directly to be sprayed along hollow driving wheel tangential direction, injection
Reaction force is completely used for driving hollow driving wheel, and there is no axial thrust load, fuel gas alternative efficiency is up to 100%, significantly improves
Fuel availability.
Description of the drawings
Fig. 1 is the dimensional structure diagram of an embodiment of the present invention；
Fig. 2 is the sectional view of an embodiment of the present invention；
In figure：1st, housing；2nd, compressor；3rd, combustion chamber；4th, mechanical sealing member；5th, fixed set thrust plate；6th, hollow driving wheel；7、
Hollow driving rod；8th, nozzle is driven；9th, after-burner；10th, jet pipe；11st, step-up jet；12nd, flameholder.
Specific embodiment
Momentum thrust aerojet formula engine provided by the invention is taken using hollow driving wheel 6,7 structure of hollow driving rod
For turbine drives structure of the prior art, momentum thrust caused by high-temperature high-pressure fuel gas is completely used for driving hollow driving
Wheel 6, there is no the axial thrust load in turbine drives structure, so as to reach raising fuel availability, reach fuel conversion efficiency
100% purpose；2 main shaft of compressor and engine power output shaft is driven to operate by hollow driving wheel 6, aviation flight body is produced
By adding after-burner 9 to further improve flying speed, rotation driving and power injection are promoted for raw forward pulling force
It is divided into two parts, design requirement can be substantially reduced, manufacturing process is relatively easy, easy to maintenance, easily worn part significantly reduces, drop
The low R＆D cycle of engine, R＆D costs and rate of breakdown.
The invention will be further described below in conjunction with the accompanying drawings.Following embodiment is only used for clearly illustrating the present invention
Technical solution, and be not intended to limit the protection scope of the present invention and limit the scope of the invention.
As shown in Figure 1 and Figure 2, air intake duct, compressor of the invention including sequentially being arranged from front to back in housing 1, housing 1
2nd, combustion chamber 3, hollow driving wheel 6, after-burner 9 and jet pipe 10.Hollow driving wheel 6 be set side by side with it is N number of, N be more than
Positive integer equal to 1, the practical value of N can be determined according to power factor (PF), be distributed on the periphery of each hollow driving wheel 6
M hollow driving rod 7, M are the positive integer more than or equal to 2.Offered on each hollow driving rod 7 in hollow driving rod 7
One or more blind holes that chamber is connected, interior be equipped with of blind hole spray gas booster speedup along hollow 6 tangent to periphery direction of driving wheel
The driving nozzle 8 gone out.It should be noted that each fuel gas injection direction should be simultaneously along hollow driving wheel 6 on hollow driving wheel 6
Tangential direction clockwise or tangential direction counterclockwise, ensure fuel gas injection reaction be completely used for pushing hollow driving wheel 6 suitable
Hour hands counterclockwise rotate.
Enter combustion chamber 3 through air intake duct during present invention work, after pressure-air and the fuel mixing compressed through compressor 2 to fire
It burning, the high-temperature high-pressure fuel gas of generation enters hollow driving wheel 6, hollow driving rod 7, through nozzle 8 is driven to spray, spray reaction forces
Hollow driving rod 7 is pushed to move, hollow driving wheel 6 is driven to operate, is exported with the engine power that hollow driving wheel 6 is sequentially connected
Axis operating synchronous with 2 main shaft of compressor, engine operation generate forward pulling force, 2 continuous Repeated Compression of compressor sucking air
And fuel.The combustion gas ejected from driving nozzle 8 is expanded through jet pipe 10 outside Accelerating Removal housing 1, while engine is generated
Forward thrust accelerates flying body flying speed.Flameholder 12 is additionally provided in jet pipe 10, jet pipe 10 can using direction
Adjust nozzle.
To further improve the flying speed of flying body, the present invention is additionally provided with after-burner 9 in the tail portion of housing 1, adds
Step-up jet 11 is equipped in power combustion chamber 9.As the preferred embodiment of the present invention, nozzle 8 and/or step-up jet 11 is driven to select and draw
Wa Er nozzles.
Hollow driving wheel 6 is rotary power component, defeated from combustion chamber 3 to hollow driving wheel 6 to reduce high-temperature high-pressure fuel gas
Leakage during sending is additionally provided with fixed set thrust plate 5, combustion chamber 3 and hollow drive between combustion chamber 3 and hollow driving wheel 6
It is connected between driving wheel 6 by mechanical sealing member 4, mechanical sealing member 4 is flush-mounted in fixed set thrust plate 5.Mechanical sealing member 4 can be adopted
With the tooth-like packing part in side.
The above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, several improvement and deformation can also be made, these are improved and deformation
Also it should be regarded as protection scope of the present invention.
Claims (9)
1. a kind of momentum thrust aerojet formula engine, air intake duct, compressor including housing, in housing, combustion chamber
And engine power output shaft, which is characterized in that further include what is connect with engine power output shaft and compressor spindle drive
Hollow driving wheel, the hollow driving rod on hollow drive wheel circumferences face, inner cavity and the hollow driving of the hollow driving wheel
The inner cavity of bar and the gas outlet of combustion chamber are connected；It offers on the hollow driving rod and is connected with hollow driving rod inner cavity
Logical blind hole, the blind hole is interior to be equipped with the driving nozzle for spraying gas booster speedup along hollow drive wheel circumferences tangential direction.
2. momentum thrust aerojet formula engine according to claim 1, which is characterized in that the tail portion of the housing is also
Equipped with after-burner, step-up jet is equipped in the afterbunring room.
3. momentum thrust aerojet formula engine according to claim 2, which is characterized in that it is described driving nozzle and/or
Step-up jet is Laval nozzle.
4. momentum thrust aerojet formula engine according to claim 1, which is characterized in that further include set on housing tail
The jet pipe accelerated for combustion gas expansion in portion.
5. momentum thrust aerojet formula engine according to claim 4, which is characterized in that also set in the jet pipe
There is flameholder.
6. momentum thrust aerojet formula engine according to claim 4, which is characterized in that the jet pipe use side
To adjustable nozzles.
7. momentum thrust aerojet formula engine according to claim 1, which is characterized in that the combustion chamber with it is hollow
Fixed set thrust plate is additionally provided between driving wheel.
8. momentum thrust aerojet formula engine according to claim 7, which is characterized in that the combustion chamber with it is hollow
It is connected between driving wheel by mechanical sealing member, the mechanical sealing member is flush-mounted in fixed set thrust plate.
9. momentum thrust aerojet formula engine according to claim 8, which is characterized in that the mechanical sealing member packet
Include the tooth-like packing part in side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810310779.5A CN108194227A (en) | 2018-04-09 | 2018-04-09 | A kind of momentum thrust aerojet formula engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810310779.5A CN108194227A (en) | 2018-04-09 | 2018-04-09 | A kind of momentum thrust aerojet formula engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108194227A true CN108194227A (en) | 2018-06-22 |
Family
ID=62596481
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810310779.5A Pending CN108194227A (en) | 2018-04-09 | 2018-04-09 | A kind of momentum thrust aerojet formula engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108194227A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3059428A (en) * | 1957-05-31 | 1962-10-23 | Galonska Walter Otto | Internal combustion turbine with supercharging turbine for liquid fuels and coal dust |
| CN1693691A (en) * | 2005-04-30 | 2005-11-09 | 张鸿元 | Air compression aeroengine |
| CN106321240A (en) * | 2016-08-19 | 2017-01-11 | 深圳福世达动力科技有限公司 | Centrifugal compression reactive radial-flow internal combustion engine |
-
2018
- 2018-04-09 CN CN201810310779.5A patent/CN108194227A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3059428A (en) * | 1957-05-31 | 1962-10-23 | Galonska Walter Otto | Internal combustion turbine with supercharging turbine for liquid fuels and coal dust |
| CN1693691A (en) * | 2005-04-30 | 2005-11-09 | 张鸿元 | Air compression aeroengine |
| CN106321240A (en) * | 2016-08-19 | 2017-01-11 | 深圳福世达动力科技有限公司 | Centrifugal compression reactive radial-flow internal combustion engine |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180622 |
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| RJ01 | Rejection of invention patent application after publication |