CN106438107A - Blade propeller side jet type aeroengine - Google Patents
Blade propeller side jet type aeroengine Download PDFInfo
- Publication number
- CN106438107A CN106438107A CN201610839365.2A CN201610839365A CN106438107A CN 106438107 A CN106438107 A CN 106438107A CN 201610839365 A CN201610839365 A CN 201610839365A CN 106438107 A CN106438107 A CN 106438107A
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- CN
- China
- Prior art keywords
- fuel
- main shaft
- leaf oar
- blade propeller
- aero
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- 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
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
-
- 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
- F02C7/222—Fuel flow conduits, e.g. manifolds
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The invention relates to the technical field of aeroengines, in particular to a blade propeller side jet type aeroengine. By adoption of the blade propeller side jet type aeroengine, the technical defects that an existing rocket engine is complex in structure, and the reliability and fuel optimality are limited are overcome. The blade propeller side jet type aeroengine comprises a spindle, a spindle frame assembly, a blade propeller and a case. The blade propeller is fixedly connected with the spindle. The spindle is movably connected to the spindle frame assembly, and the spindle frame assembly is fixedly mounted on the case. An energy nozzle is arranged on the side edge of the blade propeller, a blade propeller fuel channel communicating with the energy nozzle is formed in the blade propeller, and a spindle fuel channel communicating with the blade propeller fuel channel is formed in the spindle. Kinetic energy generated by fuel spraying can make the blade propeller rotate, the structure is simple and easy to manufacture, and firmness and reliability are guaranteed; and various kinds of fuel can be applied, the blade propeller side jet type aeroengine is suitable for gas fuel, liquid fuel, solid powder fuel and solid particle fuel and particularly suitable for highly-explosive fuel gunpowder, explosives and relevant highly-explosive products for propelling the blade propeller to operate.
Description
Technical field
The present invention relates to aero-engine technology field.
Background technology
Airborne vehicle provides the engine of flight required drive, mainly has four types：Piston aviation engine, combustion gas whirlpool
Turbine, punching engine and rocket motor engine；At present, also do not have one kind suitable with rocket motor mechanomotive force, it moves
Can be again that structure is simply easily made on existing routine aero-engine, solid reliability is with can to apply fuel many simultaneously
The aero-engine of sample.
Content of the invention
In sum, it is an object of the invention to solving existing rocket motor structure complexity, reliability, fuel washability
The technical deficiency such as limited, and leaf oar side spray hairdo aero-engine is proposed.
For solving technical problem proposed by the invention, the technical scheme of employing is：Leaf oar side spray hairdo aero-engine,
It is characterized in that described engine includes：Main shaft, main shaft frame member, leaf oar and casing；Leaf oar is fixedly connected with main shaft, main shaft
It is movably connected on main strut assemblies, main strut assemblies are fixedly mounted with casing；The side of described leaf oar is provided with energy spout,
It is provided with the leaf oar fuel channel communicating with energy spout in leaf oar, in described main shaft, be provided with the master communicating with leaf oar fuel channel
Axle fuel channel, the outer wall that main shaft is located at main shaft frame module position is provided with the main shaft fuel inlet communicating with main shaft fuel channel,
Main shaft frame member inwall or and the outer wall of main shaft be provided with fuel corresponding with main shaft fuel inlet supply groove, main shaft frame
Offer on assembly and supply groove corresponding support fuel channel with fuel, the entrance of support fuel channel is described engine
Fuel inlet.
Described leaf oar is provided with gravity drop hammer.
Two side positions being located at fuel supply groove on described main strut assemblies are respectively equipped with bearing assembly.
Described bearing assembly includes the bearing being socketed on main shaft respectively, jump ring, oil gas envelope and fuel envelope.
Described casing includes the tail shell covering in outside leaf oar, and tail shell is additionally provided with recoil corresponding with energy spout
Plate.
Described main shaft fuel channel and leaf oar fuel channel junction are provided with horn-like combustion chamber.
Described main strut assemblies are provided with the generator assembly being generated electricity by main shaft drives.
Described leaf oar is replaced using the lever without windward side.
Beneficial effects of the present invention are：The side of the leaf oar of the present invention is provided with energy spout, dynamic produced by fuel eruption
Leaf oar can be made to rotate, structure simply easily makes, solid reliability, fuel can be applied to have a diversity, gas, liquid, solid powder,
Solid particle fuel is all applicable, is particularly suited for high detonation material gunpowder, explosive and the quick-fried leaf oar that pushes away of related high quick-fried product and operates.
Brief description
Fig. 1 is the principle schematic diagram. of embodiments of the invention 1；
Fig. 2 is the main shaft of inventive embodiment 1 and the cross-sectional structure at main shaft frame assembly position；
Fig. 3 is the perspective view of inventive embodiment 1；
Fig. 4 is the principle schematic diagram. of inventive embodiment 2.
Specific embodiment
Below in conjunction with accompanying drawing and currently preferred specific embodiment, the structure of the present invention is further described.
Embodiment 1
With reference to shown in Fig. 1 and Fig. 3, leaf oar side spray hairdo aero-engine of the present invention includes：Main shaft 1, main shaft frame member 2,
Leaf oar 3 and casing 4；Leaf oar 3 is fixedly connected with main shaft 1, and main shaft 1 is movably connected on main strut assemblies 2, main strut assemblies 2 with
Casing 4 fixedly mounts.
The side of leaf oar 3 is provided with energy spout 31, and fuel erupts produced kinetic energy from energy spout 31 and promotes leaf oar 3 to revolve
Turn, leaf oar 3 can also only be made lever and use, every leaf oar 3 is all rotated with main shaft 1 for fulcrum, and leaf oar 3 is longer, main shaft 1 output
Moment of torsion is bigger.It is provided with the leaf oar fuel channel 32 communicating with energy spout 31 in leaf oar 3.
It is provided with the main shaft fuel channel 11 communicating with leaf oar fuel channel 32 in main shaft 1；Main shaft 1 is located at main strut assemblies 2
The outer wall of position is provided with the main shaft fuel inlet 12 communicating with main shaft fuel channel 11.Main shaft frame member 2 inwall and main shaft fuel
Groove 21 supplied by the corresponding fuel of entrance 12, main strut assemblies 2 offers and supplies the corresponding support fuel of groove 21 with fuel
Passage 22, the entrance of support fuel channel 22 is the fuel inlet of described engine.In specific implementation process, fuel supply is recessed
Groove 21 can be toroidal cavity or semi-ring connected in star, and the purposes that groove 21 supplied by fuel is to realize support fuel channel 22 and rotation
The main shaft fuel channel 11 turning in the main shaft 1 of state turns on all the time, and the fuel that can import support fuel channel 22 persistently imports
Main shaft fuel channel 11.Furthermore it is possible to only in the outer wall of main shaft 1, or it is provided with and main shaft fuel inlet in the outer wall of main shaft 1 simultaneously
Groove supplied by 12 corresponding fuel.
In order to ensure that leaf oar 3 can rotate in continued smooth under effect of inertia, leaf oar 3 is provided with gravity drop hammer, is conducive to accelerating
Afterburning.
Two side positions being located at fuel supply groove 21 on main strut assemblies 2 are respectively equipped with bearing assembly；Bearing assembly bag
Include the bearing being socketed on main shaft respectively, jump ring, oil gas envelope and fuel envelope.Bearing assembly provides for main shaft 1 and supports simultaneously, rises
Prevent fuel losses to sealing.
Casing 4 includes the tail shell 41 covering in outside leaf oar 3, because the fuel that energy spout 31 ejects will not be all
Can be clean in moment burning, fuel gathering of burning again in tail shell 41 is advantageous for reaching capacitation amount and environmental protection purpose again；For
The propulsive thrust of lifting leaf oar 3, tail shell 11 is additionally provided with recoil plate 42 corresponding with energy spout.
Embodiment 2
The present embodiment be embodiment 1 general principle on the basis of improve further, in main shaft fuel channel 11 and leaf oar fuel
Passage 32 junction is provided with horn-like combustion chamber 13.Fuel can be lighted in horn-like combustion chamber 13, in main shaft fuel channel
The screw mechanism 14 that fuel accelerates propulsion can also be increased in 11.Screw mechanism 14 is conducive to energy quickly to move to spout.For
Realize synchronous generator during main shaft 1 rotation, main strut assemblies 2 are provided with and are driven, by main shaft 1, the generator assembly 23 generating electricity.
Manufacturing under its tangible modern technologies equipment condition of the kinetic energy structure of the present invention to be illustrated is very simple thing, as long as
Leaf oar is designed to cavity or is hollow structure, and just can be easily achieved engine in leaf oar side design energy spout start
Accelerate.The cavity structure of its leaf oar is mainly used to complete two purposes：1st, utilize cavity structure to transmit fuel, be transmitted from fuel
To leaf oar energy spout and firing point quick-fried after propulsive thrust to obtain leaf oar motion kinetic energy.2nd, cavity structure is utilized to transmit energy
Amount, in the junction horn-like combustion chamber of design of leaf oar and main shaft and quick-fried in this ignition point, high-pressure energy passes through leaf oar cavity
The propulsive thrust being transferred to the generation of leaf oar energy spout is obtaining leaf oar motion energy.
The main shaft fuel channel of main shaft, as fuel channel function, can be designed to semi-hollow and full hollow:Work as spindle end
When portion needs machine driving function, fuel can be supplied using semi-hollow pedestal direction.Full hollow cavity structure is primarily adapted for use in master
The fuel supply of shaft end direction.
Main strut assemblies design in bottom warm area, are an advantage over due to not having high temperature to affect its reliability under same speed conditions
Conventional aero-engine；In addition, design house generator is very easy to realize in main strut assemblies.
Do not have tail shell to be also a more complete engine of ratio, but have tail shell just can reach following two purposes：1st, after erupting
Fuel and tail shell reaction recoil are advantageous for the afterburning acceleration of leaf oar.2nd, not all fuel can be clean in moment burning, combustion
Material gathering of burning again in tail shell is advantageous for reaching capacitation amount and environmental protection purpose again.3rd, design recoil plate in tail shell inwall,
The energy impact recoil plate face of energy spout can obtain more reaction forces, high detonation material light a fire on recoil plate be the most preferable it
Place.
The non-aero-engine of machine deformationization:As long as deducting the windward side of leaf oar so as to become lever, lever side spout is used
Push the main shaft that the dynamic lever other end connects, lever is rotated track circumferentially with main shaft for fulcrum, makes the another of main shaft
End transmission mechanical energy, engine this moment has changed and has become lever side spray hairdo kinetic energy engine, alternatively referred to as Lever machine.
Fuel explanation:The applicable present invention of gas, liquid, solid powder, solid particle fuel, with conventional fuel Lai complete
Becoming the difficulty that eruption promotion leaf oar moves to be far above applies high detonation material powder explosive and the quick-fried leaf oar that pushes away of related high quick-fried product to operate.When
So conventional fuel is the optimal eruption effect needing to find fuel.The requirement to engine material for the high detonation material is naturally high
Many, in particularly pressure fuel-resistant impact high requests.Can be accelerated with gas starter liquid solid fuel is afterburning in application.Start
Machine has a possibility of bombing bore as firearms, but much less than the probability of firearms bombing bore, firearms many because of bullet bombing bore, in belonging to together
Absolutely empty chamber transmission energy the machine is provided with that the comparatively safe ground of bullet is many, and actual high-voltage is subtracted by leaf oar or lever rotating speed.
Operation principle：1st, the operation principle of leaf oar side spray hairdo engine it is simply that erupted produced with leaf oar side fuel
Kinetic energy makes leaf oar and circumferentially restrains, with the main shaft being connected, the aero-engine that movement locus principle works.2. lever side spray hairdo is sent out
The operation principle of motivation is the engine being changed by leaf paddle, and its operation principle is：Lever side spout thrust promotes lever,
The spindle operation that linkage is connected, thus realizing obtaining mechanical energy in another termination of main shaft.
Feature performance benefit：When leaf oar reaches three to five meters or more sizes with lever length, its machine is surprising, fuels and energy certainly
Full, on producing super big build machine, fuel capability has no problem, and the adaptation ability of manufacture material needs progressively to be confirmed.Root
According to the well-known saying of Archimedes, give my lever I just can prize the earth, confirm that this word is more definite with Lever machine, in this machine
Upper fulcrum, lever, strength is all very sufficient, and it is whole world Explosive Energy the most brave and fierce that this strength can be the whole world.Lever machine is with I
CN201410227219.5 directly make a concerted effort to coordinate with intelligent grid on power-generating industry by quick-fried formula engine, has thermoelectricity, water power down to nuclear power
The startup-shutdown on demand that all cannot accomplish, will need the ability accelerating.Its respond is in seconds.Also will for kinetic energy with hydrogen is quick-fried
It is environment-protective motor.
Lever machine heat energy utilization, change planes that shell to obtain heat energy for shell and tube heat exchanger, shell of changing planes to obtain for Central Air-Conditioner
Cold and hot energy.
Claims (8)
1. leaf oar side spray hairdo aero-engine is it is characterised in that described engine includes：Main shaft, main shaft frame member, leaf oar
And casing；Leaf oar is fixedly connected with main shaft, and spindle mobility is connected on main strut assemblies, main strut assemblies fixing peace with casing
Dress；The side of described leaf oar is provided with energy spout, is provided with the leaf oar fuel channel communicating with energy spout in leaf oar, described
Be provided with the main shaft fuel channel communicating with leaf oar fuel channel in main shaft, main shaft be located at main shaft frame module position outer wall be provided with
The main shaft fuel inlet that main shaft fuel channel communicates, main shaft frame member inwall or and main shaft outer wall be provided with and main shaft combustion
Material entrance corresponding fuel supply groove, main strut assemblies offers and supplies groove corresponding support fuel channel with fuel,
The entrance of support fuel channel is the fuel inlet of described engine.
2. leaf oar side spray hairdo aero-engine according to claim 1 it is characterised in that：Described leaf oar is provided with weight
Power is hammered into shape.
3. leaf oar side spray hairdo aero-engine according to claim 1 it is characterised in that：On described main strut assemblies
Two side positions supplying groove positioned at fuel are respectively equipped with bearing assembly.
4. leaf oar side spray hairdo aero-engine according to claim 2 it is characterised in that：Described bearing assembly includes
There are the bearing being socketed on main shaft respectively, jump ring, oil gas envelope and fuel envelope.
5. leaf oar side spray hairdo aero-engine according to claim 1 it is characterised in that：Described casing includes cover
Tail shell outside in leaf oar, tail shell is additionally provided with recoil plate corresponding with energy spout.
6. leaf oar side spray hairdo aero-engine according to claim 1 it is characterised in that：Described main shaft fuel channel
It is provided with horn-like combustion chamber with leaf oar fuel channel junction.
7. leaf oar side spray hairdo aero-engine according to claim 1 it is characterised in that：On described main strut assemblies
It is provided with the generator assembly being generated electricity by main shaft drives.
8. leaf oar side spray hairdo aero-engine according to claim 1 it is characterised in that：Described leaf oar is not using containing
The lever of windward side replaces.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610839365.2A CN106438107A (en) | 2016-09-22 | 2016-09-22 | Blade propeller side jet type aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610839365.2A CN106438107A (en) | 2016-09-22 | 2016-09-22 | Blade propeller side jet type aeroengine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106438107A true CN106438107A (en) | 2017-02-22 |
Family
ID=58166103
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610839365.2A Pending CN106438107A (en) | 2016-09-22 | 2016-09-22 | Blade propeller side jet type aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106438107A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106524226A (en) * | 2016-11-15 | 2017-03-22 | 姚永新 | Spiral movement combustion type combustor |
| CN110273784A (en) * | 2018-03-13 | 2019-09-24 | 姚永新 | Screw eruption type engine |
| CN110685933A (en) * | 2018-07-06 | 2020-01-14 | 姚永新 | Novel high-efficient environment humidification cooling presses down dirt machine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1173144A (en) * | 1965-10-14 | 1969-12-03 | Rolls Royce | Power Plants including a Ducted Fan |
| US4208590A (en) * | 1978-01-06 | 1980-06-17 | Blomquist Cecil R | Jet electric generator |
| US5408824A (en) * | 1993-12-15 | 1995-04-25 | Schlote; Andrew | Rotary heat engine |
| CN1115004A (en) * | 1995-04-20 | 1996-01-17 | 郭颖 | Reaction type jet engine |
| CN1892010A (en) * | 2005-12-27 | 2007-01-10 | 王学章 | Jet external-rotor engine |
| CN101363387A (en) * | 2008-09-17 | 2009-02-11 | 王学章 | Rotating athodyd |
-
2016
- 2016-09-22 CN CN201610839365.2A patent/CN106438107A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1173144A (en) * | 1965-10-14 | 1969-12-03 | Rolls Royce | Power Plants including a Ducted Fan |
| US4208590A (en) * | 1978-01-06 | 1980-06-17 | Blomquist Cecil R | Jet electric generator |
| US5408824A (en) * | 1993-12-15 | 1995-04-25 | Schlote; Andrew | Rotary heat engine |
| CN1115004A (en) * | 1995-04-20 | 1996-01-17 | 郭颖 | Reaction type jet engine |
| CN1892010A (en) * | 2005-12-27 | 2007-01-10 | 王学章 | Jet external-rotor engine |
| CN101363387A (en) * | 2008-09-17 | 2009-02-11 | 王学章 | Rotating athodyd |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106524226A (en) * | 2016-11-15 | 2017-03-22 | 姚永新 | Spiral movement combustion type combustor |
| CN110273784A (en) * | 2018-03-13 | 2019-09-24 | 姚永新 | Screw eruption type engine |
| CN110685933A (en) * | 2018-07-06 | 2020-01-14 | 姚永新 | Novel high-efficient environment humidification cooling presses down dirt machine |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170222 |