CN109533352A - Aircraft and its engine - Google Patents
Aircraft and its engine Download PDFInfo
- Publication number
- CN109533352A CN109533352A CN201811318322.5A CN201811318322A CN109533352A CN 109533352 A CN109533352 A CN 109533352A CN 201811318322 A CN201811318322 A CN 201811318322A CN 109533352 A CN109533352 A CN 109533352A
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- Prior art keywords
- clutch
- arrangement
- interior
- guide vane
- casing
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- 230000000712 assembly Effects 0.000 claims abstract description 26
- 238000000429 assembly Methods 0.000 claims abstract description 26
- 230000007246 mechanism Effects 0.000 claims description 60
- 230000001105 regulatory effect Effects 0.000 claims description 33
- 238000002485 combustion reaction Methods 0.000 claims description 14
- 238000000926 separation method Methods 0.000 claims description 4
- 230000001360 synchronised effect Effects 0.000 claims description 3
- 239000000306 component Substances 0.000 description 33
- 239000007789 gas Substances 0.000 description 12
- 230000005540 biological transmission Effects 0.000 description 10
- 230000000694 effects Effects 0.000 description 4
- 230000006870 function Effects 0.000 description 4
- 230000008450 motivation Effects 0.000 description 3
- 239000002245 particle Substances 0.000 description 3
- 230000001737 promoting effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000004826 seaming Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The disclosure provides a kind of aircraft and its engine, is related to technical field of aerospace.The engine includes outer casing, interior casing, turbine wheel shaft, arrangement of clutch, rotor assemblies and fan.Outer casing has external admission end and outer outlet side.Interior casing has interior inlet end and interior outlet side, and interior inlet end is extended in outer casing by outer outlet side.Turbine wheel shaft is set in interior casing and is extended in outer casing by interior inlet end.Arrangement of clutch is set in outer casing, and with turbine axis connection, arrangement of clutch can at least switch between first state and the second state.Rotor assemblies are set to outside outer casing, and when arrangement of clutch is in first state, rotor assemblies are sequentially connected by arrangement of clutch and turbine wheel shaft.Fan is set in outer casing and is sheathed on outside arrangement of clutch, and when arrangement of clutch is in the second state, fan is sequentially connected by arrangement of clutch and turbine wheel shaft.
Description
Technical field
This disclosure relates to technical field of aerospace, in particular to a kind of aircraft and the engine of aircraft.
Background technique
Currently, requirement of the people to aircraft performance is higher and higher with the extensive use of aircraft, wherein as winged
The performance of the core component of row device, engine is directly related to the performance of aircraft.In the prior art, by taking helicopter as an example,
Generally using turboaxle motor as power source, rotor rotational is driven by turboaxle motor, to provide for helicopter
Lift；Meanwhile the exhaust velocity of existing turboaxle motor is very low, is nearly free from thrust, turboaxle motor can only pass through
Transmission system drives promote paddle rotation, or by tilting rotor, provide thrust for helicopter, realize that the flat of helicopter flies,
But this can make helicopter, and structure is complicated, and the helicopter of this structure is limited by factors such as rotor blade tip tangential velocities, flies
Scanning frequency degree is lower, general no more than 500km/h, can not further be promoted.
It should be noted that information is only used for reinforcing the reason to the background of the disclosure disclosed in above-mentioned background technology part
Solution, therefore may include the information not constituted to the prior art known to persons of ordinary skill in the art.
Summary of the invention
Flying speed can be improved in a kind of engine for being designed to provide aircraft and aircraft of the disclosure, and advantageous
In the structure for simplifying aircraft.
According to one aspect of the disclosure, a kind of engine of aircraft is provided, comprising:
Outer casing has external admission end and outer outlet side；
Interior casing, has interior inlet end and interior outlet side, and the interior inlet end is extended to described outer by the outer outlet side
In casing；
Turbine wheel shaft extends in the outer casing in the interior casing and by the interior inlet end；
Arrangement of clutch, be set to the outer casing in, and with the turbine axis connection, the arrangement of clutch at least can be first
Switch between state and the second state；
Rotor assemblies are set to outside the outer casing, and when the arrangement of clutch is in first state, the rotor assemblies are logical
It crosses the arrangement of clutch and the turbine wheel shaft is sequentially connected；
Fan in the outer casing and is sheathed on outside the arrangement of clutch, is in the second shape in the arrangement of clutch
When state, the fan is sequentially connected by the arrangement of clutch and the turbine wheel shaft.
In a kind of exemplary embodiment of the disclosure, the arrangement of clutch includes:
First clutch component, including first shell, the first driving link and the first driven member, first driving link can be rotated
Ground be set to the first shell in, first driven member be set to the first shell in and can slide axially, with it is described
First driving link connects or separates；First driving link and the turbine axis connection, the first shell and the rotor group
Part connection；
Second clutch component, including second shell, the second driving link and the second driven member, second driving link can be rotated
Ground is set in the second shell, and second driven member is set to and the second shell and can slide axially, with described the
Two driving links connect or separate；Second driving link be sheathed on the turbine wheel shaft it is outer and with the turbine axis connection, the wind
Fan is sheathed on outside the second shell and connect with the second shell；
When the arrangement of clutch is in first state, first driving link is connect with first driven member, described
Second driving link is separated with second driven member；When the arrangement of clutch is in the second state, first driving link with
The first driven member separation, second driving link are connect with second driven member.
In a kind of exemplary embodiment of the disclosure, the arrangement of clutch further include:
Planetary gear set, including sun gear, planetary gear, planet carrier and ring gear, the sun gear are located in the ring gear,
The planet carrier is fixed in the outer casing, the planetary gear be rotationally connected with the planet carrier and simultaneously with the sun gear
It is engaged with the ring gear；
The turbine wheel shaft is connect by the sun gear with first driving link, and the ring gear and described second is actively
Part connection.
In a kind of exemplary embodiment of the disclosure, the engine further includes jet pipe, is connected to the interior outlet
End.
In a kind of exemplary embodiment of the disclosure, the jet pipe includes:
Fixing pipe is connect with the interior outlet side；
Multiple rotating plates, are distributed in a ring, and are rotatablely connected with the fixing pipe；
Rotating plate driving mechanism is set to the fixing pipe, and connect with each rotating plate, for driving each rotating plate synchronous
Rotation.
In a kind of exemplary embodiment of the disclosure, the engine further includes guide vane regulating mechanism, the guide vane tune
Saving mechanism includes:
Multiple guide vanes, multiple guide vanes are spaced apart in a ring in the periphery of the interior casing, and are turned with the interior casing
Dynamic connection；
Guide vane driving mechanism is connect set on the periphery of the interior casing, and with each guide vane, for driving each described lead
Leaf rotation, to adjust the gap of adjacent two guide vane.
In a kind of exemplary embodiment of the disclosure, the quantity of the guide vane regulating mechanism is multiple, and is included at least
First guide vane regulating mechanism and the second guide vane regulating mechanism, the first guide vane regulating mechanism is located in the outer casing, and position
In the fan close to the side of the interior casing；The second guide vane regulating mechanism is located at outside the outer casing.
In a kind of exemplary embodiment of the disclosure, the engine further include:
Locking device is set to the arrangement of clutch, is used for when the arrangement of clutch is in first state, by the fan
Locking.
In a kind of exemplary embodiment of the disclosure, the engine further include:
Combustion chamber is set in the interior casing；
Compressor is set in the interior casing, and is located at the combustion chamber close to the side of the fan；
Turbine assembly is set in the interior casing, and is located at side of the combustion chamber far from the fan.
In a kind of exemplary embodiment of the disclosure, including engine described in above-mentioned any one.
The aircraft and its engine of the disclosure can make arrangement of clutch be in the first shape when taking off, hovering and landing
State makes rotor assemblies and turbine wheel shaft be sequentially connected by arrangement of clutch, so as to drive rotor assemblies by turbine wheel shaft, for flight
Device provides the required lift that takes off, hovers and land；When aircraft is flat winged, arrangement of clutch is in the second state, passes through clutch
Device makes fan and turbine wheel shaft be sequentially connected, and the rotation of turbine wheel shaft driving fan is formed and is discharged by outer outlet side and interior outlet side
Air-flow, flat fly required thrust to generate.
It can make the structure of aircraft from using promoting paddle and relevant transmission system to realize that the flat of aircraft flies as a result,
It is simplified.Meanwhile when avoiding aircraft high-performance cruise rotor blade tip tangential velocity limitation, improve and equal winged flight speed
Degree, the flying speed is even up to 800km/h.In addition, the centrifugal force that fan is generated in rotation may also function as particle separation
Effect, so that engine is discharged, prevent the sundries such as sandstone enter interior casing.
It should be understood that above general description and following detailed description be only it is exemplary and explanatory, not
The disclosure can be limited.
Detailed description of the invention
The drawings herein are incorporated into the specification and forms part of this specification, and shows the implementation for meeting the disclosure
Example, and together with specification for explaining the principles of this disclosure.It should be evident that the accompanying drawings in the following description is only the disclosure
Some embodiments for those of ordinary skill in the art without creative efforts, can also basis
These attached drawings obtain other attached drawings.
Fig. 1 is the schematic diagram of disclosure embodiment engine.
Fig. 2 is the schematic diagram of the arrangement of clutch of disclosure embodiment engine.
In figure: 1, outer casing；2, interior casing；3, turbine wheel shaft；4, arrangement of clutch；41, the first driving link；42, first is driven
Part；43, the second driving link；44, the second driven member；45, sun gear；46, planetary gear；47, planet carrier；48, ring gear；5, rotor
Component；51, rotor；6, fan；7, jet pipe；71, fixing pipe；72, rotating plate；8, guide vane regulating mechanism；81, the first guide vane is adjusted
Mechanism；82, the second guide vane regulating mechanism；9, combustion chamber；10, compressor；11, turbine assembly；111, the first turbine；112, second
Turbine；12, output shaft；100, by-pass air duct；200, main duct.
Specific embodiment
Example embodiment is described more fully with reference to the drawings.However, example embodiment can be with a variety of shapes
Formula is implemented, and is not understood as limited to embodiment set forth herein；On the contrary, thesing embodiments are provided so that the present invention will
Fully and completely, and by the design of example embodiment comprehensively it is communicated to those skilled in the art.Identical attached drawing in figure
Label indicates same or similar structure, thus the detailed description that will omit them.
Although the term of relativity, such as "upper" "lower" is used to describe a component of icon for another in this specification
The relativeness of one component, but these terms are in this manual merely for convenient, for example, with reference to the accompanying drawings described in show
The direction of example.It is appreciated that, if making it turn upside down the device overturning of icon, the component described in "upper" will
As the component in "lower".When certain structure is at other structures "upper", it is possible to refer to that certain structural integrity is formed in other structures
On, or refer to that certain structure is " direct " and be arranged in other structures, or refer to that certain structure is arranged by the way that another structure is " indirect " in other knots
On structure.Term "one", " one ", "the" and " described " to indicate there are one or more elements/component part/etc.；Term
" comprising " and " having " to indicate the open meaning being included and refer in addition to list element/component part/
Also may be present Deng except other element/component part/etc.；Term " first ", " second " only use as label, are not to it
The quantity of object limits.
Disclosure embodiment provides a kind of engine of aircraft, which can be helicopter, unmanned plane etc.,
It is only illustrated by taking helicopter as an example below, but not limited to this.As shown in Figure 1, the engine may include outer casing 1, interior machine
Casket 2, turbine wheel shaft 3, arrangement of clutch 4, rotor assemblies 5 and fan 6, in which:
Outer casing 1 can have external admission end and outer outlet side.
Interior casing 2 can have interior inlet end and interior outlet side, which is extended in outer casing 1 by outer outlet side.
Turbine wheel shaft 3 can be set in interior casing 2 and be extended in outer casing 1 by interior inlet end.
Arrangement of clutch 4 can be set in outer casing 1, and connect with turbine wheel shaft 3, arrangement of clutch 4 at least can first state with
Switch between second state.
Rotor assemblies 5 can be set to outside outer casing 1, and when arrangement of clutch 4 is in first state, rotor assemblies 5 pass through clutch
Device 4 and turbine wheel shaft 3 are sequentially connected.
Fan 6 is set in outer casing 1 and is sheathed on outside arrangement of clutch 4, when arrangement of clutch 4 is in the second state, fan 6
It is sequentially connected by arrangement of clutch 4 and turbine wheel shaft 3.
The engine of disclosure embodiment can make arrangement of clutch 4 be in the in aircraft takeoff, hovering and landing
One state makes rotor assemblies 5 and turbine wheel shaft 3 be sequentially connected, so as to drive rotor group by turbine wheel shaft 3 by arrangement of clutch 4
Part 5 provides the required lift that takes off, hovers and land for aircraft；When aircraft is flat winged, arrangement of clutch 4 is made to be in second
State makes fan 6 and turbine wheel shaft 3 be sequentially connected by arrangement of clutch 4, and the rotation of 3 driving fan 6 of turbine wheel shaft forms air inlet gas
Stream pressurization flies required thrust to generate and put down, at this point, can lock rotor 51, becomes fixed-wing form.It as a result, can be from
Using promoting paddle and relevant transmission system to realize, the flat of aircraft flies, and is simplified the structure of aircraft.Meanwhile it avoiding
The limitation of rotor blade tip tangential velocity when aircraft high-performance cruise, improves cruising speed, and flying speed even up to arrives
800km/h.In addition, the centrifugal force that fan 6 is generated in rotation may also function as the effect of particle separation, from so that sandstone etc. is miscellaneous
Engine is discharged in object, guarantees engine work.
Each section of disclosure embodiment engine is described in detail with reference to the accompanying drawing:
Outer casing 1 can be tubular structure, and cross section can be circle, ellipse etc., not do particular determination herein.Together
When, outer casing 1 can have the external admission end and outer outlet side of perforation, so that air-flow passes through.
Interior casing 2 can be tubular structure, and cross section can be round, ellipse or polygon etc., and it is special not do herein
It limits.Interior casing 2 can have perforation interior inlet end and interior outlet side, so that air-flow passes through.Meanwhile interior casing 2 can be with outer machine
Casket 1 is coaxially disposed, i.e. the central axes of the two are conllinear, and the interior inlet end of interior casing 2 can be extended to outer by the outer outlet side of outer casing 1
In casing 1, and the by-pass air duct 100 that passes through of gas supply stream is formed between outer casing 1, and formed in interior casing 2 gas supply stream across
The generation type of main duct 200, main duct 200 is not particularly limited herein.
Length of the interior casing 2 on the direction of central axes can be greater than the length of outer casing 1, thus the interior outlet side of interior casing 2
Outside outer casing 1, certainly, length of the interior casing 2 on the direction of central axes also may be less than or equal to the length of outer casing 1, make
Casing 2 can be fully located in outer casing 1 in obtaining.
Turbine wheel shaft 3 can be set in interior casing 2, and the central axes of turbine wheel shaft 3 and the central axes of interior casing 2 are collinearly arranged.Together
When, one end of turbine wheel shaft 3 can be extended in outer casing 1 by the interior inlet end of interior casing 2, the other end can inwardly casing 2 it is interior go out
Gas end extends.
Arrangement of clutch 4 can be set in outer casing 1, and connect with turbine wheel shaft 3, arrangement of clutch 4 at least can first state with
Switch between second state.Turbine wheel shaft 3 and rotor assemblies 5 or fan 6 can be sequentially connected by arrangement of clutch 4, will pass through whirlpool
Wheel shaft 3 respectively drives rotor assemblies 5 or fan 6.
Rotor assemblies 5 can be set to outside outer casing 1, such as at the top of aircraft etc..When arrangement of clutch 4 is in first state,
Rotor assemblies 5 can be sequentially connected by arrangement of clutch 4 and turbine wheel shaft 3, at this point, turbine wheel shaft 3 can drive rotor assemblies 5, to be
Aircraft provides lift, realizes taking off, hover and landing for aircraft.For example, rotor assemblies 5 may include rotationally rotor 51
And transmission mechanism, rotor 51 is connect by the transmission mechanism and arrangement of clutch 4 with turbine wheel shaft 3, specifically, arrangement of clutch 4 can
It is connect by output shaft 12 with transmission mechanism, transmission mechanism can be connect with rotor 51.The pivot center of rotor 51 can be perpendicular to whirlpool
Wheel shaft 3 is arranged, and rotor 51 can be driven to rotate by turbine wheel shaft 3.
Fan 6 can be set in outer casing 1, and can be sheathed on outside arrangement of clutch 4, when arrangement of clutch 4 is in the second state,
Fan 6 and turbine wheel shaft 3 can be sequentially connected by arrangement of clutch 4, at this point, turbine wheel shaft 3 can driving fan 6 rotate, to enter by-pass air duct
100 and 200 air-flow of main duct be tentatively pressurized, which is discharged by by-pass air duct 100 and main duct 200, is flown to form driving
Row device equals winged thrust.
Arrangement of clutch 4 is illustrated below:
Arrangement of clutch 4 may include the first clutch component and the second clutch component, in which:
Turbine wheel shaft 3 is connect by the first clutch component with rotor assemblies 5, and when arrangement of clutch 4 is in first state, the
One clutch component is in gearing state, so that turbine wheel shaft 3 can be driven by the first clutch component to rotor assemblies 5, makes rotor 51
Rotation.For example:
First clutch component may include first shell, the first driving link 41 and the first driven member 42, wherein first shell can
For tubular structure, the first driving link 41 is rotatably arranged in first shell, and the first driven member 42 is set in first shell, with the
One shell is slidably connected, can sliding axially along first shell；It is sliding along the axial direction of first shell by the first driven member 42 of control
It is dynamic, the first driven member 42 can be made to connect or separate with the first driving link 41.First driving link 41 can be connect with turbine wheel shaft 3, and first
Shell can be connect with rotor assemblies 5.When arrangement of clutch 4 is in first state, the first driving link 41 and the first driven member 42 connect
It connects, so that the first clutch component is in gearing state, the first driven member 42 and first shell synchronous with the first driving link 41 can turn
It is dynamic, so that rotor 51 be driven to rotate.
For the ease of driving the first driven member 42 sliding, the first clutch component may also include the first driving mechanism, and first drives
Motivation structure may include the first gas source, and the first gas source can be connected to first shell, can be by being filled with gas to first shell, to push
First driven member 42 reciprocatingly slides, and this will not be detailed here for concrete principle, certainly, can also drive the first driven member otherwise
42 slidings, will not enumerate herein.
Turbine wheel shaft 3 is connect by the second clutch component with fan 6, and when arrangement of clutch 4 is in the second state, second from
Seaming element is in gearing state, so that turbine wheel shaft 3 can be driven by the second clutch component to fan 6, rotates fan 6.
For example: the second clutch component may include second shell, the second driving link 43 and the second driven member 44, wherein
Second shell can be tubular structure, can be sheathed on turbine wheel shaft 3 and be located in outer casing 1 outside one end, and the second driving link 43 can be rotated
Ground is set in second shell；Second driven member 43 can be set in second shell, and be slidably connected with second shell, can be along second shell
Body slides axially；By controlling the second sliding axially along second shell of driven member 44, the second driven member 44 and second can be made
Driving link 43 connects or separates.Second driving link 43 can be connect with turbine wheel shaft 3, can be rotated under the drive of turbine wheel shaft 3, fan 6
It can be sheathed on outside second shell, and be connect with second shell.When arrangement of clutch 4 is in the second state, the second driving link 43 with
The connection of second driven member 44, so that the second clutch component is in gearing state, the second driven member 44 and second shell can be with second
Driving link 43 rotates synchronously, so that fan 6 be driven to rotate.
For the ease of driving the second driven member 44 sliding, the second clutch component may also include the second driving mechanism, and second drives
Motivation structure may include the second gas source, and the second gas source can be connected to second shell, can be by being filled with gas to second shell, to push
Second driven member 44 reciprocatingly slides, and this will not be detailed here for concrete principle, certainly, can also drive the second driven member otherwise
44 slidings, will not enumerate herein.
It should be noted that the first clutch component is in gearing state when arrangement of clutch 4 is in first state, i.e.,
One driving link 41 is connect with the first driven member 42, at this point, the first clutch component can be at discrete state, i.e., the second driving link 43 can
It is separated with the second driven member 44.Certainly, at this point, the second clutch component can also be in gearing state.Second is in arrangement of clutch 4
When state, the second clutch component is in gearing state, i.e. the second driving link 43 is connect with the second driven member 44, at this point, first from
Seaming element is in discrete state, i.e. the first driving link 41 is separated with the first driven member 42.Certainly, at this point, the second clutch component
It can be at gearing state.
In addition, arrangement of clutch 4 may also include planetary gear set, and turbine wheel shaft 3 can pass through the planetary gear component for the ease of transmission
It is not connect with the first clutch component and the second clutch component.The planetary gear set may include sun gear 45, planetary gear 46, planet carrier 47
With ring gear 48, in which:
Sun gear 45 can be located in ring gear 48, and be sheathed on outside turbine wheel shaft 3, and connect with turbine wheel shaft 3, can be with turbine wheel shaft
3 rotate synchronously；Meanwhile sun gear 45 is also connect with the first driving link 41 of the first clutch component, so that passing through sun gear 45 will
Turbine wheel shaft 3 is connected with the first driving link 41.Ring gear 48 is rotatably arranged in outer casing 1, and is sheathed on turbine wheel shaft 3
Outside, the second driving link 43 of the second clutch component can be fixedly connected with ring gear 48.Planet carrier 47 is securable in outer casing 1,
Planetary gear 46 is rotationally connected with planet carrier 47, and planetary gear 46 can be between sun gear 45 and ring gear 48, and simultaneously and too
Sun wheel 45 and ring gear 48 engage.To pass through sun gear 45, planetary gear 46 and ring gear 48 for turbine wheel shaft 3 and the second driving link
43 connect.Turbine wheel shaft 3 can drive sun gear 45 to rotate, and rotate the first driving link 41, and under the transmission of planetary gear 46,
The rotation of the second driving link 44 can be driven by ring gear 48.
The explanation of arrangement of clutch 4 is merely illustrative above, in the other embodiment of the disclosure, can also be adopted
Above-mentioned function is realized with other clutches, no longer an an example is enumerated herein.
The engine of disclosure embodiment may also include jet pipe 7, and one end of jet pipe 7 may connect to interior casing 2
Interior outlet side, the other end extend to the direction far from interior casing 2, for being discharged to guidance air-flow.For the ease of adjusting exhaust speed
Degree, jet pipe 7 may include fixing pipe 71, rotating plate 72 and rotating plate driving structure, in which:
One end of fixing pipe 71 can be connect with the interior outlet side of interior casing 2, and the other end prolongs to the direction far from interior casing 2
It stretches, and the central axes of fixing pipe 71 can be conllinear with the central axes of interior casing 2.The shape of the cross section of fixing pipe 71 can be circle
Shape, ellipse or polygon etc..
The quantity of rotating plate 72 can be to be multiple, and multiple rotating plates 72 can be distributed in a ring, and each rotating plate 72 with fixing pipe 71
One end far from interior casing 2 is rotatablely connected, to surround the adjustable ring structure of a bore.
Rotating plate driving mechanism can be set to fixing pipe 71, and connect simultaneously with each rotating plate 72, can be driven by rotating plate driving mechanism
Each rotating plate 72 is moved simultaneously to rotating on the inside or outside of fixing pipe 71, to adjust the bore of above-mentioned ring structure, rotating plate driving mechanism
Specific structure do not do particular determination herein, as long as can drive rotating plate 72 rotate, for example, rotating plate driving mechanism may include
Multiple connecting rods and multiple pressurized struts, each pressurized strut can respectively drive the rotation of rotating plate 72 by each connecting rod.
In aircraft takeoff, hovering and landing, arrangement of clutch 4 is in first state, and turbine wheel shaft 3 drives rotor assemblies 5
Rotor 51 rotate, at this point, can be driven by rotating plate driving mechanism each rotating plate 72 to the outside of fixing pipe 71 rotate, spray tail
Pipe 7 is in expansion state, reduces exhaust velocity, reduces thrust.When aircraft is flat winged, can be driven by rotating plate driving mechanism
Each rotating plate 72 is rotated to the inside of fixing pipe 71, then jet pipe 7 is convergence state, increases exhaust velocity, to improve thrust,
Increase level speed.
For the ease of adjusting the air-flow being discharged by by-pass air duct 100, the engine of disclosure embodiment can also include leading
Leaf regulating mechanism 8, the guide vane regulating mechanism 8 may include guide vane and guide vane driving mechanism, in which:
The quantity of guide vane can be to be multiple, and multiple guide vanes can be spaced apart in a ring in the periphery of interior casing 2, and with it is interior
Casing 2 is rotatablely connected, the pivot center of guide vane can radially extending along interior casing 2, each guide vane can radially inside casing 2
Outside extend.
Guide vane driving mechanism can be set to the periphery of interior casing 2, and connect simultaneously with each guide vane, can by guide vane driving mechanism
Each guide vane is driven to rotate, to adjust the angle of guide vane, thus the gap of two neighboring guide vane, and then adjusting makes guide vane regulating mechanism
The handling capacity of 8 pairs of air-flows.The specific structure of guide vane driving mechanism does not do particular determination herein, as long as guide vane rotation can be driven i.e.
Can, for example, guide vane driving mechanism may include pressurized strut and linkage mechanism, linkage mechanism is connect with guide vane, and pressurized strut can pass through connection
Motivation structure drives each guide vane rotation, and linkage mechanism may include multiple connecting rods, and this will not be detailed here for specific structure, lead as long as can drive
Leaf rotation.
The quantity of above-mentioned guide vane regulating mechanism 8 can be to be multiple, and each guide vane regulating mechanism 8 can be along the axial direction of interior casing 2 point
Cloth, and multiple guide vane regulating mechanisms 8 include at least the first guide vane regulating mechanism 81 and the second guide vane regulating mechanism 82, wherein the
One guide vane regulating mechanism 81 can be located in outer casing 1, and be located at fan 6 close to the side of interior casing 2, the second guide vane regulating mechanism
82 can be located at outside outer casing 1.
In aircraft takeoff, hovering and landing, arrangement of clutch 4 is in first state, and turbine wheel shaft 3 drives rotor assemblies 5
Rotor 51 rotate, at this point, the gap of the guide vane of the first guide vane regulating mechanism 81 and the second guide vane regulating mechanism 82 can be made to subtract
Small, i.e. the first guide vane regulating mechanism 81 and the second guide vane regulating mechanism 82 turn down, to reduce the gas being discharged by by-pass air duct 100
Stream, and since the first guide vane regulating mechanism 81 is to the barrier effect of air-flow, air-flow can be made to flow to main duct 200, be conducive to mention
The power of high turbine wheel shaft 3, to improve the revolving speed of the rotor 51 of rotor assemblies 5.When aircraft is flat winged, the first guide vane tune can be made
The gap of the guide vane of section mechanism 81 and the second guide vane regulating mechanism 82 increases, i.e. the first guide vane regulating mechanism 81 and the second guide vane
Regulating mechanism 82, which turns down, to be opened greatly, is improved the capacity of by-pass air duct 100, is conducive to increase thrust, increases level speed.
For the ease of braking to fan 6, the engine of disclosure embodiment may also include locking device, locking dress
Setting can be set in outer casing 1, when arrangement of clutch 4 is in first state, can lock fan 6 by locking device, make fan 6
Stalling.Further, it is connect in the first driving link 41 with the first driven member 42, and the second driving link 43 divides with the second driven member 44
From when, locking device can lock fan 6.The structure of locking device does not do particular determination herein, as long as fan 6 can be locked and can
Unlock.
The engine of disclosure embodiment may also include combustion chamber 9, compressor 10 and turbine assembly 11, in which:
Combustion chamber 9 can be set in interior casing 2, for by fuel oil and gas mixing and burning, to form high-temperature high-pressure air flow,
The air-flow can inwardly casing 2 interior outlet side flowing.Combustion chamber 9 can be an integral structure with interior casing 2, or be set to interior casing 2
Interior individual cavity.
Compressor 10 is located in interior casing 2, and is located at combustion chamber 9 close to the side of fan 6, enters main duct for compressing
200 air-flow provides pressure condition to improve the pressure of air-flow for gas burning in combustion chamber 9.
Turbine assembly 11 can be set in interior casing 2, and be located at side of the combustion chamber 9 far from fan 6, after combustion chamber 9 is burnt
The air-flow of ejection may act on turbine assembly 11, rotate turbine assembly 11, so that turbine wheel shaft 3 be driven to rotate.Turbine assembly 11
It may include being socketed on the first turbine 111 and the second turbine 112 on turbine wheel shaft 3,111 He of the first turbine along the axis of turbine wheel shaft 3
Second turbine 112 can rotate under the action of air-flow.
Disclosure embodiment also provides a kind of aircraft, which may include the engine of above embodiment, should
Details are not described herein for the structure of engine.The aircraft can be helicopter, unmanned plane etc..Simultaneously as the aircraft uses
The engine of above embodiment, therefore, can from using promoting paddle and relevant transmission system to realize that the flat of aircraft flies,
It is simplified the structure of aircraft.Meanwhile the centrifugal force that fan 6 is generated in rotation may also function as the effect that particle separates,
It prevents the sundries such as sandstone from entering interior casing 2, guarantees that aircraft works normally.
Those skilled in the art after considering the specification and implementing the invention disclosed here, will readily occur to its of the disclosure
Its embodiment.This application is intended to cover any variations, uses, or adaptations of the disclosure, these modifications, purposes or
Person's adaptive change follows the general principles of this disclosure and including the undocumented common knowledge in the art of the disclosure
Or conventional techniques.The description and examples are only to be considered as illustrative, and the true scope and spirit of the disclosure are by appended
Claim is pointed out.
Claims (10)
1. a kind of engine of aircraft characterized by comprising
Outer casing has external admission end and outer outlet side；
Interior casing, has interior inlet end and interior outlet side, and the interior inlet end extends to the outer casing by the outer outlet side
It is interior；
Turbine wheel shaft extends in the outer casing in the interior casing and by the interior inlet end；
Arrangement of clutch, be set to the outer casing in, and with the turbine axis connection, the arrangement of clutch at least can be in first state
And second switch between state；
Rotor assemblies are set to outside the outer casing, and when the arrangement of clutch is in first state, the rotor assemblies pass through institute
It states arrangement of clutch and the turbine wheel shaft is sequentially connected；
Fan in the outer casing and is sheathed on outside the arrangement of clutch, when the arrangement of clutch is in the second state,
The fan is sequentially connected by the arrangement of clutch and the turbine wheel shaft.
2. engine according to claim 1, which is characterized in that the arrangement of clutch includes:
First clutch component, including first shell, the first driving link and the first driven member, first driving link are rotationally set
In in the first shell, first driven member is set in the first shell and can slide axially, with described first
Driving link connects or separates；First driving link and the turbine axis connection, the first shell and the rotor assemblies connect
It connects；
Second clutch component, including second shell, the second driving link and the second driven member, second driving link are rotationally set
In in the second shell, second driven member is set to the second shell and can slide axially, to lead with described second
Moving part connects or separates；Second driving link be sheathed on the turbine wheel shaft it is outer and with the turbine axis connection, the fan set
It is connect outside the second shell and with the second shell；
When the arrangement of clutch is in first state, first driving link is connect with first driven member, and described second
Driving link is separated with second driven member；When the arrangement of clutch is in the second state, first driving link with it is described
The separation of first driven member, second driving link are connect with second driven member.
3. engine according to claim 2, which is characterized in that the arrangement of clutch further include:
Planetary gear set, including sun gear, planetary gear, planet carrier and ring gear, the sun gear is located in the ring gear, described
Planet carrier is fixed in the outer casing, the planetary gear be rotationally connected with the planet carrier and simultaneously with the sun gear and institute
State ring gear engagement；
The turbine wheel shaft is connect by the sun gear with first driving link, and the ring gear and second driving link connect
It connects.
4. engine according to claim 1, which is characterized in that the engine further includes jet pipe, is connected to described
Interior outlet side.
5. engine according to claim 4, which is characterized in that the jet pipe includes:
Fixing pipe is connect with the interior outlet side；
Multiple rotating plates, are distributed in a ring, and are rotatablely connected with the fixing pipe；
Rotating plate driving mechanism is set to the fixing pipe, and connect with each rotating plate, for driving each rotating plate is synchronous to turn
It is dynamic.
6. engine according to claim 1, which is characterized in that the engine further includes guide vane regulating mechanism, described
Guide vane regulating mechanism includes:
Multiple guide vanes, multiple guide vanes are spaced apart in a ring in the periphery of the interior casing, and are connected with the interior casing rotation
It connects；
Guide vane driving mechanism is connect set on the periphery of the interior casing, and with each guide vane, for driving each guide vane to turn
It is dynamic, to adjust the gap of adjacent two guide vane.
7. engine according to claim 6, which is characterized in that the quantity of the guide vane regulating mechanism is multiple, and extremely
It less include the first guide vane regulating mechanism and the second guide vane regulating mechanism, the first guide vane regulating mechanism is located at the outer casing
It is interior, and it is located at the fan close to the side of the interior casing；The second guide vane regulating mechanism is located at outside the outer casing.
8. engine according to claim 1, which is characterized in that the engine further include:
Locking device is set to the arrangement of clutch, for when the arrangement of clutch is in first state, the fan to be locked
It is fixed.
9. engine according to claim 1-8, which is characterized in that the engine further include:
Combustion chamber is set in the interior casing；
Compressor is set in the interior casing, and is located at the combustion chamber close to the side of the fan；
Turbine assembly is set in the interior casing, and is located at side of the combustion chamber far from the fan.
10. a kind of aircraft, which is characterized in that including the described in any item engines of claim 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811318322.5A CN109533352A (en) | 2018-11-07 | 2018-11-07 | Aircraft and its engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811318322.5A CN109533352A (en) | 2018-11-07 | 2018-11-07 | Aircraft and its engine |
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| Publication Number | Publication Date |
|---|---|
| CN109533352A true CN109533352A (en) | 2019-03-29 |
Family
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811318322.5A Pending CN109533352A (en) | 2018-11-07 | 2018-11-07 | Aircraft and its engine |
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| CN102239321A (en) * | 2008-10-08 | 2011-11-09 | 希尔莱特有限责任公司 | Hybrid propulsive engine including at least one independently rotatable propeller/fan |
| CN106988926A (en) * | 2017-05-22 | 2017-07-28 | 西北工业大学 | Whirlpool axle turbofan combined cycle engine |
| CN108190006A (en) * | 2015-08-14 | 2018-06-22 | 赵红艳 | Jet-propelled wing flap lift-rising connection wing system and its aircraft |
| CN108583859A (en) * | 2018-05-04 | 2018-09-28 | 西北工业大学 | A kind of VTOL binary aircraft |
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- 2018-11-07 CN CN201811318322.5A patent/CN109533352A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1952369A (en) * | 2005-10-19 | 2007-04-25 | 通用电气公司 | Gas turbine engine assembly and methods of assembling same |
| CN101105183A (en) * | 2006-07-11 | 2008-01-16 | 通用电气公司 | Turbofan engine and its operation method |
| CN102239321A (en) * | 2008-10-08 | 2011-11-09 | 希尔莱特有限责任公司 | Hybrid propulsive engine including at least one independently rotatable propeller/fan |
| CN108190006A (en) * | 2015-08-14 | 2018-06-22 | 赵红艳 | Jet-propelled wing flap lift-rising connection wing system and its aircraft |
| CN106988926A (en) * | 2017-05-22 | 2017-07-28 | 西北工业大学 | Whirlpool axle turbofan combined cycle engine |
| CN108583859A (en) * | 2018-05-04 | 2018-09-28 | 西北工业大学 | A kind of VTOL binary aircraft |
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Application publication date: 20190329 |
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