CN206439121U - Jet engine and aircraft - Google Patents
Jet engine and aircraft Download PDFInfo
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- CN206439121U CN206439121U CN201621475181.4U CN201621475181U CN206439121U CN 206439121 U CN206439121 U CN 206439121U CN 201621475181 U CN201621475181 U CN 201621475181U CN 206439121 U CN206439121 U CN 206439121U
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Abstract
The utility model provides a kind of jet engine and aircraft, is related to the technical field of engine, the jet engine includes：Fan, gas collection cylinder body, compressor and turbine in housing are successively set on from top to bottom；Also include being set in combustion chamber cylinder body outside the compressor, the combustion chamber cylinder body being provided with multiple combustion chambers, multiple combustion chambers are along the circumferentially disposed of the compressor；The gas collection funnel is connected with the air inlet of the compressor by the first tracheae, and the gas outlet of the compressor is connected with the combustion chamber by the second tracheae；Outside air sequentially passes through the fan, and the collection chamber, the compressor and the combustion chamber spray from main duct jet pipe.The length that alleviates jet engine present in prior art is longer, baroque technical problem.
Description
Technical field
The utility model is related to technical field of engines, more particularly, to a kind of jet engine and aircraft.
Background technology
Engine be it is a kind of other forms can be converted into the machine of mechanical energy, including (gasoline is sent out such as internal combustion engine
Motivation etc.), external-combustion engine (Stirling engine, steam engine etc.), motor etc..If internal combustion engine is typically that chemical energy is converted into machine
Tool energy.Engine is not only suitable for power generating apparatus, can also refer to the whole machine including power set (such as：Petrol engine, boat
Empty engine).Engine is born in Britain earliest, so, the concept of engine also comes from English, and its literal sense refers to that
" mechanical device for producing power ".
Traditional jet engine uses axial-flow compressor or centrifugal-flow compressor.The work of axial-flow compressor
Principle is pressurizeed by the rotation of propeller blade, and air is pressed into combustion chamber.The principle of centrifugal-flow compressor is to utilize
Centrifugal force throws air into combustion chamber.Traditional jet engine is axial-flow compressor and centrifugal-flow compressor, both pressures
The mode of entrance of the gas of mechanism of qi is entered at the propeller blade of compressor.
Either centrifugal compressor or axial-flow compressor, can all cause the resistance of jet engine to increase.And pass
The axial-flow compressor of system or the length of centrifugal-flow compressor are longer, and space-consuming is big, and weight is big, complicated.
Utility model content
The purpose of this utility model is to provide a kind of jet engine and aircraft, to alleviate present in prior art
The length of jet engine is longer, baroque technical problem.
The jet engine that the utility model is provided, including：Fan, air collecting cylinder in housing are successively set on from top to bottom
Body, compressor and turbine；
Also include being set in the combustion chamber cylinder body outside the compressor, the combustion chamber cylinder body being provided with multiple burnings
Room, multiple combustion chambers are along the circumferentially disposed of the compressor；
The gas collection funnel is connected with the air inlet of the compressor by the first tracheae, the gas outlet of the compressor with
The combustion chamber is connected by the second tracheae；
Outside air sequentially passes through the fan, the collection chamber, the compressor and the combustion chamber, and from main duct
Jet pipe sprays.
Further, the compressor includes first order compressor, second level compressor and third level compressor；
The turbine includes first order turbine, second level turbine and fan turbine；
The first order turbine is connected with the first order compressor；
The second level turbine is connected with the second level compressor；
The fan turbine is connected with the third level compressor.
Further, the fan is connected by first axle with the fan turbine；
The third level compressor is connected by first axle with the fan turbine；
The second level compressor is connected by the second axle with the second level turbine；
The first order compressor is connected by the 3rd axle with the first order turbine；
Second axle is quill shaft with the 3rd axle, and second axle sleeve is located at outside the first axle, and described
Clutch shaft bearing is provided between second axle and the first axle；
3rd axle sleeve is provided with the second axle outside second axle, and between the 3rd axle and second axle
Hold.
Further, the combustion chamber is cast combustion chamber.
Further, the housing is provided with support；
3rd bearing is provided between the first axle and the support.
Further, the compressor includes：At least two sections cylinder bodies, final drive shaft, rotary-piston component, baffle assemblies；
The rotary-piston component is arranged on the final drive shaft, and the final drive shaft is rotatably mounted to the cylinder
In the inner chamber of body；
The baffle assembly is installed in rotation at the segmentation of two sections of cylinder bodies；
The inwall of the baffle assembly, the rotary-piston component and the cylinder body can constitute closed air chamber；
Air inlet and gas outlet are respectively equipped with the cylinder body.
Further, the cylinder body is annular, including upper cylinder body and lower cylinder body, and the inwall of the upper cylinder body is provided with described
Air inlet and annular first groove, the inwall of the lower cylinder body are provided with the gas outlet and annular second groove；
The rotary-piston component is provided with the sealing ring coordinated with first groove and second groove；
The upper cylinder body and the lower cylinder body are formed after being connected by fastener can accommodate the sky of the rotary-piston component
Between.
Further, the rotary-piston component includes first gear and card；
The gear is arranged on the final drive shaft；
The card is provided with piston rod, and the piston rod is provided with piston；
The sealing ring is arranged in the card.
Further, the baffle assembly includes the second rotating shaft, second gear and rotor plate；
Second rotating shaft is rotatably arranged on the cylinder cap；
The rotor plate, which is provided with, can make the breach that the piston passes through.
The utility model additionally provides a kind of aircraft, including described jet engine.
What the utility model was brought has the beneficial effect that：
The jet engine that the utility model is provided, including：Fan, gas collection cylinder body, combustion chamber cylinder body and compressor；Gas collection
Gas collection funnel is provided with cylinder body, combustion chamber cylinder body is set in outside compressor, and combustion chamber is provided with the cylinder body of combustion chamber；Combustion chamber edge
Compressor it is circumferentially disposed；Fan, gas collection cylinder body, combustion chamber cylinder body are set gradually from top to bottom；Gas collection funnel and compressor
Air inlet is connected by the first tracheae, and the gas outlet of compressor is connected with combustion chamber by the second tracheae；Compressor and fan point
Not by turbine drives, outside air sequentially passes through fan, collection chamber, compressor combustion chamber, portion of air and high-temperature fuel gas
Turbine and the rotation of fan turbine are driven, rotation generation thrust makes a part of high temperature and high pressure gas be sprayed from main duct jet pipe to turbine at a high speed
Go out, produce thrust.Combustion chamber cylinder body is set in outside compressor, and combustion chamber is provided with the cylinder body of combustion chamber；Combustion chamber is along compressor
It is circumferentially disposed；The length of jet engine is shortened by this design, to reduce the complexity of jet engine.May be used also
To save the space of jet engine occupancy.Gas collection cylinder body is arranged on after fan, and the area ratio of occupancy is simultaneously little, thus
Bigger bypass ratio can be formed, is conducive to increasing thrust.Gas collection funnel above gas collection cylinder body serves collection air and formed
The effect of the compression on basis, can lift the possibility that air enters the first tracheae.The position of gas collection cylinder body, combustion chamber and compressor
The resistance for foring minimum may.The jet engine length that the utility model is provided is short, occupies little space, lightweight, structure
Simply.
The utility model additionally provides a kind of aircraft, including the jet engine that the utility model is provided, and uses this practicality
The space that the aircraft of the jet engine of new offer can be saved in the aircraft machine of jet engine occupancy, increases interior of aircraft
Free space.
Brief description of the drawings
, below will be right in order to illustrate more clearly of the utility model embodiment or technical scheme of the prior art
The accompanying drawing used required in embodiment or description of the prior art is briefly described, it should be apparent that, describe below
In accompanying drawing be some embodiments of the present utility model, for those of ordinary skill in the art, do not paying creativeness
On the premise of work, other accompanying drawings can also be obtained according to these accompanying drawings.
The structural representation for the jet engine that Fig. 1 provides for the utility model embodiment；
Fig. 2 is Fig. 1 partial enlarged drawing；
The top view for the combustion chamber cylinder body that Fig. 3 provides for the utility model embodiment；
The top view for the gas collection cylinder body that Fig. 4 provides for the utility model embodiment；
The structural representation for the compressor that Fig. 5 provides for the utility model embodiment.
Icon：1- compressors；2- fans；5- turbines；7- gas collection cylinder bodies；8- combustion chambers cylinder body；11- upper cylinder bodies；
12- lower cylinder bodies；13- final drive shafts；32- first gears；33- cards；The rotating shafts of 41- second；42- second gears；43-
Rotor plate；431- breach；61- fasteners；62- mounting holes；111- air inlets；121- gas outlets；331- piston rods；
3311- pistons；15- first order compressors；16- second level compressor；17- third level compressors；71- gas collection funnels；
81- combustion chambers；51- first order turbines；52- second level turbine；53- fan turbines；91- first axles；The axles of 92- second；
The axles of 93- the 3rd；100- housings；102- supports；103- 3rd bearings；At 105- segmentations；The tracheaes of 1041- first；
The tracheaes of 1042- second.
Embodiment
The technical solution of the utility model is clearly and completely described below in conjunction with accompanying drawing, it is clear that described
Embodiment is a part of embodiment of the utility model, rather than whole embodiments.Based on the embodiment in the utility model, sheet
The every other embodiment that field those of ordinary skill is obtained under the premise of creative work is not made, belongs to this practicality
Novel protected scope.
, it is necessary to explanation in description of the present utility model, term " " center ", " on ", " under ", it is "left", "right", " perpendicular
Directly ", the orientation or position relationship of the instruction such as " level ", " interior ", " outer " are, based on orientation shown in the drawings or position relationship, to be only
Described for the ease of description the utility model and simplifying, rather than to indicate or imply that signified device or element must have specific
Orientation, with specific azimuth configuration and operation, therefore it is not intended that to limitation of the present utility model.In addition, term " the
One ", " second ", " the 3rd " are only used for describing purpose, and it is not intended that indicating or implying relative importance.
, it is necessary to which explanation, unless otherwise clearly defined and limited, term " are pacified in description of the present utility model
Dress ", " connected ", " connection " should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or integratedly
Connection；Can be mechanical connection or electrical connection；Can be joined directly together, can also be indirectly connected to by intermediary,
It can be the connection of two element internals.For the ordinary skill in the art, above-mentioned art can be understood with concrete condition
Concrete meaning of the language in the utility model.
The structural representation for the jet engine that Fig. 1 provides for the utility model embodiment；Fig. 2 is Fig. 1 partial enlargement
Figure；The top view for the combustion chamber cylinder body that Fig. 3 provides for the utility model embodiment；Fig. 4 provides for the utility model embodiment
The top view of gas collection cylinder body；The structural representation for the compressor that Fig. 5 provides for the utility model embodiment.
Embodiment one
As Figure 1-5, the jet engine that the utility model is provided, including：Housing is successively set on from top to bottom
Fan 2, gas collection cylinder body 7, compressor 1 and turbine in 100；Combustion chamber cylinder body 8 is set in outside compressor 1, in combustion chamber cylinder body 8
Provided with multiple combustion chambers 81, multiple combustion chambers 81 are along the circumferentially disposed of compressor 1；The air inlet of gas collection funnel 71 and compressor 1
111 are connected by the first tracheae 1041, and the gas outlet 121 of compressor 1 is connected with combustion chamber 81 by the second tracheae 1042；It is extraneous
Air sequentially passes through fan 2, and collection chamber, compressor 1 and combustion chamber 81 spray from main duct jet pipe.
Specifically, outside air sequentially passes through fan 2, collection chamber, the combustion chamber 81 of compressor 1, portion of air and height
Warm gas driven turbine and fan turbine 53 rotate, and rotation generation thrust makes a part of high temperature and high pressure gas from intension to turbine at a high speed
Road jet pipe sprays, and produces thrust.Combustion chamber cylinder body 8 is set in outside compressor 1, and combustion chamber 81 is provided with combustion chamber cylinder body 8；Combustion
Room 81 is burnt along the circumferentially disposed of compressor 1, and the length of jet engine is shortened by this design, started to reduce jet
The complexity of machine.The space of jet engine occupancy can also be saved.Gas collection cylinder body 7 is arranged on after fan 2, the area of occupancy
Ratio is simultaneously little, can thus form bigger bypass ratio, is conducive to increasing thrust.Gas collection funnel 71 above gas collection cylinder body 7
The effect for the compression for collecting air and basis of formation is served, the possibility that air enters the first tracheae 1041 can be lifted.Gas collection
The resistance that the position of cylinder body 7, combustion chamber 81 and compressor 1 forms minimum may.The jet engine that the utility model is provided
Length is short, occupies little space, lightweight, simple in construction.
Specifically, fan 2 is rotated, and outside air is sucked into the jet engine described in the present embodiment, outside air warp
Cross after the gas collection funnel 71 in gas collection cylinder body 7, compressed into compressor 1, the pressure-air of formation enters combustion chamber 81, in combustion
Room 81 and fuel oil mixed combustion are burnt, high temperature, the gas of high pressure is formed, high temperature, the gas of high pressure contain huge energy, and part is passed
Fan turbine 53 and turbine are passed, to corresponding driving fan 2 and compressor 1, another part sprays from main duct jet pipe, production
Raw thrust.
When the jet engine that the utility model is provided starts, rotated by motor rotor driven, while compressor 1 starts
Work, then after the compressed air that compressor 1 is provided has reached igniting, begins to open fuel oil and is lighted a fire.Work as combustion
After oil drop fire success, turbine starts to rotate under the high-temperature gas that combustion chamber 81 sprays, and at this moment subsequent rotor driven rotation can
Motor and the connection of motor is disengaged to stop.
In the alternative of the present embodiment, compressor 1 includes first order compressor 15, second level compressor 16 and the third level
Compressor 17；Turbine includes first order turbine 51, second level turbine 52 and fan turbine 53；First order turbine 51 and first order pressure
Mechanism of qi 15 is connected；Second level turbine 52 is connected with second level compressor 16；Fan turbine 53 and the third level compressor 17.
The driving first order of first order turbine 51 compressor 15；Second level turbine 52 drives second level compressor 16；Fan whirlpool
Wheel 53 drives third level compressor 17.
It should be noted that compressor 1 can include multistage, turbine can also include multistage turbine.In the present embodiment, three
Level is example, is not limited.
Compressor 1 described in the present embodiment includes first order compressor 15, second level compressor 16 and third level compressor
17；Turbine includes first order turbine 51 and second level turbine 52 is preferred scheme.
In the alternative of the present embodiment, fan 2 is connected by first axle 91 with fan turbine 53；Third level compressor 17
It is connected by first axle 91 with fan turbine 53；Second level compressor 16 is connected by the second axle 92 with second level turbine 52；The
One-level compressor 15 is connected by the 3rd axle 93 with first order turbine 51；Second axle 92 and the 3rd axle 93 are quill shaft, the second axle
92 are sheathed on outside first axle 91, and clutch shaft bearing is provided between the second axle 92 and first axle 91；3rd axle 93 is sheathed on second
Second bearing is provided with outside axle 92, and between the 3rd axle 93 and the second axle 92.
It should be noted that turbine can include multistage turbine, there are several turbines, just there are several axles to correspond to therewith.This reality
Apply in example, three-level is example, is not limited.
The axle of this jet engine has two regions.Front end is a region, and rear end is a region.Front end is fan 2
Axle, has several fans 2 just to correspond to several axles.Rear end is turbine wheel shaft, has several turbines just to correspond to several axles.Jet engine
Rotary-piston type compressor 1 is used, compressor 1 is laid out the inside in combustion chamber 81, and combustion chamber 81 is designed in compressor 1
Surrounded compressor 1, shortens the length of jet engine by this design, to reduce the complexity of jet engine
Property.Space in the machine that jet engine takes can also be saved for aircraft, increases the free space of interior of aircraft.
In the alternative of the present embodiment, combustion chamber 81 is cast combustion chamber 81.
Each tubular burner inner liner in pipe-type chamber 81 has single overcoat, constitutes a can burner 81.One
Jet engine can have several can burners 81, circumferentially on jet engine, wherein several combustion chambers 81 are filled
There is igniter.Flame is passed by flame tube interconnector between each combustion chamber 81 and is pressed.Pipe-type chamber 81 is easily debugged, intensity and rigidity
Good, easy disassembly and maintenance.
In the alternative of the present embodiment, housing 100 is provided with support 102；The first axle 91 and the support 102 it
Between be provided with 3rd bearing 103.Support 102 can be used for support 3rd bearing 103 and rotor.
As shown in figure 5, in the alternative of the present embodiment, compressor 1 includes：At least two sections cylinder bodies, final drive shaft 13, rotations
Turn a work 3311 components of plug and baffle assembly；The component of rotary-piston 3311 is arranged on final drive shaft 13, and final drive shaft 13 is rotatable
In the inner chamber of cylinder body；Baffle assembly is rotatably arranged on 105 at the segmentation of two sections of cylinder bodies；Baffle assembly, rotation
The component of piston 3311 can constitute closed air chamber with the inwall of cylinder body；Air inlet 111 and gas outlet 121 are respectively equipped with cylinder body.
The compressor 1 that the utility model is provided includes：At least two sections cylinder bodies, final drive shaft 13, the components of rotary-piston 3311
And baffle assembly.Compressor 1 is operated under the drive of final drive shaft 13, final drive shaft 13 drive rotary-piston component and every
Plate is rotated, and the component of piston 3311 is directly driven by the final drive shaft 13, and gas enters in cylinder body from air inlet 111, promotes rotation
The component of piston 3311 is rotated in cylinder body, while baffle assembly also rotation orderly in cylinder body, by 3311 groups of rotary-piston
Gas is pressed into the sealed gas chamber of the inwall of baffle assembly, the component of rotary-piston 3311 and cylinder body composition by part, as rotation is lived
The rotation of 3311 components is filled in, gas is compressed, and gas is discharged from gas outlet 121 afterwards.It is simple in construction, and compressed air efficiency
Height, can substitute traditional axial-flow compressor 1 and apply among jet engine.
In the alternative of the present embodiment, cylinder body is annular, including upper cylinder body 11 and lower cylinder body 12, the inwall of upper cylinder body 11
Air inlet 111 and annular first groove are provided with, the inwall of lower cylinder body 12 is provided with gas outlet 121 and annular second groove；Rotation
Turn a work 3311 components of plug and be provided with the sealing ring coordinated with the first groove and the second groove；Upper cylinder body 11 and lower cylinder body 12 are by tight
Firmware 61 is formed after connecting can accommodate the space of the component of rotary-piston 3311.
Annulus cylinder body is divided into some sections, and it is a kind of preferred scheme that annulus cylinder body is divided into 2 sections, can essentially be 2 sections
To N sections.Each section on annulus cylinder body has two duck eyes, and one is air inlet 111, and one is gas outlet 121.Work as rotation
Piston 3311 is when rotation at full speed, it is necessary to have gas outlet 121 allow the air of compression go out from, it is also necessary to there is air inlet 111 to allow
The rear portion of piston 3311 can suck air.
In addition, cylinder body be divided into above and below two parts, whole annulus cylinder body is just formed after assembling.This be in order to be able to will rotation
The component of piston 3311 is fit into the design carried out within annulus cylinder body.
In the alternative of the present embodiment, the component of rotary-piston 3311 includes first rotating shaft 31, first gear 32 and card
33；First rotating shaft 31 is connected with final drive shaft 13；Card 33 is provided with piston rod 331, and piston rod 331 is provided with piston 3311；
Sealing ring is arranged in card 33.
There is piston 3311 end of the component piston rod 331 of rotary-piston 3311, when the component of rotary-piston 3311 rotates
Wait, piston 3311 just carries out circular motion in annulus cylinder body.It should be noted that compression is batch (-type), only work as rotor plate
43 are only compression motion when separating two sections of cylinder bodies.In addition, there is an annulus sealing in the card 33 of the component of rotary-piston 3311
Circle and annulus cylinder body are brought into close contact, and form sealing effectiveness, and so that piston 3311 is when rotating, annulus cylinder body will not gas leakage.
It is preferred that, piston 3311 is circle.
In the alternative of the present embodiment, baffle assembly includes the second rotating shaft 41, second gear 42 and rotor plate 43；Second
Rotating shaft 41 is spindle rotationally arranged on cylinder cap；Rotor plate 43, which is provided with, can make the breach 431 that piston 3311 passes through.
Second rotating shaft 41 can be rotary shaft, rotary shaft, and the second rotating shaft 41 is arranged on cylinder cap after being installed by bearing
On, as long as can the second rotating shaft 41 rotation.
In the utility model embodiment, when being rotated to be directed at final drive shaft 13 at breach 431 rotor plate 43, rotation
Turn a work plug 3311 just just to move between two segmentations, then can just pass through rotor plate 43, subsequently enter another point
The annulus cylinder body of section.
Baffle assembly is arranged on 105 at the segmentation of annulus cylinder body, towards final drive shaft at the breach 431 on rotor plate 43
When 13, the space between two segmentations of annulus cylinder body will link together, and now, rotary-piston 3311 can pass through.When
Other positions of baffle assembly, when annulus cylinder body section is blocked at the position not being open, now two segmentation cylinder bodies between sky
Between come by cut-off.At this moment, one section of closed air chamber will be formed, piston 3311 can enter in the air chamber of this fan annular
The action of row compressed gas.
The shape of breach 431 above rotor plate 43：Rotary-piston 3311 can either be ensured, baffle assembly, rotation are made again
The inwall of the component of piston 3311 and cylinder body constitutes closed air chamber.The actually He of piston 3311 of the component of rotary-piston 3311
The shape pulled when card 33 is rotated.The shape that typically one circle and a bar are pulled along a circular arc
Shape.Specific shape will be drawn to much, empirically result determine.
Compressor 1 also includes cylinder cap；Cylinder cap includes upper cylinder cover and lower cylinder cap；Support is respectively equipped with upper cylinder cover and lower cylinder cap
Frame and fixed mount；Upper cylinder cover is arranged on the top of upper cylinder body 11, and upper cylinder cover is connected with upper cylinder body 11 by fastener；Lower cylinder cap
The lower section of the lower cylinder body 12 is arranged on, and lower cylinder cap is connected with the lower cylinder body 12 by fastener.
It is between segmentation or completely unconnected because annulus cylinder body is segmentation, can only be by the way that different segmentations be mounted in
Fix, the cylinder body of segmentation can be formed a whole by upper cylinder cover and lower cylinder cap above the cylinder cap of compressor 1.During installation,
The mounting hole being arranged on cylinder cap is passed through respectively by upper cylinder cover and upper cylinder body 11, lower cylinder cap and lower cylinder body 12 by using fastener
It is installed together.
In the alternative of the present embodiment, piston 3311 is in round.
It should be noted that multiple baffle assemblies：For forming sealing between the segmentation of cylinder body and connecting two kinds of effects,
Synchronized with piston 3311 by gear system, when rotary-piston 3311, which rotates one, to be enclosed, baffle assembly also have rotated N
Circle.And when piston 3311 will pass through the place between two segmentations in annulus cylinder body, baffle assembly is necessarily rotated
When coincidence to breach 431 with annulus cylinder body section, such rotary-piston 3311 could pass through the gap between segmentation.Every
Movement relation between board component and rotary-piston component can be realized by gear train, but be not limited to gear train.
In summary, this has advantages below using the jet engine of new offer：
1st, the traditional jet engine of resistance ratios is smaller, because the area that gas collection cylinder body 7 takes is than traditional axial-flow type pressure
Mechanism of qi and centrifugal-flow compressor will be small, so that resistance is smaller.Combustion chamber 81 and rotary-piston type compressor have gas collection cylinder body 7
Above keeping off, therefore be not further added by extra resistance.
2nd, bigger bypass ratio, the area very little that gas collection cylinder body 7 takes, therefore fan 2 can have bigger area to be used for
Increase bypass ratio.Therefore thrust can more effectively be increased.
3rd, shorter length：Because used rotary-piston type compressor, and by rotary-piston type compressor and combustion chamber
81 the same areas are placed, so the length for saving traditional axial-flow compressor 1 or centrifugal-flow compressor 1 takes, therefore energy
Enough make the whole length of jet engine shorter.
4th, lighter weight：Because rotary-piston type compressor is more efficient, lightweight packages are lighter, so sending out jet
The main screw lift of motivation can accomplish lighter.
Embodiment two
The utility model additionally provides a kind of aircraft, including jet engine.
The utility model additionally provides a kind of aircraft, including the jet engine that the utility model is provided, and uses this practicality
The space that the aircraft of the jet engine of new offer can be saved in the aircraft machine of jet engine occupancy, increases interior of aircraft
Free space.
Finally it should be noted that：Various embodiments above is only limited to illustrate the technical solution of the utility model, rather than to it
System；Although the utility model is described in detail with reference to foregoing embodiments, one of ordinary skill in the art should
Understand：It can still modify to the technical scheme described in foregoing embodiments, or to which part or whole
Technical characteristic carries out equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from this practicality newly
The scope of each embodiment technical scheme of type.
Claims (10)
1. a kind of jet engine, it is characterised in that including：Be successively set on from top to bottom fan in housing, gas collection cylinder body,
Compressor and turbine；
Also include being set in the combustion chamber cylinder body outside the compressor, the combustion chamber cylinder body being provided with multiple combustion chambers, it is many
The individual combustion chamber is along the circumferentially disposed of the compressor；
The gas collection funnel is connected with the air inlet of the compressor by the first tracheae, the gas outlet of the compressor with it is described
Combustion chamber is connected by the second tracheae；
Outside air sequentially passes through the fan, the collection chamber, the compressor and the combustion chamber, and from main duct jet pipe
Spray.
2. jet engine according to claim 1, it is characterised in that the compressor includes first order compressor, the
Two-stage compressor and third level compressor；
The turbine includes first order turbine, second level turbine and fan turbine；
The first order turbine is connected with the first order compressor；
The second level turbine is connected with the second level compressor；
The fan turbine is connected with the third level compressor.
3. jet engine according to claim 2, it is characterised in that the fan passes through first axle and the fan whirlpool
Wheel connection；
The third level compressor is connected by first axle with the fan turbine；
The second level compressor is connected by the second axle with the second level turbine；
The first order compressor is connected by the 3rd axle with the first order turbine；
Second axle is quill shaft with the 3rd axle, and second axle sleeve is located at outside the first axle, and described second
Clutch shaft bearing is provided between axle and the first axle；
3rd axle sleeve is provided with second bearing outside second axle, and between the 3rd axle and second axle.
4. jet engine according to claim 3, it is characterised in that the combustion chamber is cast combustion chamber.
5. jet engine according to claim 4, it is characterised in that the housing is provided with support；
3rd bearing is provided between the first axle and the support.
6. the jet engine according to claim 1,2 or 4, it is characterised in that the compressor includes：At least two sections cylinders
Body, final drive shaft, rotary-piston component and baffle assembly；
The rotary-piston component is arranged on the final drive shaft, and the final drive shaft is rotatably mounted to the cylinder body
In inner chamber；
The baffle assembly is installed in rotation at the segmentation of two sections of cylinder bodies；
The inwall of the baffle assembly, the rotary-piston component and the cylinder body can constitute closed air chamber；
Air inlet and gas outlet are respectively equipped with the cylinder body.
7. jet engine according to claim 6, it is characterised in that the cylinder body is annular, including upper cylinder body is with
Cylinder body, the inwall of the upper cylinder body is provided with the air inlet and annular first groove, and the inwall of the lower cylinder body is provided with institute
State gas outlet and annular second groove；
The rotary-piston component is provided with the sealing ring coordinated with first groove and second groove；
The upper cylinder body and the lower cylinder body are formed after being connected by fastener can accommodate the space of the rotary-piston component.
8. jet engine according to claim 7, it is characterised in that the rotary-piston component include first gear and
Card；
The gear is arranged on the final drive shaft；
The card is provided with piston rod, and the piston rod is provided with piston；
The sealing ring is arranged in the card.
9. jet engine according to claim 8, it is characterised in that the baffle assembly includes the second rotating shaft, second
Gear and rotor plate；
Second rotating shaft is rotatably arranged on cylinder cap；
The rotor plate, which is provided with, can make the breach that the piston passes through.
10. a kind of aircraft, it is characterised in that including the jet engine described in claim any one of 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621475181.4U CN206439121U (en) | 2016-12-30 | 2016-12-30 | Jet engine and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621475181.4U CN206439121U (en) | 2016-12-30 | 2016-12-30 | Jet engine and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206439121U true CN206439121U (en) | 2017-08-25 |
Family
ID=59642134
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621475181.4U Withdrawn - After Issue CN206439121U (en) | 2016-12-30 | 2016-12-30 | Jet engine and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206439121U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106523186A (en) * | 2016-12-30 | 2017-03-22 | 黄祖辉 | Jet engine and airplane |
-
2016
- 2016-12-30 CN CN201621475181.4U patent/CN206439121U/en not_active Withdrawn - After Issue
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106523186A (en) * | 2016-12-30 | 2017-03-22 | 黄祖辉 | Jet engine and airplane |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20170825 Effective date of abandoning: 20180810 |