CN108518284A - Turbojet engine and its oil channel structures - Google Patents
Turbojet engine and its oil channel structures Download PDFInfo
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- CN108518284A CN108518284A CN201810346361.XA CN201810346361A CN108518284A CN 108518284 A CN108518284 A CN 108518284A CN 201810346361 A CN201810346361 A CN 201810346361A CN 108518284 A CN108518284 A CN 108518284A
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- oil
- bearing
- bearing block
- rid
- oily
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 76
- 238000007789 sealing Methods 0.000 claims abstract description 39
- 239000003208 petroleum Substances 0.000 claims description 13
- 230000002093 peripheral effect Effects 0.000 claims description 6
- 230000000694 effects Effects 0.000 abstract description 7
- 239000000446 fuel Substances 0.000 abstract description 5
- 239000000314 lubricant Substances 0.000 abstract description 3
- 238000010304 firing Methods 0.000 abstract 1
- 230000001737 promoting effect Effects 0.000 abstract 1
- 239000003921 oil Substances 0.000 description 136
- 239000000306 component Substances 0.000 description 47
- 238000010586 diagram Methods 0.000 description 9
- 238000005461 lubrication Methods 0.000 description 9
- 239000000295 fuel oil Substances 0.000 description 8
- 239000010687 lubricating oil Substances 0.000 description 6
- 239000003595 mist Substances 0.000 description 6
- 238000001816 cooling Methods 0.000 description 5
- 239000007788 liquid Substances 0.000 description 5
- 230000001050 lubricating effect Effects 0.000 description 5
- 241000883990 Flabellum Species 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 230000015572 biosynthetic process Effects 0.000 description 3
- 239000002826 coolant Substances 0.000 description 3
- 238000013016 damping Methods 0.000 description 2
- 108091092878 Microsatellite Proteins 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000001154 acute effect Effects 0.000 description 1
- 150000001336 alkenes Chemical class 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000010724 circulating oil Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 239000010705 motor oil Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
Abstract
The invention discloses a kind of oil channel structures of turbojet engine, shaft passes through bearing block, the circumferential surface of bearing block is equipped with the input oil duct being passed through in the inner hole of bearing seat, one end of shaft is equipped with the first seal assembly that sealing is formed to bearing block one end, the output oil duct being passed into the inner hole of bearing seat at least provided with one on the circumferential surface of bearing block；Further include：It is arranged in the shaft other end and is formed to the bearing block other end the second seal assembly of sealing, it is formed between bearing block, shaft, the first seal assembly, the second seal assembly for receiving the airtight cavity for firing profit oil, the oily fore bearing in bearing block of combustion profit being flowed into airtight cavity and rear bearing are lubricated；And the oil transportation component of the combustion profit oil guiding exported from output oil duct after being lubricated rear bearing and fore bearing or the combustion chamber for being transported to turbojet engine.The present invention has the advantages of reducing fuel consumption rate, promoting course continuation mileage, improve bearing arrangement lubricant effect, improve engine life.
Description
Technical field
The present invention relates to technical field of engines, more particularly to a kind of turbojet engine and its oil channel structures.
Background technology
Micro turbine engine has the characteristics that size is small, light-weight, energy density is high, thrust-mass ratio is big, can be used as small
The thrust power of type unmanned vehicle can also be used as core component and be applied to distributed generation system and aircraft auxiliary power plant
In, there is extensive dual-use foreground, therefore have received great attention.
Lubrication for microminiature aero-turbine bearing and cooling, traditional way are with cycle with pressure
Lubricating oil, which is ejected on the bearing of rotation, plays the role of lubrication, but this pressure oil lubricating system is complicated, lubrication
The weight of system accounts for the 10%-15% of engine total weight.In miniature, the small aero using circulating oil system
On, the weight of lubricating system accounts for engine total weight ratio bigger, such as Northwestern Polytechnical University's aviation power and heating power during the State's Eighth Five-Year Plan period
China First Micro Turbine Jet Engine Experiment of Principle model machine W2P-1 of engineering department development, uses cycle lubrication strategies, wherein
Attachment, retarder weight account for the 40% of engine total weight, this is the main reason for causing the engine thrust-weight ratio relatively low.
Shared volume and quality are big within the engine for lubricating oil system, cannot look after the particularity of micro-satellite cluster.
Therefore, the structure for simplifying lubricating system and then the weight for mitigating engine are that one of the such engine thrust-weight ratio of raising is effective
Approach.So in recent years, mainly being realized using biphase gas and liquid flow, both by specific device, by a small amount of lubricating fluid and pressure
Contracting air mixes, and sprays bubble-liquid two-phase jet from nozzle to lubrication area, only contains in biphase gas and liquid flow and be torn on a small quantity
The lubricating oil of molecule is largely swiftly flowing air.Its key is compressed air by mist of oil or elaioleucite
Afterwards dispel transmission process, but this lubricant effect and bad, the high temperature failure rate of bearing is still very high.Another problem is,
This lubricating oil for being mixed with air can not recycle and burn utilization, cause certain consumption, and in engine start,
Due into unsaturated vapor, the fuel oil in burner inner liner natively burns insufficient, and jet pipe can jet out flames, and this lubrication fuel oil adds
The acute flame of tail portion.
For example, the application for a patent for invention that number of patent application is 201410410174.5 disclose it is a kind of entitled：Miniature aviation
Engine bearing fuel oil heat exchange cooling device, the patent (are added one by engine extroversion oil inlet pipe fuel feeding, combustion profit oil in fuel oil
The lubricating oil of certainty ratio had not only been used as fuel oil but also had been used as lubricating oil) coolant jacket is entered by oil inlet pipe, then entered by oil return pipe
Combustion is moistened oil penetrating burner inner liner by fuel oil jet pipe and burnt by fuel oil jet pipe.It can be incited somebody to action during combustion profit oil stream is through coolant jacket
The heat that bearing generates afterwards is taken away, to realize the cooling to rear bearing.Defect is as follows existing for the patent：
1st, combustion profit oil is that by fore bearing, bearing direction flows backward, to fire in the indoor flow direction of bearing
Moistening oily lubrication order is：Rear bearing is lubricated again after being first lubricated to fore bearing, however, the indoor temperature of bearing is non-
Chang Gao, after being lubricated to fore bearing, the greasy property of combustion profit oil is clearly to be reduced the high temperature under the action of, when flowing to
Afterwards when bearing, combustion profit oil almost loses the lubricating action to rear bearing, and dry state is nearly at so as to cause rear bearing,
Causing rear bearing to work in the hot environment for spending (degree Celsius) 200 more, in this state, the abrasion of rear bearing is very big,
Cause the service life of rear bearing short.
2nd, fuel oil is when flowing through coolant jacket, although foring cooling to rear bearing, the profit of fore bearing and rear bearing
Sliding be still is passed through combustion profit oil into bearing chamber, however, to the oil after fore bearing and rear bearing lubrication by bearing chamber after, still
It is not recycled and is directly drained by the rear end of bearing chamber, in this way, for Micro-Aviation Engine, the combustion of loss is moistened
Oil determines that the mileage of its continuation of the journey is unable to get promotion.
Invention content
The purpose of the present invention is to provide a kind of energy saving and promote the turbojet engine and its oil channel structures of course continuation mileage.
The technical solution for solving above-mentioned technical problem is as follows：
The oil channel structures of turbojet engine, including shaft, the bearing block for installing fore bearing and rear bearing, shaft pass through
Bearing block, the circumferential surface of bearing block are equipped with the input oil duct being passed through in the inner hole of bearing seat, and one end of shaft is equipped with to bearing block
One end forms the first seal assembly of sealing, is passed at least provided with one on the circumferential surface of bearing block defeated in the inner hole of bearing seat
Oil road；Further include：
Be arranged the shaft other end and to the bearing block other end formed sealing the second seal assembly, bearing block, shaft,
The airtight cavity for receiving combustion profit oil is formed between first seal assembly, the second seal assembly, is flowed into airtight cavity
The oily fore bearing in bearing block of combustion profit and rear bearing are lubricated；And
It is dynamic that the combustion profit oil exported from output oil duct after rear bearing and fore bearing are lubricated guides or be transported to whirlpool eruption
The oil transportation component of the combustion chamber of machine.
A kind of turbojet engine, including oil channel structures.
Use said program, oil channel structures of the invention first will combustion profit oil to support shaft fore bearing and rear bearing into
After row lubrication, then combustion is moistened oil guiding or is transported in the combustion chamber of turbojet engine by output oil duct and oil transportation component and is made
It burns for fuel, therefore, in the oil channel structures, after combustion profit oil is lubricated bearing, it is dynamic that whirlpool eruption will not be discharged to
The outside of machine, but further used as fuel, it is (relatively existing that it can be effectively reduced engine fuel consumption rate in this way
The weight that turbojet engine carries combustion profit oil can be reduced for oil channel structures in technology, under identical course continuation mileage), raising is had an high regard for
Than making course continuation mileage be promoted, and this preferential oil channel structures are also very simple.In addition, combustion profit oil be constantly flowed into it is close
Closed chamber body is lubricated fore bearing and rear bearing, and the upper heat of fore bearing and rear bearing is taken away, compared with the existing technology in
A small amount of combustion can only be inputted to moisten for bearing is lubricated, the oil channel structures in the present invention determine that all combustions for making carrying are moistened
Oil to fore bearing and rear bearing can adequately lubricate and cool down, especially with respect to previous design, the profit of rear bearing
Sliding effect is greatly improved and enhances, and then improves the service life of entire turbojet engine.
Description of the drawings
Fig. 1 is the structural diagram of the present invention；
Fig. 2 is the structural schematic diagram of the turbojet engine in the present invention；
Fig. 3 is the structural schematic diagram of the first case in the present invention；
Fig. 4 gets rid of the structural schematic diagram of oily component for the first in the present invention；
Fig. 5 is the structural schematic diagram of second of case in the present invention；
Fig. 6 is the schematic diagram after being assembled case in Fig. 5 and bearing block；
Fig. 7 is second of structural schematic diagram for getting rid of oily component in the present invention；
Fig. 8 is that the third in the present invention gets rid of the structural schematic diagram of oily component；
Fig. 9 is the 4th kind of structural schematic diagram for getting rid of oily component in the present invention；
A is fore bearing, and B is rear bearing, and C is flabellum, and D is combustion chamber；
10 be bearing block, and 11 be input oil duct, and 12 be output oil duct, and 13 be airtight cavity, and 14 be the first O-ring；
20 be shaft, and 21 be nut；
30 be diffuser, and 31 be axle sleeve, and 32 be first annular sealing element, and 33 be the first sealing ring, and 34 be annular projection；
40 be turbine, and 41 be the second lip ring, and 42 be ring set；
50 be case, and 50a is oil outlet, and 51 be petroleum pipeline, and 52 be annular oil cavity, and 53 be the first pilot hole, and 54 be opening,
55 be the second pilot hole；
60 is get rid of oily component, and 61 is get rid of oily channel, and 62 be entrance, and 63 be outlet, and 64 be to carry oil groove.
Specific implementation mode
As shown in Figure 1 to Figure 3, the oil channel structures of turbojet engine of the invention, including bearing block 10, shaft 20, first
Seal assembly, the second seal assembly, oil transportation component and get rid of oily component 60, below the relationship to each section and between them into
Row detailed description：
As shown in Figure 1, shaft 20 passes through bearing block 10, fore bearing A and rear bearing B are installed in 10 endoporus of bearing block, turned
One end of axis 20 passes through fore bearing A, and the other end of shaft 20 passes through rear bearing B, to which shaft 20 passes through fore bearing A and rear bearing
B is supported, and compressor flabellum C is installed in one end of shaft 20, and turbine 40 is installed in the other end of shaft 20.
As shown in Figure 1, the circumferential surface of bearing block 10 is equipped with the input oil duct 11 being passed through in the inner hole of bearing seat, pass through input
Oil duct 11, can will combustion profit oil be input in the endoporus of bearing block 10, for mounted on 10 both ends of bearing block fore bearing A and
Bearing B is lubricated afterwards.
As shown in Figure 1, the output oil duct being passed into the inner hole of bearing seat at least provided with one on the circumferential surface of bearing block 10
12, it is preferable that output oil duct 12 is multiple, it is highly preferred that output oil duct 12 is 8, the position of the input oil duct 11 is preferential
Position corresponding to rear bearing B is set, and the position of output oil duct 12 is corresponding preferentially to the position of fore bearing A, due to combustion profit oil
One main function is lubricated to fore bearing A and rear bearing B, therefore, is input to combustion profit oil when by inputting oil duct 11
After in the endoporus of bearing block 10, first rear bearing B is lubricated, then fore bearing A is lubricated again, finally by output oil
Road 12 exports, and can promote the utilization rate of combustion profit oil in this way, lubricant effect is made to be promoted.
As shown in Figure 1, one end of shaft 20 is equipped with the first seal assembly for forming sealing to 10 one end of bearing block, first is close
Sealing assembly forms sealing to one end of the bearing block 10 and shaft 20, to prevent to fire profit oil from one end of the bearing block 10
Outflow.
As depicted in figs. 1 and 2, in one or more embodiments, structure that the first seal assembly preferentially uses for：Packet
Diffuser 30 and the first sealing mechanism are included, there is diffuser 30 through-hole, the first sealing mechanism to be set in shaft 20, and first is close
At least part of sealing mechanism, which is located in the through-hole of diffuser 30 to form the through-hole, to be sealed.One end of shaft 20 is close across first
It is connect with compressor flabellum C after sealing mechanism.
As depicted in figs. 1 and 2, the first sealing mechanism includes axle sleeve 31, first annular sealing element 32, and axle sleeve 31, which is fixed on, to be turned
It is rotated with shaft 20 on axis 20, axle sleeve 31 is located in the through-hole being arranged on diffuser 30；Axle sleeve 31 preferentially using interference mode with
Shaft 20 is integrally fixed.The first annular sealing element 32 is fixed on the circumferential surface of axle sleeve 31, first annular sealing element 32
The wall surface of the hole of peripheral surface and through-hole on diffuser 30 is supported, to form sealing function to the through-hole on axle sleeve 31 and diffuser 30,
First annular sealing element 32 is preferentially made of metal material, and first annular sealing element 32 has elasticity, in the circumferential surface of axle sleeve 30
It is equipped with annular groove, first annular sealing element 32 is embedded in the annular groove, and the peripheral surface of first annular sealing element 32 and expansion
The wall surface of the hole of through-hole is supported on depressor 30, to which when axle sleeve 31 is rotated with shaft 30, first annular sealing element 32 is with axle sleeve 31
Rotation.
As depicted in figs. 1 and 2, first seal assembly further includes：In axis of the diffuser 30 towards 10 one end of bearing block
The first annular slot being arranged on end face, and the first sealing ring 33 is mounted in the first annular slot, the one of bearing block 10
After the axial end face of end and diffuser 30 is supported, and diffuser 30 and bearing block 10 are attached and are fastened by use connector,
Sealing is formd between the axial end face and the axial end face of diffuser 30 of 10 one end of bearing block.
As depicted in figs. 1 and 2, the second seal assembly is arranged the other end in shaft 20 and is formed to 10 other end of bearing block
Sealing is formed between bearing block 10, shaft 20, the first seal assembly, the second seal assembly for receiving the closed of combustion profit oil
Cavity 13, the oily fore bearing A in bearing block 10 and rear bearing B of combustion profit being flowed into airtight cavity 13 moisten
It is sliding；Second seal assembly forms sealing to the other end and shaft 20 of the bearing block 10, to prevent to fire profit oil from the axis
The other end of bearing 10 flows out.
As depicted in figs. 1 and 2, the structure that the second seal assembly preferentially uses for：Including turbine 40, the second lip ring
41 and ring set 42, turbine 40 be fixed in shaft 20, one end of turbine 40 is supported with rear bearing B, and the other end of turbine 40 is logical
21 axial limiting of nut in shaft 20 is crossed, the second annular groove, second annular groove are equipped on the circumferential surface of turbine 40
Close to one end that turbine 40 and rear bearing B is supported, second lip ring 41 is embedded in second annular groove.The whirlpool
One end of 40 the second annular groove of setting of wheel passes through ring set 42, ring set 42 to be fixedly connected with bearing block 10.
As depicted in figs. 1 and 2, ring set 42 is fixed on the axial end face of 10 other end of bearing block, it is preferable that 42 face of ring set
Annular convex platform is equipped with to one end of bearing block 10, which is embedded in the endoporus of bearing block 10, annular convex platform and bearing
The endoporus interference fit of seat 10, to enhance leakproofness of the ring set 42 to endoporus.The peripheral surface and ring of second lip ring 41
The inner peripheral surface of set 42 is supported, and is sealed to be formed to 10 other end of bearing block.
As depicted in figs. 1 and 2, in one or more embodiments, corresponding to fore bearing A's in the endoporus of bearing block 10
Wall surface of the hole is equipped with third annular groove, and the first O-ring 14 (as shown in Figure 1), the first O-ring 14 are equipped in the third annular groove
Preferential using the first O-ring 14 with elastic property, the first O-ring 14 is pressed between fore bearing A and bearing block 10, is led to
Vibration damping can be played the role of to fore bearing A by crossing the first O-ring 14, and help can be played to the life-span upgrading of engine.
After forming airtight cavity 13 in the present invention, combustion profit oil is constantly flowed into airtight cavity to fore bearing and rear axle
Hold and be lubricated, the upper heat of fore bearing and rear bearing is taken away, compared with the existing technology in can only input a small amount of combustion profit pair
For bearing is lubricated, the oil channel structures in the present invention, which determine, makes all combustions profit oil of carrying can be to fore bearing A with after
Bearing B adequately lubricate and cool down, after cooling, at rear bearing B at a temperature of drop to 100 degree or so, therefore, one
In a or multiple embodiments, corresponding to fourth annular slot is arranged on the wall surface of the hole of rear bearing B in the endoporus of bearing block 10, this
Second O-ring (not shown) is installed, the second O-ring is preferentially O-shaped using second with elastic property in four annular grooves
Circle, the second O-ring are pressed between rear bearing B and bearing block 10, and vibration damping can be played to rear bearing B by the second O-ring
Effect, help can be played to the life-span upgrading of engine.
As shown in Figure 1 to Figure 3, oil transportation component is by the combustion profit oil guiding exported from output oil duct 12 or to be transported to whirlpool eruption dynamic
The combustion chamber D of machine, combustion profit oil moisten oil for the combustion after being lubricated rear bearing and fore bearing, and oil transportation component includes：Case 50 with
And there is accommodating chamber, one end of case 50 to be equipped with the first pilot hole 53 for petroleum pipeline 51, case 50, the other end of case 50, which is equipped with, to be opened
Mouth 54, one end of bearing block 10 is after first pilot hole 53 extend into the inside of case 50, the output oil on bearing block 10
Road 12 is corresponding with the accommodating chamber of case 50, and case 50 is equipped with oil outlet 50a.The other end of case 50 and the first seal assembly connect
It connects or is integrally formed, preferably, the diffuser 30 in the other end of case 50 and the first seal assembly is integrally formed,
Such mode is convenient for that case 50 and diffuser 30 is made to cover the end of bearing block 10.Case 50 and the first seal assembly with
And a closed annular oil cavity 52 is surrounded between bearing block 10, to make the combustion profit oil flowed out from output oil duct 12 enter
In the annular oil cavity 52.
As shown in Figure 1 to Figure 3, one end of petroleum pipeline 51 is connect with the oil outlet 50a on case 50, one or more real
It applies in mode, it is preferable that the oil outlet on case 50 is multiple, and petroleum pipeline 51 is also multiple, each oil outlet on case 50
It is connect with one end of a petroleum pipeline 51, the other end of petroleum pipeline 51 is connect with combustion chamber D, to lubricate the combustion after bearing
The guiding of profit oil is transported in the D of combustion chamber, and burning interior in alkene burns to generate the gas of high temperature and pressure.Pass through the ring of formation
Shape oil pocket 52 receives the combustion come from output oil duct 12 and moistens oil, and when oil outlet 50a is multiple, combustion profit is oily from annular oil cavity 52
Disperse and is flowed into 50a in oil outlet.
As shown in Figure 1, Figure 2 and Figure 4, it gets rid of oily component 60 to be fixed in shaft 20 and rotate with the shaft 20, it is preferable that get rid of
Oily component 60 between axle sleeve 31 and fore bearing A, support, and gets rid of the another of oily component 60 by one end and axle sleeve 31 for getting rid of oily component 60
End top low with one end of fore bearing A.In one or more embodiments, the shape for getting rid of oily component 60 preferentially uses annular, gets rid of
Oily component 60 is sleeved in shaft 20 and is fixed in the circumferential with shaft 20.
As shown in Figure 1 and Figure 4, get rid of makes combustion profit oil add at least provided with one on oily component 60 when this gets rid of the rotation of oily component 60
Speed moves in the output oil duct 12 and gets rid of oily channel 61.Preferably, the circumferential surface for getting rid of oily component 60 is corresponding with output oil duct 12,
When 20 high speed rotation of shaft, oily component 60 is got rid of with 20 high speed rotation of shaft, is entered the combustion profit oil got rid of in oily channel 61 and is existed
It is accelerated when getting rid of oily 60 high speed rotation of component, therefore so that the flow velocity and pressure of combustion profit oil increase, and combustion moistens oil and accelerating to flow
In the case of, combustion profit oil becomes mist form from liquid and enters in output oil duct 12, and the combustion profit oil of mist form passes through oil transportation
Component is directed to combustion chamber D, since combustion profit oil forms misty shape in advance, by getting rid of the effect of oily component 60, have
Power-assisted promotes the efficiency of combustion of combustion profit oil, to make the course continuation mileage of turbojet engine be promoted.Also, the combustion of mist form
The temperature of profit oil is reduced, and after reaching in the D of combustion chamber, is conducive to combustion by evaporation.
As shown in Figure 1 and Figure 4, in one or more embodiments, it is described get rid of oily channel 61 along get rid of oily component 60 revolve
The direction arrangement of produced centrifugal force is as a kind of preferred embodiment of the invention when turning, and having due to getting rid of oily component 60 can produce when rotation
It is raw to exert oneself from masterpiece, therefore, gets rid of oily channel 61 and arranged along the direction for getting rid of produced centrifugal force when oily component 60 rotates, combustion can be made
The flow velocity of profit oil reaches maximum value, to be conducive to make to form misty form completely in the combustion profit oil for getting rid of the flowing of oily channel 61.
As shown in Figure 1 and Figure 4, in one or more embodiments, it is described get rid of oily channel 61 be located at get rid of oily component 60
A kind of preferred embodiment on axial end face as the present invention, it is further preferable that on two axial end faces for get rid of oily component 60
Oily channel is got rid of described in being provided with, to disperse to the maximum extent to combustion profit oil, effectively makes combustion profit oil formation mist form, gets rid of
The quantity for getting rid of oily channel 61 on 60 each axial end face of oily component is all higher than or equal to the quantity for exporting oil duct 12.
As shown in Figure 1 and Figure 4, each getting rid of oily channel 61 has cross-sectional area, and it includes entrance 62 and outlet to get rid of oily channel 61
63, it is preferable that get rid of the cross-sectional area in oily channel and get rid of the entrance 62 in oily channel 61 from this and increase to outlet 63, in this way, helping to make
The boost in pressure of combustion profit oil is ensured.The entrance 62 is got rid of described in being arranged near the inner circumferential or the inner circumferential of oily component 60,
The outlet 63 is arranged on the periphery for getting rid of oily component 60.
As shown in Figure 1 and Figure 4, it is described get rid of oily component 60 be equipped with carry oil groove 64, it is described it is at least one get rid of oily channel 61 with
It carries the connection of oil groove 64 combustion profit oil is made to be flowed into described this by load oil groove 64 and get rid of in oily channel 61, the shape for carrying oil groove 64 preferentially uses
Annular.After being provided with load oil groove 64 on getting rid of oily component 60, combustion profit oil, which can be intensively flowed into first, to be carried in oil groove 64, then oily from carrying
Be distributed in slot 64 it is each get rid of in oily channel 61, can make in this way combustion profit oil be uniformly distributed to each get rid of in oily channel 61.When
It gets rid of after being provided with load oil groove 64 on oily component 60, the entrance 62 can only be configured near the inner circumferential for getting rid of oily component 60.
As depicted in figs. 1 and 2, oily component 60 is got rid of between axle sleeve 31 and fore bearing A as the preferred of present embodiment
Therefore mode is got rid of oily component 60 also simultaneously close to the flabellum C of compressor, since the pressure of the gas outlet at diffuser 30 is low, is led to
Cross get rid of oily component to combustion profit oil accelerate after, make combustion profit oil pressure rise, and fire profit oil in the process thrown away at a high speed
In, combustion profit oil becomes mist form from liquid, and therefore, in the case of pressure difference, there is the combustions made in bearing block 10 to moisten oily quilt
The possibility of suction, therefore the annular projection 34 being looped around around through-hole aperture is equipped on diffuser 30, which matches
It closes in the endoporus of bearing block 10 and is blocked to getting rid of the formation of oily channel 61, by the effect of blocking of annular projection 34, can avoid combustion
Profit oil is sucked out.
Other embodiment：
More than, it is the preferred embodiment of the present invention to be illustrated, but the invention is not limited in above-mentioned embodiment party
Formula can be subject to various changes without departing from the spirit and scope of the invention.
(a) in the above-described embodiment, first annular sealing element 32 can also be made of rubber material.
(b) in the above-described embodiment, the axle sleeve 31 in the first seal assembly and first annular sealing element 32 can be direct
It is replaced using first annular sealing element 32, opens up annular groove in shaft 20, which is directly anchored to
In the annular groove opened up in shaft 20, the periphery of first annular sealing element 32 and the wall surface of the hole of the through-hole on diffuser 30 are supported.
(c) in the above-described embodiment, the structure that the second seal assembly may be used is：Second seal assembly includes second
Lip ring 32, the second lip ring 32 are sleeved in shaft, which is pressed in turbine 40 with after
Between bearing B, the periphery of the second lip ring 32 and the inner wall of bearing block are supported.
Alternatively, the second seal assembly includes the second lip ring 32, the second annular fitting groove is set in shaft 20, the
Second ring sealing element 32 is mounted in the second annular fitting groove, and the periphery of the second lip ring 32 and the inner wall of bearing block support
Top.
(d) in the above-described embodiment, oil transportation component can also use such structure, as shown in Figure 5 and Figure 6, oil transportation
Component includes case 50 and petroleum pipeline 51, and case 50 has an accommodating chamber, and case 50 is equipped with oil outlet 50a, and the one of case 50
End is equipped with the first pilot hole 53, and the other end of case 50 is equipped with the second pilot hole 55, and one end of bearing block 10 is filled from described first
After distribution 53 extend into the inside of case 50, the output oil duct 12 on bearing block 10 is corresponding with the accommodating chamber of case 50, in case
A closed annular oil cavity 52 is formed between 50 and bearing block 10；Oil outlet 50a on one end and case of petroleum pipeline 51 connects
It connects.
(e) in the above-described embodiment, the structure of oil transportation component can also be：Including petroleum pipeline 51, the petroleum pipeline 51
One end is connect with output oil duct 12, and the other end of petroleum pipeline is connect with combustion chamber D, the oil transportation component of this structure type, defeated
Oil road 12 may be multiple, and each oil duct 12 that exports is all connected with a petroleum pipeline 51.
(f) in the above-described embodiment, carry oil groove 64 without configuration on oily component 60 if getting rid of, as shown in fig. 7, it is described enter
Mouth 62 is configured in the inner circumferential for getting rid of oily component 60.
(g) in the above-described embodiment, the structure type for getting rid of oily channel 61 can also be：It is arranged in and gets rid of oily component 60 axially
Oily channel 61 of getting rid of on end face is in fan-shaped (as shown in Figure 8).
(h) in the above-described embodiment, the structure type for getting rid of oily channel 61 can also be：Oily channel 61 is got rid of to get rid of to favour
The radial mode of oily component 60 is arranged, get rid of oily channel 61 arbitrary two from entrance to export direction from cross-sectional area be phase
Deng (as shown in Figure 9).
As shown in Fig. 2, the turbojet engine of the present invention, which includes described in any one of the above embodiment
Oil channel structures, other than turbojet engine shown in Fig. 2, this hair can be used in the oil channel structures on suchlike engine
Oil channel structures in bright replace, such as can be with application No. is the oil channel structures on 201410410174.5 Micro-Aviation Engine
It is replaced using the oil channel structures in the present invention.
Claims (10)
1. the oil channel structures of turbojet engine, including shaft, the bearing block for installing fore bearing and rear bearing, shaft passes through axis
Bearing, the circumferential surface of bearing block are equipped with the input oil duct being passed through in the inner hole of bearing seat, which is characterized in that one end of shaft is equipped with
The first seal assembly of sealing is formed to bearing block one end, is passed into the bearing block at least provided with one on the circumferential surface of bearing block
Output oil duct in hole；Further include：
It is arranged in the shaft other end and is formed to the bearing block other end the second seal assembly of sealing, in bearing block, shaft, first
The airtight cavity for receiving combustion profit oil is formed between seal assembly, the second seal assembly, the combustion profit being flowed into airtight cavity
Oil in bearing block fore bearing and rear bearing be lubricated；And
The combustion profit oil exported from output oil duct after rear bearing and fore bearing are lubricated guides or is transported to turbojet engine
The oil transportation component of combustion chamber.
2. the oil channel structures of turbojet engine according to claim 1, which is characterized in that further include be fixed in shaft and
Oily component is got rid of with shaft rotation, get rid of makes combustion profit oil accelerate fortune at least provided with one on oily component when this gets rid of oily component rotation
It moves in the output oil duct and gets rid of oily channel.
3. the oil channel structures of turbojet engine according to claim 2, which is characterized in that described to get rid of oily channel along getting rid of oil
The direction arrangement of component produced centrifugal force when rotating.
4. the oil channel structures of turbojet engine according to claim 3, which is characterized in that it is described get rid of oily channel be located at get rid of oil
On the axial end face of component, getting rid of oily channel has cross-sectional area, gets rid of oily channel and includes an inlet and an outlet, gets rid of the cross section in oily channel
The entrance that product gets rid of oily channel from this increases to outlet.
5. the oil channel structures of turbojet engine according to claim 2, which is characterized in that described to get rid of oily component equipped with load
Oil groove, it is described it is at least one get rid of oily channel with carry oil groove be connected to make combustion profit oil by load oil groove be flowed into described in this get rid of in oily channel.
6. the oil channel structures of the turbojet engine according to claim 1 to 5 any one, which is characterized in that the first sealing
Component includes the diffuser for having through-hole；
At least part of the first sealing mechanism being set in shaft, the first sealing mechanism is located in the through-hole of diffuser to this
Through-hole forms sealing.
7. the oil channel structures of turbojet engine according to claim 6, which is characterized in that diffuser is logical equipped with being looped around
Annular projection around the aperture of hole, the annular projection coordinate in bearing block.
8. the oil channel structures of the turbojet engine according to claim 1 to 5 any one, which is characterized in that the second sealing
Component includes：
Turbine, the turbine are fixed in shaft, and the circumferential surface of turbine is equipped with the second annular groove；
A part for second lip ring, second lip ring is located in the second annular groove on turbine；
Ring set, one end that the second annular groove is arranged in turbine pass through ring set, ring set to be fixedly connected with the bearing seat, the second lip ring
Peripheral surface and the inner peripheral surface of ring set support.
9. the oil channel structures of the turbojet engine according to claim 1 to 5 any one, which is characterized in that oil transportation component
Including：
One end of case with accommodating chamber, case is equipped with the first pilot hole, and the other end of case, which is equipped with, to be open, and the one of bearing block
After first pilot hole extend into the inside of case, the output oil duct on bearing block is corresponding with the accommodating chamber of case at end, cover
Shell is equipped with oil outlet；
The other end of case connect or is integrally formed with the first seal assembly, in case and the first seal assembly and bearing block
Between surround a closed annular oil cavity；
The petroleum pipeline that one end is connect with the oil outlet on case.
10. a kind of turbojet engine, which is characterized in that include the oil channel structures as described in claim 1 to 9 any one.
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| CN201810346361.XA CN108518284B (en) | 2018-04-18 | 2018-04-18 | Turbojet engine and oil path structure thereof |
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| CN109736951A (en) * | 2019-01-16 | 2019-05-10 | 中国科学院工程热物理研究所 | The bearing lubrication and sealing system of microminiature gas turbine rotor system |
| CN112065586A (en) * | 2020-09-08 | 2020-12-11 | 西安增材制造国家研究院有限公司 | Engine circulating lubrication oil way structure and engine rotating device |
| CN113107677A (en) * | 2021-05-20 | 2021-07-13 | 青岛海星热控实业发展有限公司 | Novel combustion device |
| CN113309617A (en) * | 2021-07-09 | 2021-08-27 | 常州环能涡轮动力股份有限公司 | Miniature turbojet engine |
| CN113958411A (en) * | 2021-10-19 | 2022-01-21 | 中国科学院工程热物理研究所 | Cantilever type elastic supporting structure of aircraft engine |
| CN114060152A (en) * | 2021-12-24 | 2022-02-18 | 常州环能涡轮动力股份有限公司 | Fuel oil atomization structure of micro turbojet engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109736951A (en) * | 2019-01-16 | 2019-05-10 | 中国科学院工程热物理研究所 | The bearing lubrication and sealing system of microminiature gas turbine rotor system |
| CN109736951B (en) * | 2019-01-16 | 2020-08-25 | 中国科学院工程热物理研究所 | Bearing lubricating and sealing system of rotor system of micro gas turbine |
| CN112065586A (en) * | 2020-09-08 | 2020-12-11 | 西安增材制造国家研究院有限公司 | Engine circulating lubrication oil way structure and engine rotating device |
| CN112065586B (en) * | 2020-09-08 | 2021-11-23 | 西安增材制造国家研究院有限公司 | Engine circulating lubrication oil way structure and engine rotating device |
| CN113107677A (en) * | 2021-05-20 | 2021-07-13 | 青岛海星热控实业发展有限公司 | Novel combustion device |
| CN113309617A (en) * | 2021-07-09 | 2021-08-27 | 常州环能涡轮动力股份有限公司 | Miniature turbojet engine |
| CN113958411A (en) * | 2021-10-19 | 2022-01-21 | 中国科学院工程热物理研究所 | Cantilever type elastic supporting structure of aircraft engine |
| CN113958411B (en) * | 2021-10-19 | 2023-03-10 | 中国科学院工程热物理研究所 | Cantilever type elastic supporting structure of aircraft engine |
| CN114060152A (en) * | 2021-12-24 | 2022-02-18 | 常州环能涡轮动力股份有限公司 | Fuel oil atomization structure of micro turbojet engine |
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