CN108547672A - A kind of micro turbine engine bearing cooler - Google Patents
A kind of micro turbine engine bearing cooler Download PDFInfo
- Publication number
- CN108547672A CN108547672A CN201810705772.3A CN201810705772A CN108547672A CN 108547672 A CN108547672 A CN 108547672A CN 201810705772 A CN201810705772 A CN 201810705772A CN 108547672 A CN108547672 A CN 108547672A
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- Prior art keywords
- bearing
- axis
- turbine disk
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- disk
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- 238000007789 sealing Methods 0.000 claims description 16
- 238000005119 centrifugation Methods 0.000 claims description 3
- 241001416181 Axis axis Species 0.000 claims 1
- 238000001816 cooling Methods 0.000 description 11
- 238000005516 engineering process Methods 0.000 description 5
- 239000004519 grease Substances 0.000 description 5
- 230000001050 lubricating effect Effects 0.000 description 5
- 230000009471 action Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 241000153246 Anteros Species 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000007634 remodeling Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
- F01D25/125—Cooling of bearings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Mounting Of Bearings Or Others (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of micro turbine engine bearing coolers, including axis, centrifugal compressor impeller, front axle bearing assembly, centrifugal impeller, bearing assembly afterwards, the turbine disk and fiaring cone, the axis is equipped with axis air inlet and axis gas outlet, the turbine disk includes the primary rotor turbine disk, the two level stator turbine disk and the secondary rotor turbine disk, the compressor impeller and front axle bearing assembly are inserted in successively on the axis being fixed between axis air inlet and axis gas outlet, the centrifugal impeller is inserted in and is fixed at the axis gas outlet of axis, the primary rotor turbine disk, bearing assembly and the secondary rotor turbine disk are inserted in successively on the axis for being fixed on the centrifugal impeller other side afterwards, the secondary rotor turbine disk connects fiaring cone, wherein fiaring cone is open in shaft end position.
Description
Technical field
The invention belongs to aero-engine technology field more particularly to a kind of micro turbine engine bearing coolers.
Background technology
In aero-engine field, bearing portions is typically to be cooled down using oil system, tiny engine also not example
Outside.The oil system of engine is mainly by oil tank, booster pump, scavenge oil pump, oil cooler, gs-oil separator, instruction system
Deng composition, for tiny engine, the weight of oil system directly results in the reduction of its power to weight ratio, thus research and develop it is a kind of can be effective
The cooling bearing and device that can improve tiny engine power to weight ratio has market prospects very much.
Invention content
It is an object of the invention to overcome above-mentioned the deficiencies in the prior art, a kind of micro turbine engine bearing cooling is provided
Device overcomes prior art middle (center) bearing and needs to carry out cooling using oil system and cause that power to weight ratio is low, oil system component
The problems such as more, consuming energy.
In order to solve technical problem, the technical scheme is that：A kind of micro turbine engine bearing cooler, packet
Axis, centrifugal compressor impeller, front axle bearing assembly, centrifugal impeller, rear bearing assembly, the turbine disk and fiaring cone are included, is set on the axis
It includes the primary rotor turbine disk, the two level stator turbine disk and secondary rotor whirlpool to have axis air inlet and axis gas outlet, the turbine disk
Wheel disc, the centrifugal compressor impeller and front axle bearing assembly are inserted in the axis being fixed between axis air inlet and axis gas outlet successively
On, the centrifugal impeller is inserted in and is fixed at the axis gas outlet of axis, the primary rotor turbine disk, the two level stator turbine disk,
Bearing assembly and the secondary rotor turbine disk are inserted in successively on the axis for being fixed on the centrifugal impeller other side afterwards, the secondary rotor turbine
Disk connects fiaring cone, and wherein fiaring cone is open in shaft end position.
Preferably, the front axle bearing assembly includes fore bearing, fore bearing front shaft sleeve and fore bearing rear axle housing, wherein fore bearing
Fore bearing sleeve sealing circle is equipped between front shaft sleeve and fore bearing rear axle housing, the fore bearing is set to fore bearing front shaft sleeve with before
In bearing bore between bearing rear axle housing.
Preferably, the rear bearing assembly includes rear bearing, rear axle brought forward axle sleeve and rear bearing rear axle housing, wherein rear bearing
Rear bearing sleeve sealing circle is equipped between front shaft sleeve and rear bearing rear axle housing, the rear bearing is set to rear axle brought forward axle sleeve with after
In bearing bore between bearing rear axle housing.
Preferably, the primary rotor turbine disk, the two level stator turbine disk and the secondary rotor turbine disk are equipped with gas port,
Wherein gas port is uniformly distributed on the circumference of the primary rotor turbine disk, the two level stator turbine disk and the secondary rotor turbine disk.
Preferably, the centrifugal compressor impeller carries out axial restraint by the side of paraxial air inlet using front nut,
Side of the middle centrifugal compressor impeller far from axis air inlet carries out radial positioning using set tooth and axis.
Preferably, the front axle bearing assembly, centrifugal impeller, the primary rotor turbine disk, rear bearing assembly and secondary rotor whirlpool
Wheel disc is radially all made of interference fit, the centrifugal impeller, the primary rotor turbine disk, rear bearing assembly and secondary rotor whirlpool with axis
Wheel disc is axial mutually closely, and wherein secondary rotor turbine back-end disk is fixed by back nut.
Preferably, the centrifugal impeller circumference is equipped with blade.
Preferably, the axis is equipped with the shaft shoulder, and wherein front axle bearing assembly and centrifugal impeller is determined in axial direction by the shaft shoulder
Position.
Compared with the existing technology, the advantage of the invention is that：
（1）The dynamic injection for driving centrifugal impeller generation centrifugal force and jet pipe air-flow of shaft rotation is made when the present invention is operated using engine
With, by from the axis air inlet of axis introduce low-temp low-pressure air-flow, pass through front axle bearing assembly, the turbine disk and rear bearing assembly after again from
Fiaring cone is drawn, and realizes the cooling to tiny engine bearing；
（2）Present invention eliminates oil systems, effectively reduce the weight of tiny engine, realize the light of tiny engine
Type improves its power to weight ratio；
（3）The configuration of the present invention is simple, the lines flow smoothly, and bearing cooling efficiency is high, and resource has been saved using air cooling.
Description of the drawings
The structural schematic diagram of Fig. 1, the present invention.
Reference sign：
1, axis, 1-1, axis air inlet, 1-2, axis gas outlet, 2, front axle bearing assembly, 2-1, fore bearing, 2-2 fore bearing front shaft sleeves, 2-
3, fore bearing rear axle housing, 2-4, fore bearing sleeve sealing circle, 3, centrifugal impeller, 3-1, blade, 4, the primary rotor turbine disk, 5, two
Grade the stator turbine disk, 6, after hold shaft assembly, 6-1, rear axle brought forward axle sleeve, 6-2, rear bearing rear axle housing, 6-3, rear bearing axle sleeve are close
Seal, 7, the secondary rotor turbine disk, 8, fiaring cone, 9, centrifugal compressor impeller, 10, gas port, 11, front nut, 12, rear spiral shell
Mother, 13, the shaft shoulder.
Specific implementation mode
The specific embodiment of the invention is described with reference to the accompanying drawings and embodiments：
It should be noted that structure, ratio, the size etc. illustrated in this specification institute attached drawing, only coordinating specification institute
The content of announcement is not limited to the enforceable qualifications of the present invention so that those skilled in the art understands and reads,
The modification of any structure, the change of proportionate relationship or the adjustment of size are not influencing the effect of present invention can be generated and institute's energy
Under the purpose reached, should all still it fall in the range of disclosed technology contents can be covered.
Meanwhile cited such as "upper" in this specification, "lower", "left", "right", " centre " and " one " term, also
Only being illustrated for ease of narration, rather than to limit the scope of the invention, relativeness is altered or modified, in nothing
Under essence change technology contents, when being also considered as the enforceable scope of the present invention.
Embodiment 1
As shown in Figure 1, the invention discloses a kind of micro turbine engine bearing cooler, including axis 1, centrifugal compressor leaf
Wheel 9, front axle bearing assembly 2, centrifugal impeller 3, rear bearing assembly 6, the turbine disk and fiaring cone 8, the axis 1 are equipped with axis air inlet 1-
1 and axis gas outlet 1-2, the turbine disk include the primary rotor turbine disk 4, the two level stator turbine disk 5 and the secondary rotor turbine disk
7, the centrifugal compressor impeller 9 and front axle bearing assembly 2 are inserted in are fixed between axis air inlet 1-1 and axis gas outlet 1-2 successively
Axis 1 on, the centrifugal impeller 3 is inserted in and is fixed at the axis gas outlet 1-2 of axis 1, the primary rotor turbine disk 4, two level
The stator turbine disk 5, rear bearing assembly 6 and the secondary rotor turbine disk 7 are inserted in successively on the axis 1 for being fixed on 3 other side of centrifugal impeller,
The secondary rotor turbine disk 7 connects fiaring cone 8, and wherein fiaring cone 8 is open in 1 end position of axis.
Embodiment 2
As shown in Figure 1, the invention discloses a kind of micro turbine engine bearing cooler, including axis 1, centrifugal compressor leaf
Wheel 9, front axle bearing assembly 2, centrifugal impeller 3, rear bearing assembly 6, the turbine disk and fiaring cone 8, the axis 1 are equipped with axis air inlet 1-
1 and axis gas outlet 1-2, the turbine disk include the primary rotor turbine disk 4, the two level stator turbine disk 5 and the secondary rotor turbine disk
7, the centrifugal compressor impeller 9 and front axle bearing assembly 2 are inserted in are fixed between axis air inlet 1-1 and axis gas outlet 1-2 successively
Axis 1 on, the centrifugal impeller 3 is inserted in and is fixed at the axis gas outlet 1-2 of axis 1, the primary rotor turbine disk 4, two level
The stator turbine disk 5, rear bearing assembly 6 and the secondary rotor turbine disk 7 are inserted in successively on the axis 1 for being fixed on 3 other side of centrifugal impeller,
The secondary rotor turbine disk 7 connects fiaring cone 8, and wherein fiaring cone 8 is open in 1 end position of axis.
As shown in Figure 1, it is preferred that the front axle bearing assembly 2 is including after fore bearing, fore bearing front shaft sleeve 2-1 and fore bearing
Axle sleeve 2-2, it is described equipped with fore bearing sleeve sealing circle 2-3 between wherein fore bearing front shaft sleeve 2-1 and fore bearing rear axle housing 2-2
Fore bearing is set in the bearing bore between fore bearing front shaft sleeve 2-1 and fore bearing rear axle housing 2-2.
As shown in Figure 1, it is preferred that bearing assembly 6 is including after rear bearing, rear axle brought forward axle sleeve 6-1 and rear bearing after described
Rear bearing sleeve sealing circle 6-3 is equipped between axle sleeve 6-2, wherein rear axle brought forward axle sleeve 6-1 and rear bearing rear axle housing 6-2, it is described
Bearing is set in the bearing bore between rear axle brought forward axle sleeve 6-1 and rear bearing rear axle housing 6-2 afterwards.
A semi-enclosed bearing bore is formed between the fore bearing front shaft sleeve 2-1, fore bearing rear axle housing 2-2 and axis 1, it is preceding
Bearing is in bearing bore, while filling lubricating grease is used for the cooling of bearing in cavity, when tiny engine is run, bearing production
Raw heat transfer is again shed heat by antero posterior axis bearing sleeve to lubricating grease, lubricating grease；Have between antero posterior axis bearing sleeve and axis
Minim gap, when tiny engine is run, lubricating grease radially throws away and is mainly gathered in outside bearing due to the effect of centrifugal force
At circle, between fore bearing front shaft sleeve 2-1 and fore bearing rear axle housing 2-2 be arranged fore bearing sleeve sealing circle 2-3 prevent lubricating grease from
It is leaked out between front and back axle sleeve gap.
Also shape between the rear axle brought forward axle sleeve 6-1, rear bearing rear axle housing 6-2 and the firsts and seconds turbine rotor turbine disk
At a semi-enclosed bearing bore, cooling principle is identical as front axle bearing assembly.
Embodiment 3
As shown in Figure 1, the invention discloses a kind of micro turbine engine bearing cooler, including axis 1, centrifugal compressor leaf
Wheel 9, front axle bearing assembly 2, centrifugal impeller 3, rear bearing assembly 6, the turbine disk and fiaring cone 8, the axis 1 are equipped with axis air inlet 1-
1 and axis gas outlet 1-2, the turbine disk include the primary rotor turbine disk 4, the two level stator turbine disk 5 and the secondary rotor turbine disk
7, the centrifugal compressor impeller 9 and front axle bearing assembly 2 are inserted in are fixed between axis air inlet 1-1 and axis gas outlet 1-2 successively
Axis 1 on, the centrifugal impeller 3 is inserted in and is fixed at the axis gas outlet 1-2 of axis 1, the primary rotor turbine disk 4, two level
The stator turbine disk 5, rear bearing assembly 6 and the secondary rotor turbine disk 7 are inserted in successively on the axis 1 for being fixed on 3 other side of centrifugal impeller,
The secondary rotor turbine disk 7 connects fiaring cone 8, and wherein fiaring cone 8 is open in 1 end position of axis.
As shown in Figure 1, it is preferred that the front axle bearing assembly 2 is including after fore bearing, fore bearing front shaft sleeve 2-1 and fore bearing
Axle sleeve 2-2, it is described equipped with fore bearing sleeve sealing circle 2-3 between wherein fore bearing front shaft sleeve 2-1 and fore bearing rear axle housing 2-2
Fore bearing is set in the bearing bore between fore bearing front shaft sleeve 2-1 and fore bearing rear axle housing 2-2.
As shown in Figure 1, it is preferred that bearing assembly 6 is including after rear bearing, rear axle brought forward axle sleeve 6-1 and rear bearing after described
Rear bearing sleeve sealing circle 6-3 is equipped between axle sleeve 6-2, wherein rear axle brought forward axle sleeve 6-1 and rear bearing rear axle housing 6-2, it is described
Bearing is set in the bearing bore between rear axle brought forward axle sleeve 6-1 and rear bearing rear axle housing 6-2 afterwards.
As shown in Figure 1, it is preferred that the primary rotor turbine disk 4, the two level stator turbine disk 5 and the secondary rotor turbine disk 7
It is equipped with gas port 10, wherein gas port 10 is in the primary rotor turbine disk 4, the two level stator turbine disk 5 and the secondary rotor turbine disk 7
Circumference on be uniformly distributed.
Embodiment 4
As shown in Figure 1, the invention discloses a kind of micro turbine engine bearing cooler, including axis 1, centrifugal compressor leaf
Wheel 9, front axle bearing assembly 2, centrifugal impeller 3, rear bearing assembly 6, the turbine disk and fiaring cone 8, the axis 1 are equipped with axis air inlet 1-
1 and axis gas outlet 1-2, the turbine disk include the primary rotor turbine disk 4, the two level stator turbine disk 5 and the secondary rotor turbine disk
7, the centrifugal compressor impeller 9 and front axle bearing assembly 2 are inserted in are fixed between axis air inlet 1-1 and axis gas outlet 1-2 successively
Axis 1 on, the centrifugal impeller 3 is inserted in and is fixed at the axis gas outlet 1-2 of axis 1, the primary rotor turbine disk 4, two level
The stator turbine disk 5, rear bearing assembly 6 and the secondary rotor turbine disk 7 are inserted in successively on the axis 1 for being fixed on 3 other side of centrifugal impeller,
The secondary rotor turbine disk 7 connects fiaring cone 8, and wherein fiaring cone 8 is open in 1 end position of axis.
As shown in Figure 1, it is preferred that the front axle bearing assembly 2 is including after fore bearing, fore bearing front shaft sleeve 2-1 and fore bearing
Axle sleeve 2-2, it is described equipped with fore bearing sleeve sealing circle 2-3 between wherein fore bearing front shaft sleeve 2-1 and fore bearing rear axle housing 2-2
Fore bearing is set in the bearing bore between fore bearing front shaft sleeve 2-1 and fore bearing rear axle housing 2-2.
As shown in Figure 1, it is preferred that bearing assembly 6 is including after rear bearing, rear axle brought forward axle sleeve 6-1 and rear bearing after described
Rear bearing sleeve sealing circle 6-3 is equipped between axle sleeve 6-2, wherein rear axle brought forward axle sleeve 6-1 and rear bearing rear axle housing 6-2, it is described
Bearing is set in the bearing bore between rear axle brought forward axle sleeve 6-1 and rear bearing rear axle housing 6-2 afterwards.
As shown in Figure 1, it is preferred that the primary rotor turbine disk 4, the two level stator turbine disk 5 and the secondary rotor turbine disk 7
It is equipped with gas port 10, wherein gas port 10 is in the primary rotor turbine disk 4, the two level stator turbine disk 5 and the secondary rotor turbine disk 7
Circumference on be uniformly distributed.
As shown in Figure 1, it is preferred that the centrifugal compressor impeller 9 utilizes front nut 11 by the side of paraxial air inlet 1-1
Axial restraint is carried out, wherein side of the centrifugal compressor impeller 9 far from axis air inlet 1-1 is carried out using set tooth with axis radial fixed
Position.
9 side of the centrifugal compressor impeller carries out axial restraint using front nut 11, and front axle bearing assembly 2 is withstood in the other side
Inner ring, side of the centrifugal compressor impeller 9 far from axis air inlet 1-1（Back segment）Equipped with set tooth, stage casing is hollow.
Embodiment 5
As shown in Figure 1, the invention discloses a kind of micro turbine engine bearing cooler, including axis 1, centrifugal compressor leaf
Wheel 9, front axle bearing assembly 2, centrifugal impeller 3, rear bearing assembly 6, the turbine disk and fiaring cone 8, the axis 1 are equipped with axis air inlet 1-
1 and axis gas outlet 1-2, the turbine disk include the primary rotor turbine disk 4, the two level stator turbine disk 5 and the secondary rotor turbine disk
7, the centrifugal compressor impeller 9 and front axle bearing assembly 2 are inserted in are fixed between axis air inlet 1-1 and axis gas outlet 1-2 successively
Axis 1 on, the centrifugal impeller 3 is inserted in and is fixed at the axis gas outlet 1-2 of axis 1, the primary rotor turbine disk 4, two level
The stator turbine disk 5, rear bearing assembly 6 and the secondary rotor turbine disk 7 are inserted in successively on the axis 1 for being fixed on 3 other side of centrifugal impeller,
The secondary rotor turbine disk 7 connects fiaring cone 8, and wherein fiaring cone 8 is open in 1 end position of axis.
As shown in Figure 1, it is preferred that the front axle bearing assembly 2 is including after fore bearing, fore bearing front shaft sleeve 2-1 and fore bearing
Axle sleeve 2-2, it is described equipped with fore bearing sleeve sealing circle 2-3 between wherein fore bearing front shaft sleeve 2-1 and fore bearing rear axle housing 2-2
Fore bearing is set in the bearing bore between fore bearing front shaft sleeve 2-1 and fore bearing rear axle housing 2-2.
As shown in Figure 1, it is preferred that bearing assembly 6 is including after rear bearing, rear axle brought forward axle sleeve 6-1 and rear bearing after described
Rear bearing sleeve sealing circle 6-3 is equipped between axle sleeve 6-2, wherein rear axle brought forward axle sleeve 6-1 and rear bearing rear axle housing 6-2, it is described
Bearing is set in the bearing bore between rear axle brought forward axle sleeve 6-1 and rear bearing rear axle housing 6-2 afterwards.
As shown in Figure 1, it is preferred that the primary rotor turbine disk 4, the two level stator turbine disk 5 and the secondary rotor turbine disk 7
It is equipped with gas port 10, wherein gas port 10 is in the primary rotor turbine disk 4, the two level stator turbine disk 5 and the secondary rotor turbine disk 7
Circumference on be uniformly distributed.
As shown in Figure 1, it is preferred that the centrifugal compressor impeller 9 utilizes front nut 11 by the side of paraxial air inlet 1-1
Axial restraint is carried out, wherein side of the centrifugal compressor impeller 9 far from axis air inlet 1-1 is carried out using set tooth with axis radial fixed
Position.
As shown in Figure 1, it is preferred that the front axle bearing assembly 2, centrifugal impeller 3, the primary rotor turbine disk 4, rear bearing assembly
6 and the secondary rotor turbine disk 7 and axis 1 are radial is all made of interference fit, the centrifugal impeller 3, the primary rotor turbine disk 4, rear axle
Bearing assembly 6 and the secondary rotor turbine disk 7 are axial mutually closely, and wherein 7 rear end of the secondary rotor turbine disk is fixed by back nut 12.
Embodiment 6
As shown in Figure 1, the invention discloses a kind of micro turbine engine bearing cooler, including axis 1, centrifugal compressor leaf
Wheel 9, front axle bearing assembly 2, centrifugal impeller 3, rear bearing assembly 6, the turbine disk and fiaring cone 8, the axis 1 are equipped with axis air inlet 1-
1 and axis gas outlet 1-2, the turbine disk include the primary rotor turbine disk 4, the two level stator turbine disk 5 and the secondary rotor turbine disk
7, the centrifugal compressor impeller 9 and front axle bearing assembly 2 are inserted in are fixed between axis air inlet 1-1 and axis gas outlet 1-2 successively
Axis 1 on, the centrifugal impeller 3 is inserted in and is fixed at the axis gas outlet 1-2 of axis 1, the primary rotor turbine disk 4, two level
The stator turbine disk 5, rear bearing assembly 6 and the secondary rotor turbine disk 7 are inserted in successively on the axis 1 for being fixed on 3 other side of centrifugal impeller,
The secondary rotor turbine disk 7 connects fiaring cone 8, and wherein fiaring cone 8 is open in 1 end position of axis.
As shown in Figure 1, it is preferred that the front axle bearing assembly 2 is including after fore bearing, fore bearing front shaft sleeve 2-1 and fore bearing
Axle sleeve 2-2, it is described equipped with fore bearing sleeve sealing circle 2-3 between wherein fore bearing front shaft sleeve 2-1 and fore bearing rear axle housing 2-2
Fore bearing is set in the bearing bore between fore bearing front shaft sleeve 2-1 and fore bearing rear axle housing 2-2.
As shown in Figure 1, it is preferred that bearing assembly 6 is including after rear bearing, rear axle brought forward axle sleeve 6-1 and rear bearing after described
Rear bearing sleeve sealing circle 6-3 is equipped between axle sleeve 6-2, wherein rear axle brought forward axle sleeve 6-1 and rear bearing rear axle housing 6-2, it is described
Bearing is set in the bearing bore between rear axle brought forward axle sleeve 6-1 and rear bearing rear axle housing 6-2 afterwards.
As shown in Figure 1, it is preferred that the primary rotor turbine disk 4, the two level stator turbine disk 5 and the secondary rotor turbine disk 7
It is equipped with gas port 10, wherein gas port 10 is in the primary rotor turbine disk 4, the two level stator turbine disk 5 and the secondary rotor turbine disk 7
Circumference on be uniformly distributed.
As shown in Figure 1, it is preferred that the centrifugal compressor impeller 9 utilizes front nut 11 by the side of paraxial air inlet 1-1
Axial restraint is carried out, wherein side of the centrifugal compressor impeller 9 far from axis air inlet 1-1 is carried out using set tooth with axis radial fixed
Position.
As shown in Figure 1, it is preferred that the front axle bearing assembly 2, centrifugal impeller 3, the primary rotor turbine disk 4, rear bearing assembly
6 and the secondary rotor turbine disk 7 and axis 1 are radial is all made of interference fit, the centrifugal impeller 3, the primary rotor turbine disk 4, rear axle
Bearing assembly 6 and the secondary rotor turbine disk 7 are axial mutually closely, and wherein 7 rear end of the secondary rotor turbine disk is fixed by back nut 12.
As shown in Figure 1, it is preferred that 3 circumference of the centrifugal impeller is equipped with blade 3-1.
As shown in Figure 1, it is preferred that the axis 1 is equipped with the shaft shoulder 13, and wherein front axle bearing assembly 2 and centrifugal impeller 3 is in axial direction
It is positioned by the shaft shoulder 13.
The centrifugal compressor impeller 9 and front axle bearing assembly 2 are positioned using front nut 11 and the shaft shoulder 13, the centrifugation
Impeller 3, the primary rotor turbine disk 4, after hold shaft assembly 6 and the secondary rotor turbine disk 7 is determined using the shaft shoulder 13 and back nut 12
Position.
Working principle of the present invention is as follows：
When tiny engine is run, the high pressure draught of jet pipe plays ejector action, while 1 turn of axis to the air-flow in fiaring cone 8
It is dynamic that centrifugal impeller 3 is driven to generate centrifugal force by axis gas outlet 1-2 by the fraction extraction of 1 intracavitary of axis, and then form air-flow
Access, low-temp low-pressure air-flow are introduced into from axis air inlet 1-1, under the action of 3 centrifugal force of centrifugal impeller, the part of 1 intracavitary of axis
Air-flow is brought out from axis gas outlet 1-2, and the direction of air-flow becomes axial from radial under the action of 3 blade 3-1 of centrifugal impeller,
Under jet pipe high pressure draught ejector action, the primary rotor turbine disk 4, the two level stator turbine disk 5, secondary rotor turbine are passed sequentially through
Gas port 10 on disk 7 is finally flowed out from the opening of fiaring cone 8, and continuously air-flow flowing is by front axle bearing assembly 2 with after
The high temperature air of bearing assembly 6 is taken away, and cooling effect is played to front and back bearings component.
Present invention eliminates oil systems, effectively reduce the weight of tiny engine, realize tiny engine
Lightness improves its power to weight ratio；The configuration of the present invention is simple, the lines flow smoothly, and bearing cooling efficiency is high, and money has been saved using air cooling
Source.
The preferred embodiment for the present invention is explained in detail above in conjunction with attached drawing, but the present invention is not limited to above-mentioned implementations
Mode within the knowledge of a person skilled in the art can also be without departing from the purpose of the present invention
It makes a variety of changes.
Many other changes and remodeling can be made by not departing from the spirit and scope of the present invention.It should be appreciated that the present invention is not
It is limited to specific embodiment, the scope of the present invention is defined by the following claims.
Claims (8)
1. a kind of micro turbine engine bearing cooler, it is characterised in that：Including axis, centrifugal compressor impeller, fore bearing
Component, centrifugal impeller, rear bearing assembly, the turbine disk and fiaring cone, the axis are equipped with axis air inlet and axis gas outlet, the whirlpool
Wheel disc includes the primary rotor turbine disk, the two level stator turbine disk and the secondary rotor turbine disk, and the centrifugal compressor impeller is with before
Bearing assembly is inserted in successively on the axis being fixed between axis air inlet and axis gas outlet, and the centrifugal impeller is inserted in and is fixed on axis
Axis gas outlet at, the primary rotor turbine disk, the two level stator turbine disk, rear bearing assembly and the secondary rotor turbine disk are successively
It is inserted on the axis for being fixed on the centrifugal impeller other side, the secondary rotor turbine disk connects fiaring cone, and wherein fiaring cone is in shaft end
Portion position is open.
2. a kind of micro turbine engine bearing cooler according to claim 1, it is characterised in that：The fore bearing
Component includes fore bearing, fore bearing front shaft sleeve and fore bearing rear axle housing, wherein between fore bearing front shaft sleeve and fore bearing rear axle housing
Equipped with fore bearing sleeve sealing circle, the fore bearing is set to the bearing bore between fore bearing front shaft sleeve and fore bearing rear axle housing
It is interior.
3. a kind of micro turbine engine bearing cooler according to claim 1, it is characterised in that：Bearing after described
Component includes rear bearing, rear axle brought forward axle sleeve and rear bearing rear axle housing, wherein between rear axle brought forward axle sleeve and rear bearing rear axle housing
Equipped with rear bearing sleeve sealing circle, the rear bearing is set to the bearing bore between rear axle brought forward axle sleeve and rear bearing rear axle housing
It is interior.
4. a kind of micro turbine engine bearing cooler according to claim 1, it is characterised in that：The level-one turns
The sub- turbine disk, the two level stator turbine disk and the secondary rotor turbine disk are equipped with gas port, and wherein gas port is in primary rotor turbine
It is uniformly distributed on the circumference of disk, the two level stator turbine disk and the secondary rotor turbine disk.
5. a kind of micro turbine engine bearing cooler according to claim 1, it is characterised in that：The centrifugation pressure
Compressor wheel carries out axial restraint by the side of paraxial air inlet using front nut, and wherein centrifugal compressor impeller is far from axis air inlet
The side of mouth carries out radial positioning using set tooth and axis.
6. a kind of micro turbine engine bearing cooler according to claim 1, it is characterised in that：The fore bearing
Component, centrifugal impeller, the primary rotor turbine disk, rear bearing assembly and the secondary rotor turbine disk and axis are radially all made of interference and match
It closes, the centrifugal impeller, the primary rotor turbine disk, rear bearing assembly and the secondary rotor turbine disk are axial mutually closely, wherein two
Grade rotor scroll back-end disk is fixed by back nut.
7. a kind of micro turbine engine bearing cooler according to claim 6, it is characterised in that：The centrifugation leaf
It takes turns circumference and is equipped with blade.
8. a kind of micro turbine engine bearing cooler according to claim 6, it is characterised in that：It is set on the axis
There are the shaft shoulder, wherein front axle bearing assembly and centrifugal impeller to be positioned by the shaft shoulder in axial direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810705772.3A CN108547672B (en) | 2018-07-02 | 2018-07-02 | Bearing cooling device of miniature turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810705772.3A CN108547672B (en) | 2018-07-02 | 2018-07-02 | Bearing cooling device of miniature turbine engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108547672A true CN108547672A (en) | 2018-09-18 |
| CN108547672B CN108547672B (en) | 2024-05-24 |
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ID=63494281
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810705772.3A Active CN108547672B (en) | 2018-07-02 | 2018-07-02 | Bearing cooling device of miniature turbine engine |
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| Country | Link |
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| CN (1) | CN108547672B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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