CN108343512B - A kind of engine rotor bracket - Google Patents
A kind of engine rotor bracket Download PDFInfo
- Publication number
- CN108343512B CN108343512B CN201810067174.8A CN201810067174A CN108343512B CN 108343512 B CN108343512 B CN 108343512B CN 201810067174 A CN201810067174 A CN 201810067174A CN 108343512 B CN108343512 B CN 108343512B
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- Prior art keywords
- supporter
- several
- engine rotor
- air inlet
- floor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 238000004519 manufacturing process Methods 0.000 claims abstract description 19
- 238000002485 combustion reaction Methods 0.000 claims description 15
- 210000000078 claw Anatomy 0.000 claims description 11
- 239000000463 material Substances 0.000 claims description 11
- 230000002093 peripheral effect Effects 0.000 claims 1
- 241000239290 Araneae Species 0.000 abstract description 13
- 238000005516 engineering process Methods 0.000 abstract description 6
- 238000009413 insulation Methods 0.000 abstract description 4
- 238000012546 transfer Methods 0.000 abstract description 4
- 238000012545 processing Methods 0.000 description 8
- 208000020442 loss of weight Diseases 0.000 description 7
- 238000000034 method Methods 0.000 description 6
- 238000010276 construction Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 4
- 239000007787 solid Substances 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000010146 3D printing Methods 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 239000012620 biological material Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000016 photochemical curing Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000005245 sintering Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000009827 uniform distribution Methods 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
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to aero-engine manufacturing technology fields, disclose a kind of engine rotor bracket.The bracket includes rack body, and one end of rack body is provided with several air inlet and several gas vents, and the other end is correspondingly arranged on several ventholes, and wherein several air inlets, several gas vents and several ventholes are uniformly distributed circumferentially.Meanwhile engine rotor internal stent is provided with air flue, air flue is respectively communicated in air inlet, gas vent and venthole.Rotor field spider can be cooled down, rotor field spider is avoided the case where thermal deformation occur, and then guarantee the stable operation of rotor and the service life of the bearing in Extending Rotor bracket.Simultaneously as rotor field spider is internally provided with air flue, and cold air can flow into air flue from air inlet, so that rotor field spider inside configuration forms air thermal resistance, reduce the heat transfer between rotor field spider inner and outer wall, and then realize the heat insulation to rotor and bearing.
Description
Technical field
The present invention relates to aero-engine manufacturing technology field more particularly to a kind of engine rotor brackets.
Background technique
Engine rotor bracket is that the support member in aero-engine, especially rotor field spider stablize high speed to rotor
Operation plays a crucial role.
Engine rotor carriage center is provided with mounting hole, and the rotor for being arranged with bearing is arranged in mounting hole, rotor field spider
It can play the role of protection and connection to rotor.Wherein engine rotor bracket is close to Inner Wall of Combustion Chamber, and combustion chamber is high
Warm component can be such that the temperature of engine rotor bracket increases, so that engine rotor bracket by the burning of fuel in combustion chamber
Thermal deformation is generated, and then influences the stable operation of rotor and shortens the service life of the bearing in engine rotor bracket.Together
When, traditional engine rotor bracket is solid construction, is unfavorable for the needs of energy saving loss of weight.In addition, traditional aero-engine
Connection between rotor field spider and other component is more complicated, the big, time and effort consuming using traditional processing mode difficulty of processing, and needs
It wants multiple processes to be assembled, and then causes processing cost high, the production cycle is long.
Summary of the invention
The purpose of the present invention is to provide a kind of engine rotor bracket, avoid engine rotor internal stent rotor and
The case where bearing thermal deformation, it is beneficial to energy conservation loss of weight.
To achieve this purpose, the present invention adopts the following technical scheme:
One end of a kind of engine rotor bracket, including rack body, the rack body is provided with several air inlet
Hole and several gas vents, the other end are correspondingly arranged on several ventholes, several described air inlets, several described exhausts
Hole and several ventholes are uniformly distributed circumferentially；The engine rotor internal stent is provided with air flue, the air flue point
It is not connected to the air inlet, the gas vent and the venthole.
Preferably, further including disk, the disk is set to one end on the rack body, and close to the air inlet
Hole.
Preferably, the rack body include be connected to the disk supporter and several be uniformly distributed circumferentially
Connecting plate, one end of the connecting plate is connected to the disk, and the other end is connected to the supporter；The air inlet setting
In on the connecting plate, the gas vent is set to one end of the supporter, and the venthole is set to the supporter
The other end, the air flue are set to inside the supporter.
Preferably, the connecting plate includes the first floor and the second floor for being connected to the supporter, described first
One end of floor is connected to the disk, and the other end is connected to second floor；The air inlet is set to second rib
On plate.
Preferably, first floor and second floor are arc structure.
Preferably, the supporter is hollow structure, the outer wall of the inner wall of the supporter and the supporter is formed
The air flue.
Preferably, the supporter inner wall is provided with step close to one end of the air inlet, the venthole is along week
To being uniformly arranged on the step.
Preferably, the supporter is internally provided with several spaced annular plates, the annular plate connects
It is connected to the supporter, and the annular plate is correspondingly arranged on several through-holes.
Preferably, several diffuser guide vanes are provided on the disk, if the side of the disk is provided with
Dry combustion chamber support claw, several described combustion chamber support claws and several described diffuser guide vanes are circumferentially uniform
Distribution.
Preferably, the combustion chamber support claw, the diffuser guide vane and the supporter pass through increasing material manufacturing
Form integrated formed structure.
Beneficial effects of the present invention:
1) several air inlet and several gas vents, the other end pair are provided with by one end of engine rotor bracket
Several ventholes should be provided with, and engine rotor internal stent is provided with air flue, air flue is respectively communicated in air inlet, exhaust
Hole and venthole, cold air can flow into air flue from air inlet, and be discharged respectively from venthole and gas vent, to engine rotor
Bracket is cooled down, and engine rotor bracket is avoided the case where thermal deformation occur, and then is guaranteed the stable operation of rotor and prolonged
The service life of bearing in long engine rotor field spider.
2) since engine rotor internal stent is provided with air flue, and cold air can flow into air flue from air inlet, so that
Air thermal resistance is formed inside engine rotor supporting structure, reduces the heat transfer between engine rotor rack inner wall and outer wall, into
And realize the heat insulation to rotor and bearing.
3) air flue is provided with by engine rotor internal stent, can reduce the weight of engine rotor bracket, compares
More traditional engine rotor bracket meets engine rotor bracket lightweight for solid construction conducive to the needs of energy saving loss of weight
Requirement.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of inventive engine rotor field spider；
Fig. 2 is the side view of inventive engine rotor field spider；
Fig. 3 is cross-sectional view of the Fig. 2 in A-A；
Fig. 4 is cross-sectional view of the Fig. 3 in B-B.
In figure:
1, rack body；2, disk；3, air inlet；4, gas vent；5, venthole；6, air flue；
11, supporter；12, connecting plate；
111, step；112, annular plate；113, through-hole；
121, the first floor；122, the second floor；
21, combustion chamber support claw；22, diffuser guide vane.
Specific embodiment
To further illustrate the technical scheme of the present invention below with reference to the accompanying drawings and specific embodiments.
A kind of engine rotor bracket is present embodiments provided, as shown in Figure 1-3, the engine rotor bracket includes bracket
Ontology 1, and one end of rack body 1 is provided with several air inlet 3 and several gas vents 4, the other end is correspondingly arranged on
Several ventholes 5, wherein several air inlets 3, several gas vents 4 and several ventholes 5 are uniformly distributed circumferentially.
Meanwhile engine rotor internal stent is provided with air flue 6, air flue 6 is respectively communicated in air inlet 3, gas vent 4 and venthole 5.
Several air inlet 3 and several gas vents 4, the other end pair are provided with by one end of engine rotor bracket
Several ventholes 5 should be provided with, and engine rotor internal stent is provided with air flue 6, air flue 6 be respectively communicated in air inlet 3,
Gas vent 4 and venthole 5, cold air can flow into air flue 6 from air inlet 3, and be discharged respectively from venthole 5 and gas vent 4, right
Engine rotor bracket is cooled down, and avoids engine rotor bracket from the case where thermal deformation occur, and then guarantee the stabilization of rotor
Operation and the service life for extending the bearing in engine rotor bracket.Simultaneously as engine rotor internal stent is arranged
There is air flue 6, and cold air can flow into air flue 6 from air inlet 3, so that forming air heat inside engine rotor supporting structure
Resistance reduces the heat transfer between engine rotor rack inner wall and outer wall, and then realizes the heat insulation to rotor and bearing.Separately
Outside, air flue 6 is provided with by engine rotor internal stent, can reduce the weight of engine rotor bracket, compared to more traditional
Engine rotor bracket be solid construction, conducive to the needs of energy saving loss of weight, to reach the light-weighted mesh of engine rotor bracket
's.
As shown in Figure 1-3, above-mentioned engine rotor bracket includes disk 2, the rack body 1 for being set to 2 side of disk,
Supporter 11 and six connecting plates 12 that are uniformly distributed circumferentially of the middle rack body 1 including being connected to disk 2, and connecting plate 12
One end be connected to disk 2, the other end is connected to supporter 11.Meanwhile connecting plate 12 includes the first floor 121 and is connected to branch
Second floor 122 of support body 11, and one end of the first floor 121 is connected to disk 2, the other end is connected to the second floor 122.The
One floor 121 and the second floor 122 are arc structure.One end by the way that the first floor 121 is arranged is connected to disk 2, another
End is connected to the second floor 122, and the second floor 122 is connected to supporter 11, enhances the company between supporter 11 and disk 2
Connect the rigidity of intensity and disk 2.Meanwhile under the requirement for meeting same intensity, the thickness of disk 2 can be reduced accordingly,
Achieve the effect that the weight for mitigating disk 2, and then meets the light-weighted requirement of engine rotor bracket.
Above-mentioned supporter 11 is hollow structure, and the outer wall of the inner wall of supporter 11 and supporter 11 forms air flue 6.Pass through
Engine rotor internal stent is provided with air flue 6, can reduce the weight of engine rotor bracket, compared to more traditional engine
Rotor field spider is solid construction, conducive to the needs of energy saving loss of weight, to reach the light-weighted purpose of engine rotor bracket.It is wherein every
An air inlet 3 is correspondingly arranged on a second floor 122, and 11 inner wall of supporter is provided with platform close to one end of air inlet 3
Rank 111 has been uniformly arranged in the circumferential direction 12 gas vents 4 on step 111.Meanwhile the other end of supporter 11 is correspondingly arranged on
Six ventholes 5.
When the engine operates, cold air is flowed into from the air inlet 3 on the second floor 122, and a part of gas is from gas vent 4
Outflow, avoids engine rotor bracket from the case where thermal deformation occur, for cooling settings turning in engine rotor internal stent
Son and bearing, and then guarantee the stable operation of rotor and extend the service life of the bearing in engine rotor bracket；Due to
The both ends of air flue 6 are respectively communicated in air inlet 3 and venthole 5, and another gas passes through the inner wall and supporter 11 of supporter 11
Outer wall form air flue 6, enter from the outflow of venthole 5 and turbine guide vane inner cavity or be expelled directly out.Cold air can be flowed from air inlet 3
Air entering flue 6 so that form air thermal resistance inside engine rotor supporting structure, reduce engine rotor rack inner wall and outer wall it
Between heat transfer, and then realize to the heat insulation of rotor and bearing.
Above-mentioned supporter 11 is cylindrical structure, and supporter 11 is internally provided with three spaced annular plates
112, annular plate 112 is connected to supporter 11, and wherein the internal diameter of annular plate 112 is identical as the outer diameter of 11 inner wall of supporter,
The outer diameter of annular plate 112 is identical as the internal diameter of the outer wall of supporter 11.By being arranged at intervals with circumferential rib inside supporter 11
Plate 112, annular plate 112 play booster action, enhance the support strength and rigidity of supporter 11, and then enhance and start
The intensity of machine rotor bracket.Meanwhile annular plate 112 is correspondingly arranged there are six through-hole 113, so that into the gas in air flue 6
Through-hole 113 can be flowed through, is discharged glibly from venthole 5.
Several diffuser guide vanes 22 are provided on above-mentioned disk 2, diffuser guide vane 22 plays collection and draws
The effect of gas out facilitates access in air inlet 3 so that cold air passes through the collection of diffuser guide vane 22.Meanwhile disk
There are three combustion chamber support claw 21, three combustion chamber support claws 21 and several diffuser guide vanes 22 are equal for 2 side setting
It is uniformly distributed circumferentially.In addition, combustion chamber support claw 21, diffuser guide vane 22 and supporter 11 are formed by increasing material manufacturing
Integrated formed structure.
Increasing material manufacturing is commonly called as 3D printing, is to have merged CAD, material processing and forming technique.With digital mould
Based on type file, by software and digital control system by dedicated metal material, nonmetallic materials and biomaterial for medical purpose, press
It is successively accumulated according to modes such as extruding, sintering, melting, photocuring, injections, produces the manufacturing technology of physical item.
Increases material manufacturing technology makes it possible the production of labyrinth components.Traditional aero-engine engine rotor
Support connection structure is complicated, big using traditional processing mode time and effort consuming, difficulty of processing, and multiple processes is needed to be assembled,
And then causing processing cost high, the production cycle is long.Using increases material manufacturing technology in aero-engine engine rotor bracket
Supporter 11, diffuser guide vane 22 and combustion chamber support claw 21 carry out integrated design and manufacture, and three components are merged
For an entirety, it is possible to reduce support and connection structure between each component avoid the need for the case where multiple processes are assembled,
And then it is easy to process, and meet loss of weight and reduce the needs of processing, maintenance cost.Therefore, the present embodiment supports combustion chamber
Pawl 21, diffuser guide vane 22 and supporter 11 form integrally formed structure by increases material manufacturing technology, not only manufacture work
Skill is simple, the period is short, light-weight, and saves material, at low cost, and then improve the cooling efficiency of engine rotor bracket,
Extend the service life of engine rotor bracket.
The present embodiment also discloses a kind of production method of engine rotor bracket, comprising the following steps:
Step 1: according to engine structure, the parameter request of engine rotor bracket is calculated, so that it is determined that engine
The outer dimension of rotor field spider, and complete the body profile design of supporter 11 in engine rotor bracket；
Step 2: according to the intensity of supporter 11 and loss of weight requirement, checking and adjust the inner wall of engine rotor bracket and outer
Wall thickness, the quantity of annular plate 112 and thickness；
Step 3: according to the rigidity requirement of bonding strength and disk 2 between supporter 11 and disk 2, completing the first floor
121 and second floor 122 design；
Step 4: according to the requirement of 11 inner air flow size and distribution of supporter, select air inlet 3, gas vent 4 and
Direction, size, quantity and the arrangement of venthole 5；
Step 5: numerical simulation being carried out to designing a model for above-mentioned steps completion, gas is cold in the determining supporter 11 of analysis
But and heat-insulating capability, and adjustment is optimized to modelling parameter according to analog result；
Step 6: the model that above-mentioned steps are completed being carried out with diffuser guide vane 22, combustion chamber support claw 21 integrated
The production of engine rotor bracket is then completed in increasing material manufacturing.
The present embodiment determines the parameter of following engine rotor bracket by taking 10kg engine as an example:
Firstly, the quantity of annular plate 112 is three, the width of each annular plate 112 is 3mm, two neighboring annular
The distance between floor 112 is 18mm；
Secondly, the quantity of the first floor 121 and the second floor 122 is six, wherein the circumferential span of the second floor 122
It is 22 °, the arc radius of the second floor 122 is 20mm, and the length of the second floor 122 is 20mm；Meanwhile first floor 121
Arc radius is 1.5mm, disk 2 with a thickness of 1mm.
Again, it is correspondingly arranged on an air inlet 3 on each second floor 122, wherein the number of air inlet 3 and venthole 5
Amount is six, and the diameter of air inlet 3 and venthole 5 is 3mm, and pair in the direction of air inlet 3 and engine rotor bracket
Angle between axis is referred to as 45 °；The quantity of gas vent 4 is 12 simultaneously, and the diameter of gas vent 4 is 1.2mm.
It should be strongly noted that the present embodiment by taking 10kg engine as an example, designs the items of engine rotor bracket
Parameter, can be according to needs of production, for different engines, and the parameters of engine rotor bracket can carry out phase
The adjustment answered.
Obviously, the above embodiment of the present invention is just for the sake of clearly illustrating examples made by the present invention, and being not is pair
The restriction of embodiments of the present invention.For those of ordinary skill in the art, may be used also on the basis of the above description
To make other variations or changes in different ways.There is no necessity and possibility to exhaust all the enbodiments.It is all this
Made any modifications, equivalent replacements, and improvements etc., should be included in the claims in the present invention within the spirit and principle of invention
Protection scope within.
Claims (7)
1. a kind of engine rotor bracket, including rack body (1), which is characterized in that one end of the rack body (1) is arranged
There are several air inlet (3) and several gas vents (4), the other end is correspondingly arranged on several ventholes (5), several institutes
Air inlet (3), several described gas vents (4) and several ventholes (5) are stated to be uniformly distributed circumferentially；
The engine rotor internal stent is provided with air flue (6), and the air flue (6) is respectively communicated in the air inlet (3), institute
State gas vent (4) and the venthole (5)；
It further include disk (2), the disk (2) is set to one end of the rack body (1), and close to the air inlet；
The rack body (1) include be connected to the disk (2) supporter (11) and several be uniformly distributed circumferentially
One end of connecting plate (12), the connecting plate (12) is connected to the disk (2), and the other end is connected to the supporter (11)；
The air inlet (3) is set on the connecting plate (12), and the gas vent (4) is set to the one of the supporter (11)
End, the venthole (5) are set to the other end of the supporter (11), and the air flue (6) is set to the supporter (11)
It is internal；
The connecting plate (12) includes the first floor (121) and is connected to the second floor (122) of the supporter (11), described
One end of first floor (121) is connected to the disk (2), and the other end is connected to second floor (122)；The air inlet
(3) it is set on second floor (122).
2. engine rotor bracket according to claim 1, which is characterized in that first floor (121) and described
Two floors (122) are arc structure.
3. engine rotor bracket according to claim 1, which is characterized in that the supporter (11) is hollow structure,
The inner wall of the supporter (11) and the outer wall of the supporter (11) form the air flue (6).
4. engine rotor bracket according to claim 3, which is characterized in that supporter (11) inner wall is close to described
One end of air inlet (3) is provided with step (111), and the venthole (5) is uniformly arranged in the circumferential direction on the step (111).
5. engine rotor bracket according to claim 3, which is characterized in that the supporter (11) is if be internally provided with
Dry spaced annular plate (112), the annular plate (112) is connected to the supporter (11), and the annular
Floor (112) is correspondingly arranged on several through-holes (113).
6. engine rotor bracket according to claim 5, which is characterized in that the outer peripheral surface of the disk (2) is uniformly set
Several diffuser guide vanes (22) are equipped with, have circumferentially been uniformly arranged several between the disk (2) and the supporter
Combustion chamber support claw (21).
7. engine rotor bracket according to claim 6, which is characterized in that the combustion chamber support claw (21), described
Diffuser guide vane (22) and the supporter (11) form integrated formed structure by increasing material manufacturing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810067174.8A CN108343512B (en) | 2018-01-24 | 2018-01-24 | A kind of engine rotor bracket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810067174.8A CN108343512B (en) | 2018-01-24 | 2018-01-24 | A kind of engine rotor bracket |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108343512A CN108343512A (en) | 2018-07-31 |
| CN108343512B true CN108343512B (en) | 2019-11-12 |
Family
ID=62960581
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810067174.8A Expired - Fee Related CN108343512B (en) | 2018-01-24 | 2018-01-24 | A kind of engine rotor bracket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108343512B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1740523A (en) * | 2004-06-11 | 2006-03-01 | 斯内克马发动机公司 | Turbo machine with axial retention means for the rotor |
| CN106801726A (en) * | 2015-09-25 | 2017-06-06 | 通用电气公司 | Epicyclic gearbox with the cylindrical roller bearing with high density roller assembly |
| CN107246324A (en) * | 2017-03-02 | 2017-10-13 | 蔡肃民 | A kind of Micro Turbine Jet Engine vertically borrows gas high pressure cooling and lubricating bearing arrangement |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130243575A1 (en) * | 2012-03-13 | 2013-09-19 | United Technologies Corporation | Cooling pedestal array |
-
2018
- 2018-01-24 CN CN201810067174.8A patent/CN108343512B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1740523A (en) * | 2004-06-11 | 2006-03-01 | 斯内克马发动机公司 | Turbo machine with axial retention means for the rotor |
| CN106801726A (en) * | 2015-09-25 | 2017-06-06 | 通用电气公司 | Epicyclic gearbox with the cylindrical roller bearing with high density roller assembly |
| CN107246324A (en) * | 2017-03-02 | 2017-10-13 | 蔡肃民 | A kind of Micro Turbine Jet Engine vertically borrows gas high pressure cooling and lubricating bearing arrangement |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108343512A (en) | 2018-07-31 |
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Granted publication date: 20191112 |
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