CN107246324B - Vertical air-borrowing high-pressure cooling lubrication bearing structure of miniature turbojet engine - Google Patents
Vertical air-borrowing high-pressure cooling lubrication bearing structure of miniature turbojet engine Download PDFInfo
- Publication number
- CN107246324B CN107246324B CN201710121680.6A CN201710121680A CN107246324B CN 107246324 B CN107246324 B CN 107246324B CN 201710121680 A CN201710121680 A CN 201710121680A CN 107246324 B CN107246324 B CN 107246324B
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- Prior art keywords
- bearing
- turbine
- pressure
- air
- vortex
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- 238000001816 cooling Methods 0.000 title claims abstract description 21
- 238000005461 lubrication Methods 0.000 title claims abstract description 15
- 238000003825 pressing Methods 0.000 claims abstract description 26
- 230000004308 accommodation Effects 0.000 claims description 4
- 230000002093 peripheral effect Effects 0.000 abstract description 10
- 230000000694 effects Effects 0.000 abstract description 8
- 230000001050 lubricating effect Effects 0.000 abstract description 6
- 239000010705 motor oil Substances 0.000 abstract description 4
- 230000002035 prolonged effect Effects 0.000 abstract description 3
- 239000003921 oil Substances 0.000 description 13
- 239000010687 lubricating oil Substances 0.000 description 7
- 238000010586 diagram Methods 0.000 description 2
- 239000003595 mist Substances 0.000 description 2
- 238000007664 blowing Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a vertical high-pressure cooling and lubricating bearing structure of a miniature turbojet engine, which comprises a shaft, a pressure impeller, a turbine, a bearing casing, a pressure end bearing, a vortex end bearing, a pressure end fixed sleeve, a vortex end fixed sleeve and a diffuser. The end pressing and fixing sleeve is provided with an end pressing and fixing sleeve outer peripheral surface and an end pressing and fixing sleeve end surface, the end pressing and fixing sleeve outer peripheral surface is opposite to the inner peripheral surface of the bearing casing, the end pressing and fixing sleeve outer peripheral surface is sealed with the inner peripheral surface of the bearing casing, the end pressing and fixing sleeve end surface is opposite to the end pressing bearing, the end pressing and fixing sleeve end surface is of a cambered surface structure for baffling and guiding, and the diffuser is provided with an air borrowing channel for borrowing air. The invention has the advantages that: (1) The lubrication effect of the pressure end bearing and the vortex end bearing is good, and the addition of engine oil is reduced by 60%. And (2) the cooling effect is good, and the service life of the bearing is prolonged.
Description
Technical Field
The invention relates to a turbojet engine, in particular to a vertical air-borrowing high-pressure cooling lubrication bearing structure of a miniature turbojet engine.
Background
Referring to fig. 1, a conventional vertical air-assisted high-pressure cooling and lubricating bearing structure of a micro-turbojet engine is shown, and comprises a shaft 1, a pressure impeller 2, a turbine 8, a bearing casing 4, a pressure end bearing 5, a vortex end bearing 6, a pressure end fixed sleeve 3, a vortex end fixed sleeve 7 and a diffuser 9. Specifically, the air hole 10 is opened from the back of the diffuser to the back of the pressure impeller, and the high-pressure air flow behind the diffuser is introduced between the back of the pressure impeller and the front of the diffuser, and then is folded to the bearing casing. When the borrowed air flow is between the back of the impeller wheel and the front of the diffuser, high-pressure air can enter the bearing casing to flow to the turbine end, and can also flow to the position of the air passage outlet 11 of the impeller wheel; in the starting stage of the engine, because the rotating speed is low, enough pressure is not formed in the engine, and the lubricating bearing is not cooled by blowing lubricating oil to the turbine end through air; when the engine runs at a high rotating speed, the pressure of the air flow which is borrowed is high, and the pressure of the back of the impeller and the pressure of the pressure bearing casing are low, so that part of the air flow brings lubricating oil to the turbine end through the bearing, the effect of cooling and lubricating the bearing is achieved, but the effect of cooling the bearing is poor due to insufficient air borrowing; and the other part of the air flows to the air passage outlet of the impeller and the air passage inlet of the diffuser by virtue of the air, and is carried into the diffuser again by the new high-speed air flow of the air inlet to flow into the engine body, so that the engine efficiency is reduced.
Disclosure of Invention
The invention aims to overcome the problems in the prior art and provides a novel vertical air-borrowing high-pressure cooling lubrication bearing structure of a miniature turbojet engine.
In order to achieve the purpose, the technical scheme of the invention is as follows: the utility model provides a miniature turbojet engine is perpendicular with air high pressure cooling lubrication bearing structure, includes, axle, pressure impeller, turbine, bearing housing, pressure end bearing, vortex end bearing, pressure end fixed cover, vortex end fixed cover and diffuser, wherein, the axle has along its axial relative pressure impeller end and the turbine end that sets up, the pressure impeller end of axle has the pressure impeller, the turbine end of axle has the turbine, the bearing housing encircle in the outside of axle and place pressure impeller and between the turbine, the bearing housing with there is the distance between the axle for both boundary the bearing accommodation cavity, have in the bearing accommodation cavity be in pressure impeller side the pressure end bearing and be in the turbine bearing of turbine side, epaxial in pressure end bearing with pressure impeller in between the pressure groove have the pressure end fixed cover, epaxial in the turbine end bearing with have the turbine end fixed cover between the turbine, the diffuser encircles in the pressure outlet and is located between pressure housing and the pressure bearing.
As a preferable scheme of the miniature turbojet engine vertical air borrowing high-pressure cooling lubrication bearing structure, the air borrowing sleeve is provided with an air borrowing channel which is provided with a channel air inlet and a channel air outlet, the channel air inlet is positioned in an engine cavity, the channel air outlet is opposite to the air borrowing channel end face, so that air in the engine cavity enters the bearing accommodating cavity from the air borrowing channel through the air borrowing channel end face.
As a preferable scheme of the vertical air-borrowing high-pressure cooling lubrication bearing structure of the miniature turbojet engine, the vortex end fixed sleeve is provided with a vortex end fixed sleeve end face, the vortex end fixed sleeve end face is positioned on the vortex end bearing, and the vortex end fixed sleeve end face is a cambered surface structure for baffling and guiding.
As a preferable scheme of the miniature turbojet engine vertical air-borrowing high-pressure cooling lubrication bearing structure, the air-borrowing channels are uniformly distributed along the circumferential direction of the diffuser.
As a preferable scheme of the miniature turbojet engine vertical air-borrowing high-pressure cooling lubrication bearing structure, the number of the air-borrowing channels is 6.
Compared with the prior art, the invention has the advantages that: (1) The lubrication effect of the pressure end bearing and the vortex end bearing is good, and the addition of 60% of engine oil is reduced: lubrication can be fully carried into the bearing casing for lubrication of the bearing, both at high engine speeds and at low engine speeds. The high-pressure cold air flow borrowed by the air channel is vertically shot on the end face of the pressure end sleeve, and the lubricating oil is vertically shot on the end face of the pressure end sleeve by the oil pipe, in the process, the lubricating oil is changed into tiny oil drops by creating the baffle guide face of the pressure end sleeve and centrifugally separating, the high-pressure air flow is forcedly mixed with the fine oil drops to atomize the fine oil drops, the lubricating oil enters the bearing box in the form of oil mist to lubricate the bearing, the oil mist lubricates the bearing with the best effect, and the miniature turbojet engine of the non-patent needs to add 5% of engine oil in the fuel oil, but the structure of the invention is adopted to add no or at most 2% of engine oil. (2) good cooling effect, and prolonged bearing service life: the invention is characterized in that a large amount of high-pressure cold air flow (2-3 times more than the traditional air borrowing amount without the invention) vertically enters a cavity formed by the pressure impeller, the diffuser, the pressure end fixed sleeve and the bearing casing through six air inlets, and is baffled and guided to enter the bearing casing at high speed through the baffling guide surface of the pressure end fixed sleeve, so that the pressure end bearing and the vortex end bearing are subjected to air cooling, and particularly, the high temperature conducted to the vortex end bearing by the turbine and the shaft neck at the fixed turbine are subjected to strong air cooling, thereby obtaining a very good effect. The temperature of the eddy end bearing can be reduced by 34% through measurement, and the service life of the bearing is greatly prolonged. Because of this, no or little oil is used after the engine has been turned off. (3) Under the condition of low air pressure in the engine in the starting stage, the lubricating oil is ensured to flow into the bearing casing and lubricate the bearing, and the phenomenon of oil leakage at the impeller end of the traditional engine is changed.
Drawings
Fig. 1 is a schematic diagram of a prior art structure.
Fig. 2 is a schematic structural diagram of an embodiment of the present invention.
Detailed Description
The invention will be described in further detail below with reference to the drawings by means of specific embodiments.
Referring to fig. 2, a vertical air-assisted high-pressure cooling lubrication bearing structure of a micro turbojet engine is shown in the drawing, and comprises a shaft 1, a pressure impeller 2, a turbine 8, a bearing casing 4, a pressure end bearing 5, a vortex end bearing 6, a pressure end fixed sleeve 3, a vortex end fixed sleeve 7 and a diffuser 9, wherein the shaft 1 is provided with a pressure impeller 2 end and a turbine 8 end which are oppositely arranged along the axial direction, the pressure impeller 2 of the shaft 1 is provided with the pressure impeller 2, the turbine 8 end of the shaft 1 is provided with the turbine 8, the bearing casing 4 is arranged around the outer side of the shaft 1 and between the pressure impeller 2 and the turbine 8, a distance exists between the bearing casing 4 and the shaft 1, so that a bearing accommodating cavity is defined between the bearing casing 4 and the shaft 1, the bearing accommodating cavity is provided with the pressure end bearing 5 positioned on the pressure impeller 2 side and the turbine 8 bearing positioned on the turbine 8 side, the shaft 1 is provided with the pressure impeller 2 and the pressure end fixed sleeve 3 positioned between the pressure impeller 8 and the pressure casing 6 and the air flow passage 9 positioned between the pressure impeller 8 and the pressure casing 6. The end pressing and fixing sleeve 3 is provided with an end pressing and fixing sleeve 3 outer peripheral surface and an end pressing and fixing sleeve 3 end surface, the end pressing and fixing sleeve 3 outer peripheral surface is opposite to the inner peripheral surface of the bearing casing 4, the end pressing and fixing sleeve 3 outer peripheral surface is sealed with the inner peripheral surface of the bearing casing 4, the end pressing and fixing sleeve 3 end surface is opposite to the end pressing bearing 5, the end pressing and fixing sleeve 3 end surface is of a cambered surface structure for baffling and guiding, the diffuser 9 is provided with an air borrowing channel 10 for borrowing air, the air borrowing channel 10 is provided with a channel air inlet and a channel air outlet, the channel air inlet is opposite to the end pressing and fixing sleeve 3 end surface, so that air in the engine cavity enters the bearing accommodating cavity from the air borrowing channel 10 through the end pressing and fixing sleeve 3 end surface.
When oil is vertically sprayed to the end face of the end pressing fixed sleeve 3 through the oil inlet pipe, the oil can only be thrown to the inner wall of the bearing casing 4 under the centrifugal action of the end face of the end pressing fixed sleeve 3 and can only be atomized in a cavity formed by the impeller 2, the diffuser 9, the end pressing fixed sleeve 3 and the bearing casing 4, and the oil can only flow into the bearing casing 4 to pass through the end pressing bearing 5 and the vortex end bearing 6 no matter the engine speed is high or low because the cavity is only opened in the direction of the bearing casing 4 and the pressure is the lowest, so that the purposes of cooling and lubricating the bearings are achieved and oil leakage of the air compressor can not be caused when the engine speed is low.
Also, when a large amount of high-pressure cold air flow (2-3 times more than the conventional air borrowing amount without the invention) pressurized by the diffuser 9 is perpendicularly emitted from the air borrowing channels 10 (6 in total) toward the end face of the pressure end stator sleeve 3, the high-pressure cold air flow is forced to be folded toward the bearing housing 4. Because the seal (see seal position) is formed between the end pressing fixed sleeve 3 and the bearing casing 4, only the direction of the bearing casing 4 is opened in the cavity formed by the impeller 2, the diffuser 9, the end pressing fixed sleeve 3 and the bearing casing 4, and the air pressure is the lowest, the introduced high-pressure cold air flow brings lubricating oil into the bearing casing 4 together, and is discharged by the turbine 8 after passing through the end pressing bearing 5 and the turbine end bearing 6, thereby achieving the purposes of cooling and lubricating the bearing.
The foregoing has outlined rather broadly the more detailed description of the invention in order that the detailed description thereof that follows may be better understood, and in order that the present invention may be better understood. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the invention, which are all within the scope of the invention. Accordingly, the scope of protection of the present invention is to be determined by the appended claims.
Claims (3)
1. The utility model provides a miniature turbojet engine is perpendicular with air high pressure cooling lubrication bearing structure, include, axle, pressure impeller, turbine, bearing cartridge, pressure end bearing, vortex end bearing, pressure end fixed cover, vortex end fixed cover and diffuser, wherein, the axle has along its axial relative pressure impeller end and the turbine end that sets up, the pressure impeller of axle is served and is had the pressure impeller, the turbine is served to the turbine of axle, the bearing cartridge is encircleed in the outside of axle and is arranged in pressure impeller and between turbine, the bearing cartridge and the interaxial have a distance for both delimit the bearing accommodation cavity, have in the bearing accommodation cavity pressure end bearing and the turbine bearing of turbine side that is located in pressure impeller side, have pressure end fixed cover between pressure end bearing and the pressure impeller on the axle, the turbine end bearing and the turbine are arranged on the shaft, the diffuser is arranged around the turbine end bearing, the diffuser is provided with an air flow channel at the outlet of the impeller and is positioned between the impeller and the turbine end bearing casing, the turbine end bearing is characterized in that the turbine end bearing is provided with a turbine end bearing outer circumferential surface and a turbine end bearing end surface, the turbine end bearing outer circumferential surface is sealed with the turbine end bearing inner circumferential surface, the turbine end bearing end surface is positioned with the turbine end bearing, the turbine end bearing end surface is provided with an arc surface structure for guiding baffle, the diffuser is provided with an air channel for air borrowing, the air channel is provided with a channel air inlet and a channel air outlet, the channel air inlet is positioned in an engine cavity, the channel air outlet is positioned with the turbine end bearing end surface, so that air in the engine cavity is led from the air channel, and the bearing enters the bearing accommodating cavity through the end surface of the pressing end fixed sleeve, and the number of the air borrowing channels is 6.
2. The structure of claim 1, wherein the vortex end sleeve has a vortex end sleeve end face, the vortex end sleeve end face is positioned on the vortex end bearing, and the vortex end sleeve end face is a cambered surface structure for deflection guiding.
3. The structure of claim 1 or 2, wherein the air-passage channels are uniformly distributed along the circumferential direction of the diffuser.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710121680.6A CN107246324B (en) | 2017-03-02 | 2017-03-02 | Vertical air-borrowing high-pressure cooling lubrication bearing structure of miniature turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710121680.6A CN107246324B (en) | 2017-03-02 | 2017-03-02 | Vertical air-borrowing high-pressure cooling lubrication bearing structure of miniature turbojet engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107246324A CN107246324A (en) | 2017-10-13 |
| CN107246324B true CN107246324B (en) | 2024-01-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710121680.6A Active CN107246324B (en) | 2017-03-02 | 2017-03-02 | Vertical air-borrowing high-pressure cooling lubrication bearing structure of miniature turbojet engine |
Country Status (1)
| Country | Link |
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| CN (1) | CN107246324B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108343512B (en) * | 2018-01-24 | 2019-11-12 | 深圳意动航空科技有限公司 | A kind of engine rotor bracket |
| CN108518284B (en) * | 2018-04-18 | 2024-03-22 | 常州环能涡轮动力股份有限公司 | Turbojet engine and oil path structure thereof |
| CN109854629A (en) * | 2019-03-28 | 2019-06-07 | 绵阳小巨人动力设备有限公司 | A kind of heat-proof device of Micro Turbine Jet Engine bearing |
| CN115095428B (en) * | 2022-05-31 | 2024-08-27 | 中科航星科技股份有限公司 | Oil mist lubrication cooling structure suitable for high-efficiency Fischer-Tropsch engine bearing |
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| Publication number | Publication date |
|---|---|
| CN107246324A (en) | 2017-10-13 |
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