CN114542324A - Porous two-phase bearing of micro turbojet engine and rotor supporting structure thereof - Google Patents

Porous two-phase bearing of micro turbojet engine and rotor supporting structure thereof Download PDF

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Publication number
CN114542324A
CN114542324A CN202210191351.XA CN202210191351A CN114542324A CN 114542324 A CN114542324 A CN 114542324A CN 202210191351 A CN202210191351 A CN 202210191351A CN 114542324 A CN114542324 A CN 114542324A
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CN
China
Prior art keywords
bearing
porous
central shaft
supporting structure
turbojet engine
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Pending
Application number
CN202210191351.XA
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Chinese (zh)
Inventor
***
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hangxing Aerospace Taicang Kinetic Energy Technology Co ltd
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Beijing Yingtian Aviation Power Technology Co ltd
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Publication date
Application filed by Beijing Yingtian Aviation Power Technology Co ltd filed Critical Beijing Yingtian Aviation Power Technology Co ltd
Priority to CN202210191351.XA priority Critical patent/CN114542324A/en
Publication of CN114542324A publication Critical patent/CN114542324A/en
Pending legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • 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
    • 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
    • F02C7/28—Arrangement of seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C35/00—Rigid support of bearing units; Housings, e.g. caps, covers
    • F16C35/02—Rigid support of bearing units; Housings, e.g. caps, covers in the case of sliding-contact bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C37/00—Cooling of bearings
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Rolling Contact Bearings (AREA)
  • Support Of The Bearing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention discloses a porous two-phase bearing of a microminiature turbojet engine and a rotor supporting structure thereof, wherein the porous two-phase bearing comprises an impeller, a central shaft, a turbine, a front bearing and a rear bearing; the impeller is fixed at the front end of the central shaft, the turbine is fixed at the rear end of the central shaft, the front bearing is arranged at the front end of the central shaft and behind the impeller, and the rear bearing is arranged at the rear end of the central shaft and in front of the turbine. The porous characteristic of the bearing material and the affinity of the material and oil are fully utilized, the cooling and lubrication of the bearing, the shaft sleeve and the central shaft are completed by the lubricating oil and the ambient air of the bearing, a separate bearing lubricating pipeline is not required to be arranged, and the structure of an engine oil supply system is simple; the porous bearing is composed of a bearing inner ring and a bearing outer ring, has a ball-free structure, and has smaller radial size and lower cost compared with the traditional rolling bearing. Many aspects such as compressible adjustable ring, elastic gasket compensate displacement and vibration, effectively improve bearing life-span and rotor system's job stabilization nature and reliability.

Description

Porous two-phase bearing of micro turbojet engine and rotor supporting structure thereof
Technical Field
The invention relates to the field of engines, in particular to a porous two-phase bearing of a micro turbojet engine and a rotor supporting structure thereof.
Background
Compared with the conventional engine, the microminiature turbojet engine has small size, light weight and high thrust-weight ratio, is widely applied to microminiature unmanned target planes, reconnaissance planes and model airplanes, can also provide power for tactical cruise missiles, and simultaneously has rapidness and convenience compared with charging because of adopting an oiling mode to supplement energy, and can also be used as a portable future field operation energy.
The bearing lubricating system is an indispensable important component in an engine system, fully ensures the safe and reliable operation of an engine rotor in the processes of starting, operating and shutting down the engine, and prevents the engine from being damaged due to friction overheating so as to prevent the engine from working abnormally.
Most of the existing microminiature turbojet engines adopt a rolling bearing lubricating system, and although the rolling bearing has good starting performance and can keep higher bearing capacity at medium speed, the microminiature turbojet engines also have the defect of fatality, so that the development of the turbojet engines is limited to a certain extent. On one hand, due to the existence of the rolling bearing, an engine system needs to be additionally provided with a separate lubricating oil supply pipeline, so that the complexity of the system is increased; on the other hand, as the rolling bearing for the turbojet engine generally consists of an inner ring, an outer ring and balls, the radial dimension of the rolling bearing is larger due to the existence of the balls; secondly, the rolling bearing has low vibration damping capacity, and when the engine works at high rotating speed, the service life of the bearing is greatly reduced; finally, ball bearing lubrication systems are costly.
Disclosure of Invention
The problems that an engine is lubricated by a rolling bearing, the structure of a system oil way is complex, the size is large and the service life is short in the prior art are solved. The invention provides a porous two-phase bearing of a micro turbojet engine and a rotor supporting structure thereof, wherein the porous two-phase bearing is used for supporting, lubricating oil is impregnated in the porous two-phase bearing, self lubricating and cooling are realized, the structure is simple, and the rotor supporting structure has a damping effect.
In order to achieve the purpose, the invention provides a porous two-phase bearing of a micro turbojet engine and a rotor supporting structure thereof, which comprise an impeller, a front bearing, a rear bearing, a central shaft and a turbine; the impeller is fixed in the front end of center pin, and the turbine is fixed in the rear end of center pin, and the step has all been seted up to the front and back end of center pin, and preceding bearing housing is located on the center pin and sets up in the step that is close to the center pin front end, and back bearing housing is located on the center pin and sets up in the step that is close to the center pin rear end, and preceding bearing and back bearing all configure into porous bearing, and porous bearing includes outer lane and inner circle, and the outer lane cover is located outside the inner circle, and outer lane and inner circle are porous structure.
In a preferred technical scheme of the invention, a shaft sleeve is sleeved outside the central shaft, a double-layer sealing ring is arranged between the front bearing and the shaft sleeve, and a single-layer sealing ring is arranged between the rear bearing and the shaft sleeve.
In a preferred technical scheme of the invention, a plurality of elastic gaskets are mounted at the rear end of the front bearing, and a single elastic gasket is mounted at the front end of the rear bearing.
In a preferred technical scheme of the invention, an oil storage tank is arranged on the inner side of the outer ring.
In a preferred technical scheme of the invention, the front end of the central shaft is connected with a front locking nut which abuts against the impeller, the rear end of the central shaft is connected with a rear locking nut which abuts against the turbine.
In a preferred technical scheme of the invention, a diffuser is arranged outside the shaft sleeve, and a casing is arranged outside the diffuser.
In a preferred technical scheme of the invention, a flame tube is arranged in the casing, the flame tube is sleeved outside the shaft sleeve, the output end of the flame tube is connected with a guider, and the guider extends to one side of the turbine.
In a preferred embodiment of the present invention, the central shaft is further sleeved with a compressible adjusting ring, and the compressible adjusting ring abuts against the rear end of the rear bearing.
In a preferred technical scheme of the invention, the front end of the casing is further fixed with a jacket, the inner side of the jacket forms an air inlet, and the impeller extends into the air inlet.
In a preferred technical scheme of the invention, the rear end of the casing is connected with a tail nozzle, and the tail nozzle is communicated with the casing.
The invention has the beneficial effects that:
according to the porous two-phase bearing of the micro turbojet engine and the rotor supporting structure of the bearing, the porous characteristic of a bearing material and the affinity of the material and oil are fully utilized, the cooling and lubrication of the bearing, a shaft sleeve and a central shaft are completed by means of lubricating oil and ambient air carried by the bearing, a separate bearing lubricating pipeline is not required to be arranged, and an engine oil supply system is simple in structure; the porous bearing is composed of a bearing inner ring and a bearing outer ring, has a ball-free structure, and has smaller radial size and lower cost compared with the traditional rolling bearing. Displacement and vibration can be compensated in multiple aspects such as the compressible adjusting ring and the elastic gasket, and the working stability and reliability of the rotor system are effectively improved.
Drawings
FIG. 1 is a schematic structural diagram of a porous two-phase bearing and a rotor supporting structure thereof of a micro turbojet engine according to an embodiment of the present invention;
FIG. 2 is an enlarged schematic view of the structure at A in FIG. 1;
FIG. 3 is an enlarged view of the structure at B in FIG. 1;
FIG. 4 is a schematic view of the air flow direction in the operating state of the rotor system of FIG. 1;
FIG. 5 is a schematic view showing the oil leakage direction of the porous bearing pores in the operating state of the rotor system;
FIG. 6 is a schematic view showing the oil return direction of the porous bearing pores in the operating state of the rotor system;
FIG. 7 is a cross-sectional view of the front and rear bearings of FIG. 1;
fig. 8 is a perspective view of the front and rear bearings.
In the figure:
1-impeller, 2-diffuser, 3-shaft sleeve, 41-front bearing, 42-rear bearing, 43-outer ring, 44-inner ring, 45-oil storage groove, 46-bearing clearance, 5-central shaft, 6-compressible adjusting ring, 7-turbine, 8-front locking nut, 9-rear locking nut, 10-casing, 11-outer sleeve, 12-air inlet, 13-flame tube, 14-guider, 15-tail nozzle and 16-elastic gasket.
Detailed Description
The technical scheme of the invention is further explained by the specific implementation mode in combination with the attached drawings.
As shown in fig. 1-8, the embodiment provides a porous two-phase bearing of a micro turbojet engine and a rotor supporting structure thereof, which comprises an impeller 1, a front bearing 41, a rear bearing 42, a central shaft 5 and a turbine 7; the impeller 1 is fixed at the front end of the central shaft 5, the turbine 7 is fixed at the rear end of the central shaft 5, steps are formed in the front and rear of the central shaft 5, the front bearing 41 is sleeved on the central shaft 5 and is arranged in the step close to the front end of the central shaft 5, the rear bearing 42 is sleeved on the central shaft 5 and is arranged in the step close to the rear end of the central shaft 5, the front bearing 41 and the rear bearing 42 are both configured to be porous bearings, each porous bearing comprises an outer ring 43 and an inner ring 44, the outer ring 43 is sleeved outside the inner ring 44, and the outer ring 43 and the inner ring 44 are both of porous structures.
When the rotor system is applied to a micro turbojet engine, a shaft sleeve 3 is sleeved outside a central shaft 5, a diffuser 2 is installed outside the shaft sleeve 3 and close to one side of an impeller 1, and a casing 10 is arranged outside the diffuser 2. An outer sleeve 11 is fixed at the front end of the casing 10, an air inlet channel 12 is formed inside the outer sleeve 11, and the impeller 1 extends into the air inlet channel 12. The rear end of the casing 10 is connected with a tail nozzle 15. A flame tube 13 is arranged outside the shaft sleeve 3 and inside the casing 10, the output end of the flame tube 13 is connected with a guider 14, and the guider 14 extends to one side of the turbine 7.
When the central shaft 5 is not rotating, the lubricating oil fills the pores of the outer ring 43 and the inner ring 44 of the bearing. In the process of engine operation, the central shaft 5 rotates, the lubrication of the bearing is realized by means of a high-temperature-resistant lubricant coating sprayed on the contact surface of the bearing inner ring 44 and the bearing outer ring 43 on one hand, and when the rotor system slightly vibrates, the lubricating oil in the oil storage tank 45 immediately flows to the bearing gap 46 on the other hand, and the lubricating effect of the bearing gap 46 is ensured on the other hand. High-pressure air enters a gap formed between the back surface of the impeller 1 and the diffuser 2 through the diffuser 2, and the air passes through the front bearing 41 under the action of pressure. Because the bearing in the embodiment is of a porous structure and has a strong flow equalizing effect on air passing through the bearing, the air can realize the isotropic cooling of the bearing, the air passing through the front bearing 41 continuously flows towards the rear bearing 42, the inner wall of the shaft sleeve 3 and the central shaft 5 are cooled in the process, and finally flows into the rear bearing 42 to isotropic cool the rear bearing 42. To this end, cooling of the entire bearing system and the central shaft 5 is achieved.
When the rotor is in operation, as the temperature of the bearing rises, the volume expansion coefficient of the oil is larger than that of the metal, so that the lubricating oil automatically enters the bearing clearance 46, the lubrication and cooling of the bearing are realized, the lubricating oil in the oil storage tank 45 also partially flows into the bearing clearance 46, and the loss of the lubricating oil overflowing through the pores due to the high-speed long-time operation of the bearing or the over-high temperature rise and the like is compensated.
When the rotor stops rotating, the front bearing 41 and the rear bearing 42 are cooled, the pores recover, and the lubricating oil returns to the pores of the bearing, at this time, the lubricating oil returning to the pores inside the bearing consists of two parts, one part is the lubricating oil seeped out through the porous bearing in the working state of the rotor, and the other part is the lubricating oil flowing into the bearing gap 46 in the oil storage tank 45 when the engine is started or compensated.
Furthermore, a double-layer sealing ring is arranged between the front bearing 41 and the shaft sleeve 3, and a single-layer sealing ring is arranged between the rear bearing 42 and the shaft sleeve 3. The sealing ring can prevent lubricating oil from flowing backwards, and the lubricating oil is prevented from flowing out of the concave table too fast, so that the lubricating efficiency is low.
Further, a plurality of elastic washers 16 are mounted to the rear end of the front bearing 41, and a single elastic washer 16 is mounted to the front end of the rear bearing 42. The elastic pad 16 on the front bearing 41 is used to compensate the axial displacement of the central shaft 5 and the front bearing 41, and the elastic pad 16 on the rear bearing 42 is also used to compensate the axial position to avoid the bearing displacement.
Further, an oil storage tank 45 is provided inside the outer ring 43. The oil storage tank 45 is filled with lubricating oil, and when the rotor slightly vibrates, the lubricating oil in the oil storage tank 45 immediately flows to the bearing gap 46, so that the lubricating effect is guaranteed.
Further, the front end of the central shaft 5 is connected with a front locking nut 8, the front locking nut 8 abuts against the impeller 1, the rear end of the central shaft 5 is connected with a rear locking nut 9, and the rear locking nut 9 abuts against the turbine 7. The front locking nut 8 compresses the front end of the impeller 1 onto the central shaft 5, and the rear locking nut 9 supports the turbine 7 tightly onto the central shaft 5, so that the axial fixation of the whole rotor system is realized, and the change of the axial position of the rotor system due to vibration during working is avoided.
Further, a guide 14 is connected to an output end of the combustor basket 13, and the guide 14 extends to one side of the turbine 7. The guide 14 can guide the high-temperature gas output by the flame tube 13 to the turbine 7, so that the turbine 7 can fully receive the high-temperature gas to rotate, and the rotating efficiency is improved.
Furthermore, a compressible adjusting ring 6 is sleeved on the central shaft 5, and the compressible adjusting ring 6 abuts against the rear end of the rear bearing 42. The compressible adjusting ring 6 is fixed at the rear end of the rear bearing 42, so that the rear bearing 42 is always in a compression state on one hand, and the vibration generated when the rotor rotates can be absorbed on the other hand, and the rotor system can be ensured to work stably and lowly.
Further, the air in the rear bearing 42 is discharged and mixed with the gas at the front end of the turbine 7, and is discharged through the tail pipe 15 to generate thrust.
Other techniques of the present embodiment employ existing techniques.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the spirit and scope of the invention. The present invention is not to be limited by the specific embodiments disclosed herein, and other embodiments that fall within the scope of the claims of the present application are intended to be within the scope of the present invention.

Claims (10)

1. A porous two-phase bearing of microminiature turbojet engine and a rotor supporting structure thereof are characterized in that: comprises an impeller (1), a front bearing (41), a rear bearing (42), a central shaft (5) and a turbine (7);
impeller (1) is fixed in the front end of center pin (5), turbine (7) are fixed in the rear end of center pin (5), the step has all been seted up around center pin (5), front bearing (41) cover is located on center pin (5) and is set up in the step that is close to center pin (5) front end, rear bearing (42) cover is located on center pin (5) and is set up in the step that is close to center pin (5) rear end, porous bearing is all configured to with rear bearing (42) to front bearing (41), porous bearing includes outer lane (43) and inner circle (44), outer lane (43) cover is located outside inner circle (44), and outer lane (43) and inner circle (44) are porous structure.
2. The porous two-phase bearing and the rotor supporting structure thereof for the micro turbojet engine as recited in claim 1, wherein:
the bearing is characterized in that a shaft sleeve (3) is sleeved outside the central shaft (5), a double-layer sealing ring is arranged between the front bearing (41) and the shaft sleeve (3), and a single-layer sealing ring is arranged between the rear bearing (42) and the shaft sleeve (3).
3. The porous two-phase bearing and the rotor supporting structure thereof for the micro turbojet engine as recited in claim 1, wherein:
a plurality of elastic gaskets (16) are installed at the rear end of the front bearing (41), and a single elastic gasket (16) is installed at the front end of the rear bearing (42).
4. The porous two-phase bearing and the rotor supporting structure thereof for the micro turbojet engine as recited in claim 1, wherein:
an oil storage tank (45) is arranged on the inner side of the outer ring (43).
5. The porous two-phase bearing and the rotor supporting structure thereof for the micro turbojet engine as recited in claim 1, wherein:
the front end of the central shaft (5) is connected with a front locking nut (8), the front locking nut (8) abuts against the impeller (1), the rear end of the central shaft (5) is connected with a rear locking screw, and a rear locking nut (9) abuts against the turbine (7).
6. The porous two-phase bearing and the rotor supporting structure thereof for the micro turbojet engine as recited in claim 2, wherein:
a diffuser (2) is arranged outside the shaft sleeve (3), and a casing (10) is arranged outside the diffuser (2).
7. The porous two-phase bearing of micro turbojet engine and the rotor supporting structure thereof as claimed in claim 6, wherein:
be provided with flame tube (13) in casing (10), flame tube (13) cover is located outside axle sleeve (3), the output of flame tube (13) is connected with director (14), director (14) extend to one side of turbine (7).
8. The porous two-phase bearing and the rotor supporting structure thereof for the micro turbojet engine as recited in claim 1, wherein:
the central shaft (5) is also sleeved with a compressible adjusting ring (6), and the compressible adjusting ring (6) is abutted against the rear end of the rear bearing (42).
9. The porous two-phase bearing of micro turbojet engine and the rotor supporting structure thereof as claimed in claim 6, wherein:
the front end of machine casket (10) still is fixed with overcoat (11), and the inboard constitution intake duct (12) of overcoat (11), impeller (1) extends to in intake duct (12).
10. The porous two-phase bearing of micro turbojet engine and the rotor supporting structure thereof as claimed in claim 6, wherein:
the rear end of the casing (10) is connected with a tail nozzle (15), and the tail nozzle (15) is communicated with the casing (10).
CN202210191351.XA 2022-02-28 2022-02-28 Porous two-phase bearing of micro turbojet engine and rotor supporting structure thereof Pending CN114542324A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210191351.XA CN114542324A (en) 2022-02-28 2022-02-28 Porous two-phase bearing of micro turbojet engine and rotor supporting structure thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210191351.XA CN114542324A (en) 2022-02-28 2022-02-28 Porous two-phase bearing of micro turbojet engine and rotor supporting structure thereof

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Publication Number Publication Date
CN114542324A true CN114542324A (en) 2022-05-27

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN201053353Y (en) * 2006-12-29 2008-04-30 深圳市康铖机械设备有限公司 Mini turbine jet engine
CN105871101A (en) * 2016-05-23 2016-08-17 杭州万辰机电科技有限公司 High-speed permanent magnet motor
CN106424771A (en) * 2016-11-30 2017-02-22 湖南大学 Micro spindle for fine machining
EP3343053A1 (en) * 2016-12-16 2018-07-04 General Electric Company Joint-less continuous plain journal bearing
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

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN201053353Y (en) * 2006-12-29 2008-04-30 深圳市康铖机械设备有限公司 Mini turbine jet engine
CN105871101A (en) * 2016-05-23 2016-08-17 杭州万辰机电科技有限公司 High-speed permanent magnet motor
CN106424771A (en) * 2016-11-30 2017-02-22 湖南大学 Micro spindle for fine machining
EP3343053A1 (en) * 2016-12-16 2018-07-04 General Electric Company Joint-less continuous plain journal bearing
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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Inventor after: Li Qiang

Inventor after: Peng Hongwei

Inventor after: Chen Kerun

Inventor after: Li Na

Inventor after: Zuo Anjun

Inventor after: Ni Zhehua

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