CN112761791A - Bearing-embedded miniature gas turbine of motor - Google Patents
Bearing-embedded miniature gas turbine of motor Download PDFInfo
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- CN112761791A CN112761791A CN202011288570.7A CN202011288570A CN112761791A CN 112761791 A CN112761791 A CN 112761791A CN 202011288570 A CN202011288570 A CN 202011288570A CN 112761791 A CN112761791 A CN 112761791A
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- rotating shaft
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- 230000005611 electricity Effects 0.000 description 1
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- 238000010248 power generation Methods 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
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Classifications
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- 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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
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- 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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
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- 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
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/053—Shafts
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K5/00—Casings; Enclosures; Supports
- H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
- H02K5/16—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields
- H02K5/167—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields using sliding-contact or spherical cap bearings
- H02K5/1672—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields using sliding-contact or spherical cap bearings radially supporting the rotary shaft at both ends of the rotor
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- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Magnetic Bearings And Hydrostatic Bearings (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a bearing-embedded micro gas turbine of a motor, which comprises a rotor system, a motor casing, a gas turbine casing and a combustion chamber, wherein the rotor system comprises a rotating shaft, a thrust bearing, a first radial bearing, the motor, a gas compressor, a second radial bearing and the turbine are sequentially arranged on the rotating shaft, and a third bearing is arranged between the rotating shaft and the motor; the motor casing is covered on the periphery of the motor; the gas turbine casing is covered on the peripheries of the gas compressor and the turbine and is connected with the motor casing; the combustion chamber is connected to the gas turbine casing. According to the micro gas turbine with the bearing embedded in the motor, the rotating shaft is supported by the bearings at two ends and is stressed uniformly, so that the unbalanced weight caused by the suspension of the shaft end of the rotor can be avoided, the operation stability is good, and the size adjustable range of the rotating shaft in the axial direction is large. The radial bearing is arranged in the motor, so that the mutual disturbance between the motor and the rotating shaft during high-speed rotation is reduced, and the stability of the rotor during the operation of the gas turbine is effectively enhanced.
Description
Technical Field
The invention relates to a bearing embedded type micro gas turbine with a motor, and belongs to the technical field of micro gas turbines.
Background
In the field of micro gas turbine power generation, a micro gas turbine power generator set generally includes a coaxially mounted generator and a micro gas turbine. Specifically, the micro gas turbine mainly comprises three parts, namely a gas compressor, a combustion chamber and a turbine, wherein air is compressed into high-temperature and high-pressure air after entering the gas compressor, then the high-temperature and high-pressure air is supplied to the combustion chamber to be mixed and combusted with fuel, and the generated high-temperature and high-pressure gas expands in the turbine to do work to push the turbine to rotate so as to drive the generator to generate electricity. Because the magnetic components and coil windings in the generator are not high-temperature resistant, the generator cannot be arranged at the hot end of the rotor system, namely one side of the turbine; in the prior art, a generator is generally installed at an air inlet end of a rotating shaft of a micro gas turbine, namely an air inlet end of a compressor. In order to support the rotating shaft, radial bearings are arranged between the rotating shaft and the stator and positioned at two end parts of the stator to be used as fulcrums; the tail part (namely the gas outlet end) of the gas turbine is also provided with components such as a gas compressor, a turbine, a combustion chamber and the like, so that the weight is large, and the following problems exist:
1. the rotating shaft cannot be too long, otherwise, the problems of downward inclination of the tail part, upwarp of the head part, unstable operation of the rotor, serious vibration and the like can be caused.
2. The motor has large mass, and the rotating shaft and the motor have large disturbance when rotating relatively, so that the whole machine generates serious vibration.
In addition, the epaxial thrust dish that currently commonly uses is mostly protruding formula, and its problem that exists is, and thrust dish and pivot an organic whole are made, add man-hour, need on whole root axle material turning process, because the thrust dish height is great, can produce great turning volume, extravagant material, and because the turning number of times is many, need destressing many times, the technology is complicated. Moreover, because a single thrust disc is heavy in weight, when the rotating shaft rotates at a high speed, inertia force can be generated, the rotating shaft is caused to deviate from the axis to rotate, and the rotating stability is poor and the vibration is serious in a rotor system.
Disclosure of Invention
In view of the prior art, the invention provides a micro gas turbine with a bearing embedded in a motor. According to the micro gas turbine with the bearing embedded in the motor, the two branch points are respectively arranged at the two ends of the rotating shaft, so that the balance of the rotating shaft is better, the operation stability of a rotor system is good, and the problem of vibration of the whole machine can be further solved by arranging the bearing in the motor. The invention can solve the size limitation of the tail part of the rotating shaft and solve the problems of unstable operation and serious vibration of a rotor system.
The invention is realized by the following technical scheme:
a bearing-embedded micro gas turbine of a motor comprises a rotor system, a motor casing, a gas turbine casing and a combustion chamber, wherein the rotor system comprises a rotating shaft, a thrust bearing, a first radial bearing, the motor, a gas compressor, a second radial bearing and the turbine are sequentially arranged on the rotating shaft, and a third bearing is arranged between the rotating shaft and the motor; the motor casing is covered on the periphery of the motor; the gas turbine casing is covered on the peripheries of the gas compressor and the turbine and is connected with the motor casing; the combustion chamber is connected with the gas turbine casing, the gas inlet of the combustion chamber is connected with the gas outlet of the gas compressor, and the gas outlet of the combustion chamber is connected with the gas inlet of the turbine.
Further, the third bearing is sleeve-shaped, and the matching relationship between the third bearing and the motor is in three modes, including the following steps:
(1) the outer wall of the third bearing is provided with a plurality of convex blocks parallel to the axis, correspondingly, the inner wall of the motor is provided with a groove corresponding to the convex blocks, and the third bearing is axially arranged in the motor to enable the convex blocks to be clamped in the grooves for fixing; a preset gap is arranged between the inner wall of the third bearing and the rotating shaft.
(2) The third bearing is sleeved in the motor in a hot mode and is in tight fit with the motor, a part (such as a pin) for preventing circumferential rotation is arranged between the motor and the third bearing, one end of the part for preventing circumferential rotation is fixed in the motor, and the other end of the part for preventing circumferential rotation is fixed on the outer wall of the third bearing; a preset gap is arranged between the third bearing and the rotating shaft, and the rotating shaft is supported in the third bearing by virtue of an air film in the preset gap; at this time, the third bearing is used as a radial bearing.
(3) The third bearing is sleeved in the motor in a hot mode and is in tight fit with the motor, a part (such as a pin) for preventing circumferential rotation is arranged between the motor and the third bearing, one end of the part for preventing circumferential rotation is fixed in the motor, and the other end of the part for preventing circumferential rotation is fixed on the outer wall of the third bearing; at least one circle of rubber coating is arranged around the outer wall of the third bearing to be used as damping; a predetermined gap is provided between the third bearing and the rotating shaft, and the rotating shaft is supported in the third bearing by means of an air film in the predetermined gap. In the present embodiment, in addition to the fitting relationship shown in (2), a damper is provided on the surface of the third bearing.
Further, the third bearing is made of one or more of nylon reinforced plastics, polyethylene, polycarbonate, carbon fiber, glass fiber, aluminum oxide and silicon carbide.
Furthermore, a diffuser is arranged between the exhaust port of the compressor and the air inlet of the combustion chamber so as to further improve the pressure of the high-temperature and high-pressure gas entering the turbine for doing work.
Furthermore, a reinforcing ring is arranged between the gas compressor and the turbine, the second radial bearing is sleeved on the reinforcing ring, and the reinforcing ring is supported in the second radial bearing by means of a gas film. The function of setting up the beaded finish is: the requirement on the rigidity of the rotor (the high requirement on the strength of the rotating shaft in the high-speed rotating process of the rotor system) is met, and meanwhile, the reinforcing ring can be used as a mounting shaft of the second radial bearing.
Furthermore, the rotating shaft comprises a first shaft section and a second shaft section which are integrally formed, the diameter of the first shaft section is larger than that of the second shaft section, and a step surface is formed at the transition position of the first shaft section and the second shaft section.
Further, the thrust bearing, the first radial bearing and the motor are arranged on the first shaft section; the compressor, the second radial bearing and the turbine are arranged on the second shaft section; one end of the compressor is abutted against the step surface.
Further, two coaxial thrust discs are arranged on the first shaft section close to the air inlet end.
Further, the shaft diameter of the second shaft section can be made thin (for rotor dynamic performance reasons, the lighter the weight of the shaft, the lighter the diameter of the shaft).
Further, the first radial bearing, the second radial bearing or/and the third bearing is/are air bearings. The air bearing is a dynamic pressure bearing, a static pressure bearing or a dynamic and static pressure mixed bearing.
Furthermore, the third bearing is a dynamic pressure air bearing, and the rotating shaft is supported by an air film to rotate in the third bearing after floating.
Further, the structure of the thrust bearing is as follows: the left bearing unit and the right bearing unit are arranged oppositely, an air cavity is arranged between the two bearing units, an air inlet on the bearing shell continuously ventilates, the air enters the bearing air cavity along a gap between the two bearing units, air holes of the two bearing units enter the two sides, an air film is formed between the bearing units and the thrust disc, and the axial thrust effect is achieved.
According to the micro gas turbine with the bearing embedded in the motor, the rotating shaft is supported by the bearings at two ends (namely the first radial bearing and the second radial bearing), the stress is uniform, the unbalanced weight caused by the suspension of the shaft end of the rotor can be avoided, the operation stability is good, and the size adjustable range of the rotating shaft in the axial direction is large. The radial bearing is arranged in the motor, so that the mutual disturbance between the motor and the rotating shaft during high-speed rotation is reduced, and the stability of the rotor during the operation of the gas turbine is effectively enhanced.
According to the micro gas turbine with the bearings embedded in the motor, all the bearings are arranged in the motor casing, so that the machining precision of the part for arranging the bearing stator in the casing is only required to be ensured, and the part for connecting the bearing stator in the casing can be machined through one-time clamping during assembly.
The various terms and phrases used herein have the ordinary meaning as is well known to those skilled in the art. To the extent that the terms and phrases are not inconsistent with known meanings, the meaning of the present invention will prevail.
Drawings
FIG. 1: the invention is a structural schematic diagram of a micro gas turbine with a bearing embedded in a motor.
Fig. 2 is a partially enlarged view of a position a in fig. 1.
Fig. 3 is a partially enlarged view of a portion B in fig. 1.
FIG. 4: the motor and the bearing are in a matching relationship (embodiment 1).
FIG. 5: the motor and the bearing are in a matching relationship (embodiment 1).
FIG. 6: the motor and the bearing are in a matching relationship (embodiment 3).
FIG. 7: embodiment 3 shows a front view of a bearing in a motor and bearing mating relationship.
The damping structure comprises a rotating shaft 100, a first shaft section 110, a first shaft section 120, a second shaft section 130, a step surface 200, a thrust bearing 300, a motor 400, a second radial bearing 500, a compressor 600, a turbine 700, a reinforcing ring 810, a motor casing 820, a gas turbine casing 830, a combustion chamber 840, a diffuser 900, a first radial bearing 910, a third bearing and a damper 911.
Detailed Description
The present invention will be further described with reference to the following examples. However, the scope of the present invention is not limited to the following examples. It will be understood by those skilled in the art that various changes and modifications may be made to the invention without departing from the spirit and scope of the invention.
Embodiment 1 Motor Embedded bearing type micro gas turbine
A micro gas turbine with embedded bearings in motor comprises a rotor system, a motor casing 810, a gas turbine casing 820 and a combustion chamber 830, as shown in fig. 1, 2 and 3.
The rotor system comprises a rotating shaft 100, wherein the rotating shaft 100 comprises a first shaft section 110 and a second shaft section 120 which are integrally formed, the diameter of the first shaft section 110 is larger than that of the second shaft section 120, and a step surface 130 is formed at the transition position of the first shaft section 110 and the second shaft section 120; the first shaft segment 110 is sequentially provided with a thrust bearing 200, a first radial bearing 900 and a motor 300; the second shaft section 120 is sequentially provided with a compressor 500, a second radial bearing 400 and a turbine 600; one end of the compressor 500 abuts against the step surface 130; a third bearing 910 is provided between the rotation shaft 100 and the motor 300.
The motor housing 810 covers the outer circumference of the motor 300. The gas turbine casing 820 covers the outer peripheries of the compressor 500 and the turbine 600, and is connected to the motor casing 810. The combustion chamber 830 is connected to the gas turbine case 820, and an intake port of the combustion chamber 830 is connected to an exhaust port of the compressor 500, and an exhaust port of the combustion chamber 830 is connected to an intake port of the turbine 600.
The third bearing 910 is in a sleeve shape, and the fitting relationship with the motor 300 is as follows:
as shown in fig. 4, a plurality of protrusions are arranged on the outer wall of the third bearing 910 parallel to the axis, correspondingly, grooves are arranged on the inner wall of the motor corresponding to the protrusions, and the third bearing 910 is axially assembled into the motor 300, so that the protrusions are clamped and fixed in the grooves; a predetermined gap is provided between the inner wall of the third bearing 910 and the rotation shaft 100.
The third bearing 910 is made of one or more of nylon reinforced plastic, polyethylene, polycarbonate, carbon fiber, glass fiber, alumina, and silicon carbide.
A diffuser 840 is disposed between an exhaust port of the compressor 500 and an intake port of the combustion chamber 830 to further increase the pressure of the high-temperature and high-pressure gas entering the turbine 600 to perform work.
In order to consider both the rotor dynamics and the strength of the rotating shaft (in terms of rotor dynamics, the weight of the rotating shaft is better if the weight is lighter, and the weight is lighter if the diameter of the rotating shaft is smaller; however, during high-speed rotation of the rotor system, the strength of the rotating shaft is high), the shaft diameter of the second shaft section 120 may be set to be thin, and a reinforcing ring 700 is fixedly installed between the compressor 500 and the turbine 600 to meet the requirement of the rotor rigidity, and the reinforcing ring 700 may be used as an installation shaft of the second radial bearing 400.
The first shaft segment 110 is provided with two coaxial thrust discs near the air inlet end.
The first radial bearing 900 and the second radial bearing 400 are air bearings, and the air bearings are dynamic pressure bearings, static pressure bearings or hybrid dynamic and static pressure bearings; the third bearing 910 is a dynamic pressure air bearing, and the rotating shaft 100 is supported by an air film to rotate in the third bearing 910 after floating.
The thrust bearing 200 has the following structure: the left bearing unit and the right bearing unit are arranged oppositely, an air cavity is arranged between the two bearing units, an air inlet on the bearing shell continuously ventilates, the air enters the bearing air cavity along a gap between the two bearing units, air holes of the two bearing units enter the two sides, an air film is formed between the bearing units and the thrust disc, and the axial thrust effect is achieved.
According to the motor embedded bearing type micro gas turbine, the rotating shaft is supported through the bearings at two ends (namely the first radial bearing and the second radial bearing), the stress is uniform, the unbalanced weight caused by the suspension of the shaft end of the rotor can be avoided, the operation stability is good, and the size adjustable range in the axial direction of the rotating shaft is large. The radial bearing is arranged in the motor, so that the mutual disturbance between the motor and the rotating shaft during high-speed rotation is reduced, and the stability of the rotor during the operation of the gas turbine is effectively enhanced.
Above-mentioned little type gas turbine of embedded bearing formula of motor, all bearings are all set up in motor machine casket, only need guarantee in this machine casket like this be used for setting up the machining precision of the position of bearing stator can, the position that is used for connecting the bearing stator in this machine casket can be accomplished through the processing of once installing the card when the assembly, has reduced gas turbine generating set's machining precision and assembly precision, and the cost is reduced is fit for engineering batch production.
Embodiment 2 Motor Embedded bearing type micro gas turbine
The difference from embodiment 1 is that: the third bearing 910 is coupled to the motor 300 as follows:
as shown in fig. 5, the third bearing 910 is heat-fitted in the motor 300 and tightly fits with the motor 300, and a circumferential rotation preventing member (e.g., a pin) is disposed between the motor 300 and the third bearing 910, one end of the circumferential rotation preventing member is fixed in the motor 300, and the other end is fixed on the outer wall of the third bearing 910; a preset gap is arranged between the third bearing 910 and the rotating shaft 100, and the rotating shaft 100 is supported in the third bearing 910 by virtue of an air film in the preset gap; at this time, the third bearing 910 is used as a radial bearing.
Embodiment 3 Motor Embedded bearing type micro gas turbine
The difference from embodiment 2 is that: the third bearing 910 is coupled to the motor 300 as follows:
on the basis of the fitting relationship shown in fig. 5, a damper 911 is provided on the surface of the third bearing 910, specifically: at least one ring of rubber coating is provided around the outer wall of the third bearing 910 as shown in fig. 6 and 7.
The above examples are provided to those of ordinary skill in the art to fully disclose and describe how to make and use the claimed embodiments, and are not intended to limit the scope of the disclosure herein. Modifications apparent to those skilled in the art are intended to be within the scope of the appended claims.
Claims (10)
1. The utility model provides a little gas turbine of embedded bearing formula of motor which characterized in that: the gas turbine engine comprises a rotor system, a motor casing, a gas turbine casing and a combustion chamber, wherein the rotor system comprises a rotating shaft, a thrust bearing, a first radial bearing, a motor, a gas compressor, a second radial bearing and a turbine are sequentially arranged on the rotating shaft, and a third bearing is arranged between the rotating shaft and the motor; the motor casing is covered on the periphery of the motor; the gas turbine casing is covered on the peripheries of the gas compressor and the turbine and is connected with the motor casing; the combustion chamber is connected with the gas turbine casing, the gas inlet of the combustion chamber is connected with the gas outlet of the gas compressor, and the gas outlet of the combustion chamber is connected with the gas inlet of the turbine.
2. The micro gas turbine with bearings embedded in the motor according to claim 1, wherein: the third bearing is in a sleeve shape, and the matching relationship between the third bearing and the motor is one of the following three modes:
(1) the outer wall of the third bearing is provided with a plurality of convex blocks parallel to the axis, correspondingly, the inner wall of the motor is provided with grooves corresponding to the convex blocks, and the convex blocks are clamped in the grooves for fixing; a preset gap is formed between the inner wall of the third bearing and the rotating shaft;
(2) the third bearing is sleeved in the motor in a hot mode and is in tight fit with the motor, a part for preventing circumferential rotation is arranged between the motor and the third bearing, one end of the part for preventing circumferential rotation is fixed in the motor, and the other end of the part for preventing circumferential rotation is fixed on the outer wall of the third bearing; a preset gap is arranged between the third bearing and the rotating shaft, and the rotating shaft is supported in the third bearing by virtue of an air film in the preset gap;
(3) the third bearing is sleeved in the motor in a hot mode and is in tight fit with the motor, a part (such as a pin) for preventing circumferential rotation is arranged between the motor and the third bearing, one end of the part for preventing circumferential rotation is fixed in the motor, and the other end of the part for preventing circumferential rotation is fixed on the outer wall of the third bearing; at least one circle of rubber coating is arranged around the outer wall of the third bearing to be used as damping; a predetermined gap is provided between the third bearing and the rotating shaft, and the rotating shaft is supported in the third bearing by means of an air film in the predetermined gap.
3. The micro gas turbine with bearings embedded in the motor according to claim 1, wherein: the third bearing is made of one or more of nylon reinforced plastics, polyethylene, polycarbonate, carbon fiber, glass fiber, alumina or silicon carbide.
4. The micro gas turbine with bearings embedded in the motor according to claim 1, wherein: a diffuser is arranged between the exhaust port of the compressor and the air inlet of the combustion chamber.
5. The micro gas turbine with bearings embedded in the motor according to claim 1, wherein: a reinforcing ring is arranged between the gas compressor and the turbine, the second radial bearing is sleeved on the reinforcing ring, and the reinforcing ring is supported in the second radial bearing by means of a gas film.
6. The micro gas turbine with bearings embedded in the motor according to claim 1, wherein: the rotating shaft comprises a first shaft section and a second shaft section which are integrally formed, the diameter of the first shaft section is larger than that of the second shaft section, and a step surface is formed at the transition position of the first shaft section and the second shaft section.
7. The micro gas turbine with bearings embedded in the motor according to claim 6, wherein: the thrust bearing, the first radial bearing and the motor are arranged on the first shaft section; the compressor, the second radial bearing and the turbine are arranged on the second shaft section; one end of the compressor is abutted against the step surface;
or/and: the first shaft section is provided with two coaxial thrust discs close to the air inlet end.
8. The micro gas turbine with bearings embedded in the motor according to claim 1, wherein: the first radial bearing, the second radial bearing or/and the third bearing are/is an air bearing.
9. The micro gas turbine with bearing embedded in motor according to claim 1 or 8, wherein: the third bearing is a dynamic pressure air bearing, and the rotating shaft is supported by an air film to rotate in the third bearing after floating.
10. The micro gas turbine with bearings embedded in the motor according to claim 1, wherein: the structure of the thrust bearing is as follows: the left bearing unit and the right bearing unit are arranged oppositely, an air cavity is arranged between the two bearing units, an air inlet on the bearing shell continuously ventilates, the air enters the bearing air cavity along a gap between the two bearing units, air holes of the two bearing units enter the two sides, an air film is formed between the bearing units and the thrust disc, and the axial thrust effect is achieved.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011288570.7A CN112761791A (en) | 2020-11-18 | 2020-11-18 | Bearing-embedded miniature gas turbine of motor |
| PCT/CN2021/099972 WO2022105215A1 (en) | 2020-11-18 | 2021-06-15 | Motor-embedded bearing type micro gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011288570.7A CN112761791A (en) | 2020-11-18 | 2020-11-18 | Bearing-embedded miniature gas turbine of motor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112761791A true CN112761791A (en) | 2021-05-07 |
Family
ID=75693172
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011288570.7A Pending CN112761791A (en) | 2020-11-18 | 2020-11-18 | Bearing-embedded miniature gas turbine of motor |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN112761791A (en) |
| WO (1) | WO2022105215A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022105215A1 (en) * | 2020-11-18 | 2022-05-27 | 至玥腾风科技集团有限公司 | Motor-embedded bearing type micro gas turbine |
| CN116146348A (en) * | 2023-04-04 | 2023-05-23 | 成都中科翼能科技有限公司 | Front pivot structure of gas generator |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201570939U (en) * | 2009-10-12 | 2010-09-01 | 大连科德数控有限公司 | Electric main shaft setting structure for easy motor replacement |
| JP2013015098A (en) * | 2011-07-05 | 2013-01-24 | Matsuo Shigeto | Combustor-equipped solar heat power generation regeneration gas turbine |
| US20160172931A1 (en) * | 2014-12-11 | 2016-06-16 | Joseph Michael Teets | Alternator rotor to stator integrated hrdrodynamic bearing |
| CN111042923A (en) * | 2019-12-25 | 2020-04-21 | 迅玲腾风汽车动力科技(北京)有限公司 | Rotor system and micro gas turbine generator set |
| CN110863910A (en) * | 2019-12-27 | 2020-03-06 | 迅玲腾风汽车动力科技(北京)有限公司 | Long-span rotor system and gas turbine generator set |
| CN112761791A (en) * | 2020-11-18 | 2021-05-07 | 靳普 | Bearing-embedded miniature gas turbine of motor |
-
2020
- 2020-11-18 CN CN202011288570.7A patent/CN112761791A/en active Pending
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2021
- 2021-06-15 WO PCT/CN2021/099972 patent/WO2022105215A1/en active Application Filing
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022105215A1 (en) * | 2020-11-18 | 2022-05-27 | 至玥腾风科技集团有限公司 | Motor-embedded bearing type micro gas turbine |
| CN116146348A (en) * | 2023-04-04 | 2023-05-23 | 成都中科翼能科技有限公司 | Front pivot structure of gas generator |
| CN116146348B (en) * | 2023-04-04 | 2023-06-27 | 成都中科翼能科技有限公司 | Front pivot structure of gas generator |
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| WO2022105215A1 (en) | 2022-05-27 |
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