CN113700732A - Gas turbine rotor support system based on sliding bearing and thrust disc - Google Patents
Gas turbine rotor support system based on sliding bearing and thrust disc Download PDFInfo
- Publication number
- CN113700732A CN113700732A CN202110982630.3A CN202110982630A CN113700732A CN 113700732 A CN113700732 A CN 113700732A CN 202110982630 A CN202110982630 A CN 202110982630A CN 113700732 A CN113700732 A CN 113700732A
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- Prior art keywords
- bearing
- thrust
- radial
- sliding
- sliding bearing
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- 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
- F16C17/00—Sliding-contact bearings for exclusively rotary movement
- F16C17/02—Sliding-contact bearings for exclusively rotary movement for radial load only
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- 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
- F16C17/00—Sliding-contact bearings for exclusively rotary movement
- F16C17/04—Sliding-contact bearings for exclusively rotary movement for axial load only
- F16C17/08—Sliding-contact bearings for exclusively rotary movement for axial load only for supporting the end face of a shaft or other member, e.g. footstep bearings
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- 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
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- 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
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Sliding-Contact Bearings (AREA)
Abstract
The invention discloses a gas turbine rotor supporting system based on a sliding bearing and a thrust disc, which comprises a shaft, the thrust disc and three sliding bearings, wherein the thrust disc and the three sliding bearings are arranged at one end of the shaft, the three sliding bearings comprise a radial sliding bearing, a radial thrust sliding bearing and a thrust sliding bearing, the radial thrust sliding bearing and the thrust sliding bearing are arranged at one end of the shaft, the radial thrust sliding bearing and the thrust sliding bearing are connected through a bearing support leg, and the radial sliding bearing is arranged at the other end of the shaft and is connected with the bearing support leg through a bearing frame. The gas turbine rotor supporting system based on the sliding bearing and the thrust disc provided by the invention is based on the sliding bearing and the thrust disc, all the fulcrum positions adopt the sliding bearings, the advantages of the sliding bearings are fully exerted, and the gas turbine rotor supporting system has the advantages of strong bearing capacity, high radial positioning precision, good impact resistance, good rotation stability and small friction power consumption.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a gas turbine rotor supporting system based on a sliding bearing and a thrust disc.
Background
The gas turbine is a device for converting the heat energy of high-temperature and high-pressure combustion gas into mechanical energy, the power turbine is an important part for outputting the power of the gas turbine, and the power turbine bears huge axial force action because the gas expands in the turbine step by step. The power turbine is used as a large-size acting component, and the working environment of a large-size rotor system of the power turbine is loaded with heavy load, large in impact and large in vibration, so that the supporting component is easily damaged, and the reliable operation of the component is further influenced.
In the prior art, in a support layout of a rotary machine, a rolling bearing is generally used as a base for supporting the rotary machine. However, the rolling bearing cannot adapt to an environment with heavy load, large impact and long service life requirement, thereby affecting the operation stability of the rotor system or causing frequent maintenance and replacement. Not only reduces the operation safety of the components, but also increases the operation and maintenance cost.
Therefore, it is desirable to provide a support system adapted to a gas turbine rotor to address the above problems.
Disclosure of Invention
In order to solve the problems, the invention provides a gas turbine rotor supporting system based on a sliding bearing and a thrust disc, which comprises a shaft, the thrust disc arranged at one end of the shaft and three sliding bearings, wherein the three sliding bearings comprise a radial sliding bearing, a radial thrust sliding bearing and a thrust sliding bearing, the radial thrust sliding bearing and the thrust sliding bearing are arranged at one end of the shaft, the radial thrust sliding bearing and the thrust sliding bearing are connected through a bearing support leg, and the radial sliding bearing is arranged at the other end of the shaft and is connected with the bearing support leg through a force bearing frame.
The invention also provides a gas turbine rotor support system based on a sliding bearing and a thrust disk, which is characterized in that the radial thrust sliding bearing and the thrust sliding bearing are respectively arranged on two sides of the thrust disk.
The invention provides a gas turbine rotor support system based on a sliding bearing and a thrust disk, and is further characterized in that the radial thrust sliding bearing comprises a radial support pad, a radial thrust pad and a radial thrust bearing casing, a radial thrust oil film is arranged between the radial support pad and the shaft, and the radial thrust pad is close to the thrust disk.
The invention also features a gas turbine rotor support system based on a sliding bearing and a thrust disk, the thrust sliding bearing including a thrust sliding bearing case and a thrust pad, the thrust pad being adjacent the thrust disk.
The invention also provides a gas turbine rotor support system based on a sliding bearing and a thrust disc, which is characterized in that the number of the bearing legs is at least one.
The gas turbine rotor supporting system based on the sliding bearing and the thrust disc is further characterized in that when the number of the bearing supporting legs is two or more, the plurality of the bearing supporting legs are circumferentially and uniformly distributed according to an initial angle of 45 degrees and an interval angle of 90 degrees.
The invention also provides a gas turbine rotor support system based on a sliding bearing and a thrust disk, which is characterized in that the end of the bearing leg is provided with a flange for connecting the radial thrust sliding bearing and the thrust sliding bearing, and the flange is connected with the radial thrust sliding bearing and the thrust sliding bearing through bolts.
The invention provides a gas turbine rotor support system based on a sliding bearing and a thrust disk, which is further characterized in that the radial sliding bearing comprises a radial sliding support pad and a radial sliding bearing casing, and the contact surface of the radial sliding support pad and the shaft is provided with a radial sliding oil film.
The invention also provides a gas turbine rotor support system based on a sliding bearing and a thrust disk, which is characterized in that the radial sliding bearing casing is provided with a squirrel cage elastic support.
Advantageous effects
The gas turbine rotor supporting system based on the sliding bearing and the thrust disc provided by the invention is based on the sliding bearing and the thrust disc, all the fulcrum positions adopt the sliding bearings, the advantages of the sliding bearings are fully exerted, and the gas turbine rotor supporting system has the advantages of strong bearing capacity, high radial positioning precision, good impact resistance, good rotation stability and small friction power consumption.
The radial sliding bearing used in the invention has small radial thickness dimension and has the advantages of compact structure and space saving; meanwhile, the bearing casing has the structural characteristic of a squirrel-cage elastic support and has the advantage of inhibiting vibration.
The radial thrust sliding bearing and the thrust sliding bearing are positioned on one side of the bearing frame and are connected into a whole through the bearing support legs, so that the thrust disc is clamped from two sides, and the radial thrust sliding bearing and the thrust sliding bearing have the advantages of compact layout and convenience for centralized sharing design of oil and gas paths.
The bearing support leg provided by the invention has the advantages that two bearings (the thrust sliding bearing and the radial thrust sliding bearing) are connected to the force bearing frame together, and the bearing support leg has the advantages of compact layout, solid structure and convenience in installation.
Drawings
In order to more clearly illustrate the technical solution of the embodiment of the present invention, the drawings required to be used in the embodiment will be briefly described below, and it is obvious that the drawings in the following description are only one implementation means of the present invention and do not represent actual physical appearance, and for those skilled in the art, other drawings can be obtained by changing according to the needs of actual situations without creative efforts.
FIG. 1 is a schematic structural view of a sliding bearing and thrust disk based gas turbine rotor support system provided by the present invention;
FIG. 2 is a schematic view of the circumferential distribution of bearing legs in a sliding bearing and thrust disk based gas turbine rotor support system provided by the present invention.
Wherein: 1: a shaft; 2: a thrust disc; 3: a radial thrust sliding bearing; 3.1: a radial thrust pad; 3.2: radially supporting the pad; 3.3: a radial thrust sliding bearing cartridge; 4: a bearing leg; 5: a thrust sliding bearing; 5.1: a thrust sliding bearing housing; 5.2: a thrust shoe; 6: a force bearing frame; 7: a radial sliding bearing; 7.1: radially sliding the support pad; 7.2: a radial plain bearing cartridge; a: a first radial support position; b: a second radial support position; c: a first axial support position; d: a second axial support position.
Detailed Description
In order to make the technical means, the original characteristics, the achieved objects and the effects of the present invention easily understood, the following embodiments are provided to describe the gas turbine rotor support system based on the sliding bearing and the thrust disk in detail with reference to the attached drawings.
In the description of the embodiments of the present invention, it should be understood that the terms "center", "span", "chord", "up", "down", "left", "right", "left end", "right end", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the drawings, and are only used for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.
The terms "mounted," "connected," and "coupled" are to be construed broadly and may, for example, be fixedly coupled, detachably coupled, or integrally coupled; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. Furthermore, the terms "distributed," "arranged," "secured," "disposed," and the like are to be construed conceptually as referring to some specific combination or processing technique, and merely as a prelude to the more detailed description of the structure. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.
As illustrated in fig. 1-2, a sliding bearing and thrust disk based gas turbine rotor support system is provided for the present invention. The braced system includes axle 1, sets up thrust disc 2 and three slide bearing in axle 1 one end, wherein, three slide bearing includes journal bearing 7, journal bearing 3 and thrust slide bearing 5 set up the one end at axle 1, connect through bearing leg 4 between journal bearing 3 and the thrust slide bearing 5, journal bearing 7 sets up the other end at axle 1 to through bearing frame 6 with bearing leg 4 is connected.
In the above embodiment, the bearing support leg 4 connects the two bearings (the thrust sliding bearing 5 and the radial thrust sliding bearing 3) to the bearing frame 6, and has the advantages of reasonable and compact layout, strong bearing capacity, high radial positioning precision, good impact resistance, good rotational stability and low friction power consumption.
In some embodiments, the journal bearing 3 and the thrust bearing 5 are disposed on both sides of the thrust disk 2, respectively. The thrust disc 2 is clamped by the radial thrust sliding bearing 3 and the thrust sliding bearing 5 from two sides, and the thrust disc has the advantages of compact layout and convenience for oil-gas path concentration.
In some embodiments, the radial thrust sliding bearing 3 comprises a radial support pad 3.2, a radial thrust pad 3.1 and a radial thrust bearing housing 3.3, a radial thrust oil film is arranged between the radial support pad 3.2 and the shaft 1, and the radial thrust pad 3.1 is close to the thrust disc 2. In this embodiment, the radial-thrust sliding bearing 3 has both radial and axial thrust functions, the radial-thrust pad 3.2 and the shaft 1 form a first radial-thrust position a at the contact surface via a radial-thrust oil film, and the contact surface of the radial-thrust pad 3.1 and the thrust disk 2 forms a first axial-thrust position C, which is the main thrust fulcrum that bears most of the axial thrust.
In some embodiments, the thrust sliding bearing 5 comprises a thrust sliding bearing casing 5.1 and a thrust pad 5.2, the thrust pad 5.2 being adjacent to the thrust disk 2. The contact surface of the thrust pad 5.2 and the relay disc 2 forms a second axial support position D, which is a secondary thrust fulcrum bearing a small amount of reverse thrust.
In some embodiments, the radial plain bearing 7 comprises a radial sliding support pad 7.1 and a radial plain bearing cartridge 7.2, and the contact surface of the radial sliding support pad 7.1 and the shaft 1 is provided with a radial sliding oil film. The contact surface of the radial sliding support pad 7.1 and the shaft 1 forms a second radial support position B, and the radial thickness of the included radial sliding support pad is smaller, so that the radial sliding support pad has the advantages of compact structure and space saving. The radial sliding bearing casing is provided with a squirrel-cage elastic support. The squirrel-cage elastic support plays a role in inhibiting vibration.
As shown in fig. 2, in this embodiment, the number of the bearing legs 4 is 4. The 4 bearing support legs 4 are circumferentially and uniformly distributed according to an initial angle of 45 degrees and an interval angle of 90 degrees. The end of the bearing leg 4 is provided with a flange for connection with the plain radial thrust bearing 3 and the plain thrust bearing 5, which is connected with the plain radial thrust bearing 3 and the plain thrust bearing 5 by bolts. The flange is connected to a radial thrust slide bearing housing 3.3 on the radial thrust slide bearing 3 and to a thrust slide bearing housing 5.1 on the thrust slide bearing 5.
In conclusion, the gas turbine rotor supporting system based on the sliding bearing and the thrust disc provided by the invention has two radial bearings and two axial bearing points, has a better supporting effect, and has the characteristics of reasonable and compact layout, strong bearing capacity, high radial positioning precision, good impact resistance, good rotation stability and small friction power consumption.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention. The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (9)
1. The utility model provides a gas turbine rotor braced system based on slide bearing and thrust disc which characterized in that, braced system includes the axle, sets up thrust disc and three slide bearing in axle one end, wherein, three slide bearing includes journal bearing, radial thrust slide bearing and thrust slide bearing, journal bearing and thrust slide bearing set up the one end at the axle, connect through the bearing landing leg between journal bearing and the thrust slide bearing, journal bearing sets up the other end at the axle to through the bearing frame with the bearing landing leg is connected.
2. A sliding bearing and thrust disk based gas turbine rotor support system in accordance with claim 1, wherein said journal and thrust bearing are disposed on either side of said thrust disk.
3. A gas turbine rotor support system based on a sliding bearing and a thrust disc according to claim 1, characterised in that the radial thrust sliding bearing comprises radial support pads, radial thrust pads and a radial thrust bearing casing, a radial thrust oil film being provided between the radial support pads and the shaft, the radial thrust pads being close to the thrust disc.
4. The sliding bearing and thrust disk based gas turbine rotor support system of claim 1, wherein the thrust sliding bearing includes a thrust sliding bearing casing and a thrust pad, the thrust pad being proximate the thrust disk.
5. The sliding bearing and thrust disk based gas turbine rotor support system of claim 1, wherein said bearing leg is at least one.
6. The sliding bearing and thrust disk based gas turbine rotor support system of claim 5, wherein when said bearing legs are two or more, a plurality of bearing legs are circumferentially equispaced at a starting angle of 45 ° and a spacing angle of 90 °.
7. A gas turbine rotor support system based on a slide bearing and a thrust disc according to claim 6, characterised in that the ends of the bearing legs are provided with flanges for connection with the radial thrust slide bearing and the thrust slide bearing, which flanges are connected with the radial thrust slide bearing and the thrust slide bearing by means of bolts.
8. A gas turbine rotor support system based on a plain bearing and a thrust disc according to claim 1, characterised in that the radial plain bearing comprises a radial sliding support pad and a radial plain bearing cartridge, the contact surface of the radial sliding support pad and the shaft being provided with a radial sliding oil film.
9. A sliding bearing and thrust disk based gas turbine rotor support system in accordance with claim 8 wherein said radial sliding bearing cartridge has a squirrel cage elastomeric bearing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110982630.3A CN113700732B (en) | 2021-08-25 | 2021-08-25 | Gas turbine rotor supporting system based on sliding bearing and thrust disc |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110982630.3A CN113700732B (en) | 2021-08-25 | 2021-08-25 | Gas turbine rotor supporting system based on sliding bearing and thrust disc |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113700732A true CN113700732A (en) | 2021-11-26 |
| CN113700732B CN113700732B (en) | 2023-09-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110982630.3A Active CN113700732B (en) | 2021-08-25 | 2021-08-25 | Gas turbine rotor supporting system based on sliding bearing and thrust disc |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117189791A (en) * | 2023-11-07 | 2023-12-08 | 成都中科翼能科技有限公司 | Power turbine bearing casing assembly with sensor |
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| Publication number | Publication date |
|---|---|
| CN113700732B (en) | 2023-09-05 |
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