CN113700732B - Gas turbine rotor supporting system based on sliding bearing and thrust disc - Google Patents
Gas turbine rotor supporting system based on sliding bearing and thrust disc Download PDFInfo
- Publication number
- CN113700732B CN113700732B CN202110982630.3A CN202110982630A CN113700732B CN 113700732 B CN113700732 B CN 113700732B CN 202110982630 A CN202110982630 A CN 202110982630A CN 113700732 B CN113700732 B CN 113700732B
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- Prior art keywords
- thrust
- radial
- bearing
- sliding bearing
- sliding
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Classifications
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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 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 bearing support legs, and the radial sliding bearing is arranged at the other end of the shaft and is connected with the bearing support legs 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, and all fulcrum positions are all provided with the sliding bearing, so that the advantages of the sliding bearing are fully exerted, and the gas turbine rotor supporting system based on the sliding bearing and the thrust disc has the advantages of strong bearing capacity, high radial positioning precision, good shock 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, and the power turbine is an important component for power output of the gas turbine, and the power turbine bears huge axial force due to gradual expansion of the gas in the turbine. The power turbine is used as a large-size working part, and the working environment of a large-size rotor system is loaded with heavy load, large in impact and large in vibration, so that the supporting part is easy to damage, and the reliable operation of the part is influenced.
In the prior art, in a support layout of a rotary machine, it is generally supported on the basis of a rolling bearing. However, the rolling bearing cannot accommodate environments with heavy loads, large impacts, and long service life requirements, thereby affecting the operation stability of the rotor system or leading to frequent maintenance and replacement. The operation safety of the components is reduced, and the operation and maintenance cost is increased.
Accordingly, there is a need to provide a support system adapted to a gas turbine rotor to address the above-mentioned problems.
Disclosure of Invention
In order to solve the problems, the invention provides a gas turbine rotor support system based on a sliding bearing and a thrust disc, the support system 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 bearing supporting legs, and the radial sliding bearing is arranged at the other end of the shaft and is connected with the bearing supporting legs through a bearing frame.
The gas turbine rotor support system based on the sliding bearing and the thrust disk provided by the invention is also characterized in that the radial thrust sliding bearing and the thrust sliding bearing are respectively arranged at two sides of the thrust disk.
The gas turbine rotor supporting system based on the sliding bearing and the thrust disc is characterized in that the radial thrust sliding bearing comprises a radial supporting shoe, a radial thrust shoe and a radial thrust bearing casing, a radial thrust oil film is arranged between the radial supporting shoe and the shaft, and the radial thrust shoe is close to the thrust disc.
The gas turbine rotor support system based on a slide bearing and a thrust disc provided by the invention also has the feature that the thrust slide bearing comprises a thrust slide bearing casing and a thrust shoe, the thrust shoe being adjacent to the thrust disc.
The gas turbine rotor support system based on the sliding bearing and the thrust disk provided by the invention also has the characteristic that at least one bearing support leg is arranged.
The gas turbine rotor supporting system based on the sliding bearing and the thrust disc is characterized in that when two or more bearing supporting legs are provided, the plurality of bearing supporting legs are circumferentially and uniformly distributed according to an initial angle of 45 degrees and an interval angle of 90 degrees.
The gas turbine rotor support system based on the sliding bearing and the thrust disc is characterized in that the end parts of the bearing support legs are provided with flanges used for being connected with the radial thrust sliding bearing and the thrust sliding bearing, and the flanges are connected with the radial thrust sliding bearing and the thrust sliding bearing through bolts.
The gas turbine rotor support system based on the sliding bearing and the thrust disc is characterized in that the radial sliding bearing comprises a radial sliding support pad and a radial sliding bearing casing, and a radial sliding oil film is arranged on the contact surface of the radial sliding support pad and the shaft.
The gas turbine rotor support system based on the sliding bearing and the thrust disk provided by the invention is also 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, and all fulcrum positions are all provided with the sliding bearing, so that the advantages of the sliding bearing are fully exerted, and the gas turbine rotor supporting system based on the sliding bearing and the thrust disc has the advantages of strong bearing capacity, high radial positioning precision, good shock resistance, good rotation stability and small friction power consumption.
The radial sliding bearing used by the invention has small radial thickness dimension and has the advantages of compact structure and space saving; meanwhile, the bearing casing has the structural characteristics of a squirrel-cage elastic support, and has the advantage of vibration inhibition.
The radial thrust sliding bearing and the thrust sliding bearing used by the invention are both 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 in centralized sharing design of oil gas paths.
The bearing support leg provided by the invention has the advantages of compact layout, solid structure and convenience in installation, and two bearings (the thrust sliding bearing and the radial thrust sliding bearing) are connected on the bearing frame together.
Drawings
In order to more clearly illustrate the technical solution of the embodiments of the present invention, the drawings required in the embodiments 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 the actual physical shape, and it is possible for those skilled in the art to obtain other drawings according to the actual situation without any inventive effort.
FIG. 1 is a schematic view of a gas turbine rotor support system based on a plain bearing and thrust disk provided by the present invention;
FIG. 2 is a schematic view of the circumferential distribution of bearing legs in a gas turbine rotor support system based on a plain bearing and thrust disk provided by the present invention.
Wherein: 1: a shaft; 2: a thrust plate; 3: radial thrust sliding bearings; 3.1: radial thrust blocks; 3.2: radial support pads; 3.3: radial thrust sliding bearing casing; 4: a bearing leg; 5: thrust sliding bearings; 5.1: thrust sliding bearing casing; 5.2: thrust blocks; 6: a force-bearing frame; 7: a radial sliding bearing; 7.1: a radial sliding support shoe; 7.2: a radial slide bearing casing; a: a first radial support position; b: a second radial support position; c: a first axial support position; d: and a second axial support position.
Detailed Description
In order to make the technical means, creation characteristics, achievement of the purposes and effects achieved by the present invention easy to understand, the following embodiments are specifically described with reference to the accompanying drawings for a gas turbine rotor support system based on a sliding bearing and a thrust disk.
In describing embodiments of the present invention, it should be understood that the terms "center," "spanwise," "chordwise," "upper," "lower," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship described in the drawings, merely to facilitate description of the invention and to simplify description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be configured and operated in a particular orientation, and thus should not be construed as limiting the 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 a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may explicitly or implicitly include one or more such feature. In the description of the invention, unless otherwise indicated, the meaning of "a plurality" is two or more.
The terms "mounted," "connected," "coupled," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. Furthermore, the terms "distributed," "arranged," "secured," "disposed," and the like are to be construed as conceptual, and do not refer to a particular bonding or processing technique, but rather emphasize a state 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 in a specific case.
As shown in fig. 1-2, the gas turbine rotor support system based on the sliding bearing and the thrust disk is provided by the invention. The support system comprises a shaft 1, a thrust disc 2 and three sliding bearings, wherein the thrust disc 2 is arranged at one end of the shaft 1, the three sliding bearings comprise a radial sliding bearing 7, a radial thrust sliding bearing 3 and a thrust sliding bearing 5, the radial thrust sliding bearing 3 and the thrust sliding bearing 5 are arranged at one end of the shaft 1, the radial thrust sliding bearing 3 and the thrust sliding bearing 5 are connected through a bearing supporting leg 4, and the radial sliding bearing 7 is arranged at the other end of the shaft 1 and is connected with the bearing supporting leg 4 through a bearing frame 6.
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) together on the bearing frame 6, and has the advantages of reasonable and compact layout, strong bearing capacity, high radial positioning precision, good shock resistance, good rotation stability and small friction power consumption.
In some embodiments, the radial thrust sliding bearing 3 and the thrust sliding 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 radial thrust sliding bearing has the advantages of compact layout and convenience in 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 casing 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 the functions of both a radial bearing and an axial thrust, the radial support pad 3.2 and the shaft 1 form a first radial support position a at the contact surface through a radial thrust oil film, and the contact surface of the radial thrust pad 3.1 and the thrust disc 2 forms a first axial support position C, and the first axial support position C is a main thrust supporting point bearing most of the axial thrust.
In some embodiments, the thrust sliding bearing 5 comprises a thrust sliding bearing housing 5.1 and a thrust pad 5.2, the thrust pad 5.2 being adjacent to the thrust disc 2. The contact surface of the thrust pads 5.2 with the relay disc 2 forms a second axial supporting position D, which is a secondary thrust fulcrum bearing a small amount of reverse thrust.
In some embodiments, the radial slide bearing 7 comprises a radial slide support pad 7.1 and a radial slide bearing housing 7.2, the contact surface of the radial slide support pad 7.1 and the shaft 1 being provided with a radial slide oil film. The contact surface of the radial sliding support shoe 7.1 and the shaft 1 forms a second radial support position B, and the radial sliding support shoe contained therein has a smaller radial thickness, which has the advantage 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.
In this embodiment, as shown in fig. 2, the number of bearing legs 4 is 4. The 4 bearing legs 4 are circumferentially and uniformly distributed according to an initial angle of 45 degrees and an interval angle of 90 degrees. The ends of the bearing legs 4 are provided with flanges for connection with the radial thrust sliding bearing 3 and the thrust sliding bearing 5, which flanges are connected with the radial thrust sliding bearing 3 and the thrust sliding bearing 5 by bolts. The flange is connected to a radial thrust bearing housing 3.3 on the radial thrust bearing 3 and to a thrust bearing housing 5.1 on the thrust bearing 5.
In summary, 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 shock resistance, good rotation stability and small friction power consumption.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention. The foregoing is merely a preferred embodiment of the present invention, and it should be noted that it will be apparent to those skilled in the art that modifications and variations can be made without departing from the technical principles of the present invention, and these modifications and variations should also be regarded as the scope of the invention.
Claims (7)
1. A gas turbine rotor support system based on a sliding bearing and a thrust disc is characterized in that the support system 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 bearing support legs, the radial sliding bearing is arranged at the other end of the shaft and connected with the bearing support legs through a bearing frame,
the radial sliding bearing comprises a radial sliding support pad and a radial sliding bearing casing, the contact surface of the radial sliding support pad and the shaft is provided with a radial sliding oil film,
the radial sliding bearing casing is provided with a squirrel-cage elastic support.
2. The gas turbine rotor support system based on slide bearings and thrust discs of claim 1, wherein the radial thrust slide bearings and thrust slide bearings are disposed on either side of the thrust discs, respectively.
3. The gas turbine rotor support system of claim 1, wherein the radial thrust sliding bearing comprises a radial support pad, a radial thrust pad, and a radial thrust bearing cartridge, a radial thrust oil film being disposed between the radial support pad and the shaft, the radial thrust pad being proximate the thrust disk.
4. The gas turbine rotor support system of claim 1, wherein the thrust slide bearing comprises a thrust slide bearing case and a thrust shoe, the thrust shoe being proximate the thrust disk.
5. The gas turbine rotor support system based on a plain bearing and thrust disk of claim 1, wherein the bearing legs are at least one.
6. The gas turbine rotor support system based on a sliding bearing and a thrust disk according to claim 5, wherein when the number of the bearing legs is two or more, the plurality of bearing legs are circumferentially distributed at an initial angle of 45 ° and a spacing angle of 90 °.
7. The gas turbine rotor support system based on slide bearings and thrust discs of claim 6, wherein the ends of the bearing legs are provided with flanges for connection with the radial thrust slide bearings and the thrust slide bearings, the flanges being connected with the radial thrust slide bearings and the thrust slide bearings by bolts.
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 |
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| Publication Number | Publication Date |
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| CN113700732A CN113700732A (en) | 2021-11-26 |
| CN113700732B true 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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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117189791B (en) * | 2023-11-07 | 2024-01-23 | 成都中科翼能科技有限公司 | Power turbine bearing casing assembly with sensor |
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| CN113700732A (en) | 2021-11-26 |
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