CN106695656A - Bearing pad replacement method of heavy gas turbine - Google Patents
Bearing pad replacement method of heavy gas turbine Download PDFInfo
- Publication number
- CN106695656A CN106695656A CN201611035392.0A CN201611035392A CN106695656A CN 106695656 A CN106695656 A CN 106695656A CN 201611035392 A CN201611035392 A CN 201611035392A CN 106695656 A CN106695656 A CN 106695656A
- Authority
- CN
- China
- Prior art keywords
- support shaft
- rotor
- thrust
- bearing
- thrust nozzle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a bearing pad replacement method of a heavy gas turbine. The bearing pad replacement method comprises the following steps: a set of auxiliary decomposition tools is prepared; a pipeline, a coupling, a sealing cover, a front end cover, a secondary thrust nozzle, a secondary thrust tile and a thrust disc are decomposed in sequence; the secondary thrust tile is replaced; a support shaft is mounted on a rotor; a hollow guide shaft and a guide base are mounted; the support shaft and the rotor are lifted onto a support shaft bracket to guarantee uniform gap between a radial tile and the rotor; a support shaft gland is mounted; the guide base is fixedly connected with a thrust bearing base; a radial bearing base and a support shell are in detachable connection; the guide base is pulled, so that a main thrust nozzle is positioned rightly above a main thrust nozzle through hole; the main thrust nozzle is decomposed, and falls down through the main thrust nozzle through hole to butt against the support shaft; a main thrust tile is replaced; mounting persons enter the support shell; a fan-shaped plate is fixedly mounted on the support shell; a back end cover is decomposed, and is fixedly connected to the fan-shaped plate; the radial tile is replaced; and all the decomposed parts are refitted in sequence.
Description
Technical field
The invention belongs to heavy duty gas turbine maintenance technique field, more particularly to a kind of bearing shell of heavy duty gas turbine is more
Change method.
Background technology
For heavy duty gas turbine, its compact conformation, and gas turbine cylinder be level to opening structure, bearing is located at
Inside gas turbine, when needing to change bearing shell, currently used bearing shell substitute mode is：Remove outside gas turbine first
Each integrated system, then gas turbine is shifted, the upper half cylinder of lower cylinder is then decomposed, then hang out rotor, then by axle
Hold under being decomposed from rotor, finally carry out bearing shell replacing, after bearing shell is changed to be finished, then by the parts under all decomposition by suitable
Sequence is reinstalled successively.
Currently used bearing shell substitute mode, the decomposition of gas turbine parts and assembly period are long, and this is for combustion
The outfield operation maintenance of gas-turbine is very unfavorable.Therefore, a kind of brand-new bearing shell replacing options of searching are needed badly, it should possess effectively
Shorten gas turbine parts decompose and assembly period ability, and be conducive to the gas turbine to carry out outfield operation maintenance.
The content of the invention
For the problem that prior art is present, the present invention provides a kind of bearing shell replacing options of heavy duty gas turbine, can
Effectively shorten gas turbine parts to decompose and assembly period, and be conducive to the gas turbine to carry out outfield operation maintenance.
To achieve these goals, the present invention is adopted the following technical scheme that：A kind of bearing shell replacing side of heavy duty gas turbine
Method, comprises the following steps：
Step one：Prepare a set of auxiliary disassembling tool, auxiliary disassembling tool include support shaft, hollow leading axle, guide seat,
Support shaft stool, support shaft gland and fanning strip, offer main thrust nozzle by hole on the tube wall of hollow leading axle, are drawing
Main thrust nozzle decomposition window is offered on guide bracket；
Step 2：Pipeline, shaft coupling and closure are decomposed successively under；
Step 3：Under successively decomposing drive end bearing bracket, secondary thrust nozzle, secondary thrust bearing shoe valve and thrust disc, secondary thrust is then changed
Watt；
Step 4：Support shaft is fixedly installed on rotor, hollow leading axle fixed cover is then attached to support shaft and is turned
On son, then guide seat is installed on hollow leading axle；
Step 5：The related rotor of support shaft is together sling, then is installed on support shaft stool, it is ensured that radial direction watt and rotor
Between gap uniformity, then install support shaft gland, support shaft be fixed on support shaft stool and support shaft gland between, this
When support shaft replace radially watt being supported rotor；
Step 6：Guide seat is moved along hollow leading axle, guide seat is fixedly connected with thrust shaft block；
Step 7：Radial axle bearing is disengaged with support housing and is connected, pull out guide seat, make thrust shaft block and footpath
Together it is displaced outwardly to bearing block, until the main thrust nozzle that main thrust nozzle is positioned exactly on hollow leading axle is just gone up by hole
Side；
Step 8：Main thrust nozzle is decomposed with window through the main thrust nozzle decomposition in guide seat, under decomposition
Main thrust nozzle fallen by hole by the main thrust nozzle on hollow leading axle and to being placed in support shaft, then more change owner
Thrust bearing shoe valve；
Step 9：Installation personnel enters support enclosure interior by the space between radial axle bearing and support housing, will
Fanning strip is packed on support housing, is then decomposed down rear end cap, then the rear end cap under decomposing is fixedly attached into fanning strip
On, then change radial direction watt；
Step 10：Parts under all decomposition are returned into dress successively in order.
In step 5, when gap of the radial direction watt and rotor between is uneven, increase by below support shaft stool
Adjust pad, and then the height of support shaft stool is adjusted, untill gap uniformity of the radial direction watt and rotor between.
Beneficial effects of the present invention：
The present invention compared with prior art, can not remove outside gas turbine each integrated system and not decomposition gas cylinder
Under conditions of realize bearing shell change, can effectively shorten gas turbine parts decompose and assembly period, through actual measuring and calculating, combustion gas
Turbine parts are decomposed and assembly period shortens about 3/4, and then are more beneficial for gas turbine and are carried out outfield operation maintenance.
Brief description of the drawings
Fig. 1 is the gas turbine schematic diagram under the undecomposed state of parts；
Fig. 2 is the gas turbine schematic diagram under pipeline, shaft coupling and closure are decomposed；
Fig. 3 is the gas turbine schematic diagram under end cap, secondary thrust nozzle and secondary thrust bearing shoe valve are decomposed；
Fig. 4 is the gas turbine schematic diagram after support shaft, hollow leading axle and guide seat are installed；
Fig. 5 is the gas turbine schematic diagram after supporting shaft stool and support shaft gland to install；
Fig. 6 is the gas turbine schematic diagram after guide seat is connected with thrust shaft block；
Fig. 7 is that radial axle bearing disengages the gas turbine schematic diagram after being connected with support housing；
Fig. 8 is for rear end cap is decomposed down and is affixed to the gas turbine schematic diagram after fanning strip；
In figure, 1-support shaft, 2-hollow leading axle, 3-guide seat, 4-support shaft stool, 5-support shaft gland,
6-main thrust nozzle by hole, 7-pipeline, 8-shaft coupling, 9-closure, 10-drive end bearing bracket, 11-secondary thrust nozzle,
12-secondary thrust bearing shoe valve, 13-rotor, 14-radial direction watt, 15-thrust shaft block, 16-radial axle bearing, 17-support housing,
18-main thrust nozzle, 19-main thrust watt, 20-fanning strip, 21-main thrust nozzle decomposition window, 22-rear end cap,
23-adjust pad, 24-cylinder, 25-thrust disc.
Specific embodiment
The present invention is described in further detail with specific embodiment below in conjunction with the accompanying drawings.
In the present embodiment, the rotor 13 of gas turbine is supported by two groups of journal bearings, is carried out by one group of thrust bearing
Axially position, two groups of journal bearing structures are identical, it is necessary to the bearing shell changed includes secondary thrust bearing shoe valve 12, main thrust watt 19 and radial direction watt
14, its inside for being respectively positioned on gas turbine, in order to shorten, gas turbine parts are decomposed and assembly period is not, it is necessary to remove combustion
The gas-turbine each integrated system in outside and not under conditions of decomposition gas cylinder 24, realizes the replacing of bearing shell.
A kind of bearing shell replacing options of heavy duty gas turbine, comprise the following steps：
Step one：Prepare a set of auxiliary disassembling tool, auxiliary disassembling tool includes support shaft 1, hollow leading axle 2, guiding
Seat 3, support shaft stool 4, support shaft gland 5 and fanning strip 20, main thrust nozzle are offered on the tube wall of hollow leading axle 2 and are led to
Via 6, offers main thrust nozzle decomposition window 21 in guide seat 3；
Step 2：Pipeline 7, shaft coupling 8 and closure 9 are decomposed down successively, as shown in figure 1, such as Fig. 2 after decomposing before decomposing
It is shown；
Step 3：Drive end bearing bracket 10, secondary thrust nozzle 11, secondary thrust bearing shoe valve 12 and thrust disc 25 are decomposed down successively, such as Fig. 3 institutes
Show, then change secondary thrust bearing shoe valve 12；
Step 4：Support shaft 1 is fixedly installed on rotor 13, the fixed cover of hollow leading axle 2 is then attached to support shaft 1
And on rotor 13, the matching surface of rotor 13 and screw thread etc. can also be protected by hollow leading axle 2, then by guide seat
3 are installed on hollow leading axle 2, as shown in Figure 4；
Step 5：The related rotor 13 of support shaft 1 is together sling using crane, then is installed on support shaft stool 4, it is ensured that
Gap uniformity of the radial direction watt between 14 and rotor 13, then installs support shaft gland 5, and support shaft 1 is fixed on support shaft stool 4
Between support shaft gland 5, now support shaft 1 replaces radially watt 14 pairs of rotors 13 to be supported, as shown in Figure 5；
Step 6：Guide seat 3 is moved along hollow leading axle 2, guide seat 3 is fixedly connected with thrust shaft block 15, such as
Shown in Fig. 6, guide seat 3 can also avoid radial direction watt 14 and rotor when thrust shaft block 15 is guided and radial axle bearing 16 is moved
13 collide with friction；
Step 7：Radial axle bearing 16 is disengaged with support housing 17 and is connected, pull out guide seat 3, make thrust bearing
Seat 15 and radial axle bearing 16 are together displaced outwardly, until main thrust nozzle 18 is positioned exactly at the main thrust on hollow leading axle 2
Nozzle passes through directly over hole 6, as shown in Figure 7；
Step 8：Main thrust nozzle 18 is decomposed with window 21 through the main thrust nozzle decomposition in guide seat 3, point
The main thrust nozzle 18 taken off is fallen and by hole 6 by the main thrust nozzle on hollow leading axle 2 to being placed in support shaft 1,
Then main thrust watt 19 is changed；
Step 9：Installation personnel is entered in support housing 17 by the space between radial axle bearing 16 and support housing 17
Portion, fanning strip 20 is packed on support housing 17, is then decomposed down rear end cap 22, then the rear end cap 22 under decomposing is fixed
It is connected on fanning strip 20, as shown in figure 8, then changing radial direction watt 14；
Step 10：Parts under all decomposition are returned into dress successively in order.
In step 5, when gap of the radial direction watt between 14 and rotor 13 is uneven, by below support shaft stool 4
Increase adjust pad 23, and then adjust the height for supporting shaft stool 4, until gap uniformity of the radial direction watt between 14 and rotor 13 is
Only.
Scheme in embodiment and being not used to limits scope of patent protection of the invention, it is all without departing from carried out by the present invention etc.
Effect is implemented or is changed, and is both contained in the scope of the claims of this case.
Claims (2)
1. bearing shell replacing options of a kind of heavy duty gas turbine, it is characterised in that comprise the following steps：
Step one：Prepare a set of auxiliary disassembling tool, auxiliary disassembling tool includes support shaft, hollow leading axle, guide seat, support
Shaft stool, support shaft gland and fanning strip, offer main thrust nozzle by hole, in guide seat on the tube wall of hollow leading axle
On offer main thrust nozzle decomposition window；
Step 2：Pipeline, shaft coupling and closure are decomposed successively under；
Step 3：Under successively decomposing drive end bearing bracket, secondary thrust nozzle, secondary thrust bearing shoe valve and thrust disc, secondary thrust bearing shoe valve is then changed；
Step 4：Support shaft is fixedly installed on rotor, then hollow leading axle fixed cover is attached on support shaft and rotor,
Guide seat is installed on hollow leading axle again；
Step 5：The related rotor of support shaft is together sling, then is installed on support shaft stool, it is ensured that radial direction watt is and rotor between
Gap uniformity, then install support shaft gland, support shaft be fixed on support shaft stool and support shaft gland between, now prop up
Support axle replaces radial direction watt to be supported rotor；
Step 6：Guide seat is moved along hollow leading axle, guide seat is fixedly connected with thrust shaft block；
Step 7：Radial axle bearing is disengaged with support housing and is connected, pull out guide seat, make thrust shaft block and radial axle
Bearing is together displaced outwardly, until main thrust nozzle is positioned exactly at main thrust nozzle on hollow leading axle by directly over hole；
Step 8：Main thrust nozzle is decomposed with window through the main thrust nozzle decomposition in guide seat, the master under decomposing
Thrust nozzle is fallen by hole by the main thrust nozzle on hollow leading axle and to being placed in support shaft, then changes main thrust
Watt；
Step 9：Installation personnel enters support enclosure interior by the space between radial axle bearing and support housing, by sector
Plate is packed on support housing, is then decomposed down rear end cap, then the rear end cap under decomposing is fixedly attached on fanning strip, so
Radial direction watt is changed afterwards；
Step 10：Parts under all decomposition are returned into dress successively in order.
2. bearing shell replacing options of a kind of heavy duty gas turbine according to claim 1, it is characterised in that：In step 5
In, when gap of the radial direction watt and rotor between is uneven, by increasing adjust pad below support shaft stool, and then adjust
The height of shaft stool is supported, untill gap uniformity of the radial direction watt and rotor between.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611035392.0A CN106695656B (en) | 2016-11-22 | 2016-11-22 | A kind of bearing shell replacing options of heavy duty gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611035392.0A CN106695656B (en) | 2016-11-22 | 2016-11-22 | A kind of bearing shell replacing options of heavy duty gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106695656A true CN106695656A (en) | 2017-05-24 |
| CN106695656B CN106695656B (en) | 2018-05-08 |
Family
ID=58940214
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611035392.0A Active CN106695656B (en) | 2016-11-22 | 2016-11-22 | A kind of bearing shell replacing options of heavy duty gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106695656B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107717859A (en) * | 2017-11-27 | 2018-02-23 | 国家电网公司 | Below bearing type generator thrust bearing bearing shell dismantling device and assembly and disassembly methods |
| CN108223568A (en) * | 2018-03-06 | 2018-06-29 | 哈尔滨广瀚燃气轮机有限公司 | A kind of gas turbine long-life composite bearing |
| CN109570898A (en) * | 2018-09-21 | 2019-04-05 | 大连德宇机械有限公司 | Closed-smelting machine rotor brasses replacing options |
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| CN2336928Y (en) * | 1998-08-29 | 1999-09-08 | 林永森 | Mounting and dismounting device for axle bush |
| DE20214363U1 (en) * | 2002-09-16 | 2002-11-21 | Klann Tools Ltd., Oxfordshire | Device for pulling out and pressing in bearing bushes, roller bearings and the like. |
| CN200995392Y (en) * | 2007-01-15 | 2007-12-26 | 江苏江淮动力股份有限公司 | Tool for assembling cylinder jacket of engine |
| CN201038931Y (en) * | 2007-05-22 | 2008-03-19 | 上海宝钢设备检修有限公司 | Large motor axis tile pulling and drawing structure |
| CN102284925A (en) * | 2011-08-17 | 2011-12-21 | 广东核电合营有限公司 | Tool and method for replacing shaft bushing at big end of connecting rod of diesel engine of million-kilowatt-class nuclear power plant |
| CN103481055A (en) * | 2013-07-30 | 2014-01-01 | 中国海洋石油总公司 | Disassembling and assembling technology for large diesel engine crankshaft bearing bush |
| CN203390492U (en) * | 2013-07-30 | 2014-01-15 | 中国海洋石油总公司 | Suspension supporting platform for detaching and installing large-scale diesel engine crankshaft bearing |
| CN205423292U (en) * | 2016-03-15 | 2016-08-03 | 山东钢铁股份有限公司 | Can simply change shaft seal structure of axle bush water pump |
| CN205572315U (en) * | 2016-05-10 | 2016-09-14 | 中国石油集团济柴动力总厂 | Engine cam axle bush mounting tool |
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2016
- 2016-11-22 CN CN201611035392.0A patent/CN106695656B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU929386A2 (en) * | 1980-10-10 | 1982-05-23 | Краматорский Завод "Энергомашспецсталь" | Hydraulic faceplate |
| CN2336928Y (en) * | 1998-08-29 | 1999-09-08 | 林永森 | Mounting and dismounting device for axle bush |
| DE20214363U1 (en) * | 2002-09-16 | 2002-11-21 | Klann Tools Ltd., Oxfordshire | Device for pulling out and pressing in bearing bushes, roller bearings and the like. |
| CN200995392Y (en) * | 2007-01-15 | 2007-12-26 | 江苏江淮动力股份有限公司 | Tool for assembling cylinder jacket of engine |
| CN201038931Y (en) * | 2007-05-22 | 2008-03-19 | 上海宝钢设备检修有限公司 | Large motor axis tile pulling and drawing structure |
| CN102284925A (en) * | 2011-08-17 | 2011-12-21 | 广东核电合营有限公司 | Tool and method for replacing shaft bushing at big end of connecting rod of diesel engine of million-kilowatt-class nuclear power plant |
| CN103481055A (en) * | 2013-07-30 | 2014-01-01 | 中国海洋石油总公司 | Disassembling and assembling technology for large diesel engine crankshaft bearing bush |
| CN203390492U (en) * | 2013-07-30 | 2014-01-15 | 中国海洋石油总公司 | Suspension supporting platform for detaching and installing large-scale diesel engine crankshaft bearing |
| CN205423292U (en) * | 2016-03-15 | 2016-08-03 | 山东钢铁股份有限公司 | Can simply change shaft seal structure of axle bush water pump |
| CN205572315U (en) * | 2016-05-10 | 2016-09-14 | 中国石油集团济柴动力总厂 | Engine cam axle bush mounting tool |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107717859A (en) * | 2017-11-27 | 2018-02-23 | 国家电网公司 | Below bearing type generator thrust bearing bearing shell dismantling device and assembly and disassembly methods |
| CN108223568A (en) * | 2018-03-06 | 2018-06-29 | 哈尔滨广瀚燃气轮机有限公司 | A kind of gas turbine long-life composite bearing |
| CN109570898A (en) * | 2018-09-21 | 2019-04-05 | 大连德宇机械有限公司 | Closed-smelting machine rotor brasses replacing options |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106695656B (en) | 2018-05-08 |
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| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |