CN201095079Y - Positioning disc for assembling and repairing combustion turbine - Google Patents
Positioning disc for assembling and repairing combustion turbine Download PDFInfo
- Publication number
- CN201095079Y CN201095079Y CNU2007200119317U CN200720011931U CN201095079Y CN 201095079 Y CN201095079 Y CN 201095079Y CN U2007200119317 U CNU2007200119317 U CN U2007200119317U CN 200720011931 U CN200720011931 U CN 200720011931U CN 201095079 Y CN201095079 Y CN 201095079Y
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- Prior art keywords
- turbine
- disk
- assembling
- positioning disk
- disc
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- 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.)
- Expired - Fee Related
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A locating disk for assembling and maintaining a gas turbine belongs to the technology field of gas turbine. The locating disk has three parts, one end of the locating disk coordinates with a turbine disk to connect the disk shaped structure, and the other end is a disk shaped structure, the two ends are connected by a link arm, and the thickness of the disk shaped end surface is bigger than that of the processed screw. The locating disk of the utility model has the advantages of convenient maintenance, convenient assembling, accurate location and improved efficiency of turbine.
Description
Technical field
The utility model belongs to the gas turbine technology field, particularly relates to the positioning disk that a kind of gas turbine assembling repair is used.
Background technology
Gas turbine comprises stator and two parts of rotor, and rotor relies on bearing to locate in stator.For heavy duty gas turbine multistage turbine rotor, solve assembling and repair the problem of changing part is the comparison difficulty.Be generally convenient for assembly and repair, rotor is designed to the pin syndeton that is easy to dismantle, or uses and split the case structure design.With detachable rotor complex structure not only, and the life-span is low; And split casing, because it must the design and installation limit, thereby the casing wall thickness is uneven, the thermal deformation that causes after the casing of wall unevenness is heated also is uneven, this can cause the variation of turbine radial clearance inhomogeneous, too small gap is easy to initiating failure, and excessive gap can increase air loss, reduces efficiency of turbine.
The utility model content
In order to solve the problem of above-mentioned existence, the positioning disk that the utility model provides a kind of gas turbine assembling repair to use.It is installed between turbine and the back supporting, to realize the centering of rear support, reaches purpose convenient for assembly and that repair.
The utility model is divided into three parts, the one end is the clutch disk structure that matches with the turbine dish, the other end is a disc-shaped structure, between connect by linking arm, its disc end surface thickness is more than or equal to the service bolt end face, and the disc-shaped structure of this positioning disk is positioned at the space of back supporting and the formation of elastic bearing casing.
The utility model is by being bolted on the turbine dish, by equally distributed three bolts hole on the supporting casing after the elasticity service bolt twisted to lean against on the positioning disk outer rim, to realize the centering of rear support, reaches purpose convenient for assembly and that repair.
The utility model has the advantages that convenient repair, convenient for assembly, accurate positioning has improved the efficient of turbine.
Description of drawings
Fig. 1 is a mounting structure schematic diagram of the present utility model,
Fig. 2 is the I portion enlarged diagram of Fig. 1,
Fig. 3 is the A-A enlarged diagram of Fig. 2;
1. compressors among the figure, 2. combustion chamber, 3. turbine, 4. back supporting, 5. turbine dish, 6. bolt, 7. elastic bearing casing, 8. assembling bolt, 9. positioning disk, 10. service bolt, 11. linking arms.
The specific embodiment
Below in conjunction with accompanying drawing the utility model is described further:
Embodiment: as Fig. 2, shown in Figure 3, the utility model is divided into three parts, and the one end is the syndeton that matches with turbine dish 5, and the other end is a disc-shaped structure, between connect by linking arm 11, its disc end surface thickness is more than or equal to the end face of service bolt 10.
The utility model is used for gas turbine, as shown in Figure 1, gas turbine comprises compressor 1, combustion chamber 2, turbine 3, back supporting 4 and elastic bearing casing 7, turbine 3 ends are turbine dish 5, elastic bearing casing 7 is provided with 3 circumferential uniform bolt mount pads in corresponding positioning disk position, as shown in Figure 2, be used to install assembling bolt 8 or service bolt 10, behind turbine dish 5 ends, positioning disk 9 is installed, positioning disk 9 has the edge with the disc circumference that turbine dish 5 matches, it is taken be enclosed within on the turbine dish 5, fixing by bolt 6, the disc-shaped structure of this positioning disk 9 is positioned at the space of back supporting 4 and 7 formation of elastic bearing casing.
When the combustion machine assembled, positioning disk 9 was sleeved on the turbine dish 5, and is fixing with bolt 6.Again circumferential equally distributed 3 the long service bolts 10 on the elastic bearing casing 7 are twisted inward, lean on the disc-shaped structure of positioning disk 9, the combustion machine rotor is located in stator, can carry out the assembling of rear bearing 4 like this; After rear bearing 4 assemblings finish, service bolt 10 is back-outed outward, changed short normal assembling bolt 8 and screw on, guarantee that the operate as normal of combustion machine is unaffected.During repairing, replace normal assembling bolt,, can carry out the replacing of rear bearing or the repairing of turbine 3 parts under plumbness afterwards rotor, stator location with service bolt 8.
Claims (2)
1. positioning disk that the gas turbine assembling repair is used, it is characterized in that this positioning disk is divided into three parts, the one end is the clutch disk structure that matches with the turbine dish, and the other end is a disc-shaped structure, between connect by linking arm, its disc end surface thickness is more than or equal to technology screw end face.
2. the positioning disk that a kind of gas turbine assembling repair as claimed in claim 1 is used is characterized in that described positioning disk has the edge with the disc circumference that the turbine dish matches.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200119317U CN201095079Y (en) | 2007-04-29 | 2007-04-29 | Positioning disc for assembling and repairing combustion turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200119317U CN201095079Y (en) | 2007-04-29 | 2007-04-29 | Positioning disc for assembling and repairing combustion turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201095079Y true CN201095079Y (en) | 2008-08-06 |
Family
ID=39922138
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007200119317U Expired - Fee Related CN201095079Y (en) | 2007-04-29 | 2007-04-29 | Positioning disc for assembling and repairing combustion turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201095079Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103482219A (en) * | 2013-09-16 | 2014-01-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Axial and radial positioning method for rotator in gas turbine transporting process |
| CN113431703A (en) * | 2021-06-30 | 2021-09-24 | 中国航发动力股份有限公司 | Composite assembling method of multilayer assembling structure |
-
2007
- 2007-04-29 CN CNU2007200119317U patent/CN201095079Y/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103482219A (en) * | 2013-09-16 | 2014-01-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Axial and radial positioning method for rotator in gas turbine transporting process |
| CN103482219B (en) * | 2013-09-16 | 2016-06-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Rotor is carried out axle, radial localization method by a kind of internal combustion turbine transportation |
| CN113431703A (en) * | 2021-06-30 | 2021-09-24 | 中国航发动力股份有限公司 | Composite assembling method of multilayer assembling structure |
| CN113431703B (en) * | 2021-06-30 | 2022-07-12 | 中国航发动力股份有限公司 | Composite assembly method of multilayer assembly structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20080806 Termination date: 20150429 |
|
| EXPY | Termination of patent right or utility model |