CN201650665U - Connecting structure of heavy duty gas turbine compressor disk and shaft neck - Google Patents
Connecting structure of heavy duty gas turbine compressor disk and shaft neck Download PDFInfo
- Publication number
- CN201650665U CN201650665U CN2010201110612U CN201020111061U CN201650665U CN 201650665 U CN201650665 U CN 201650665U CN 2010201110612 U CN2010201110612 U CN 2010201110612U CN 201020111061 U CN201020111061 U CN 201020111061U CN 201650665 U CN201650665 U CN 201650665U
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- Prior art keywords
- gas turbine
- shaft neck
- compressor disk
- axle journal
- heavy duty
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- Expired - Fee Related
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- 238000009434 installation Methods 0.000 claims description 19
- 238000002485 combustion reaction Methods 0.000 claims description 14
- 244000126211 Hericium coralloides Species 0.000 claims description 5
- 238000004519 manufacturing process Methods 0.000 abstract description 8
- 238000005516 engineering process Methods 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 241000397426 Centroberyx lineatus Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
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Abstract
The utility model discloses a connecting structure of a heavy duty gas turbine compressor disk and a shaft neck, which belongs to the manufacturing technology filed of gas turbine gas compressors, in particular to an improvement of a connecting structure of a heavy duty gas turbine compressor disk and a shaft neck. The utility model provides a connecting structure of a heavy duty gas turbine compressor disk and a shaft neck, which can increase external field maintainability, reduces the labor strength of workers, greatly reduces the manufacturing cycle of a gas turbine, and has simple assembly process. The connecting structure of the heavy duty gas turbine compressor disk and the shaft neck comprises a compressor disk and a shaft neck, and is characterized in that the mounting sides of the compressor disk and the shaft neck use an external turning structure.
Description
Technical field:
The utility model belongs to combustion machine gas compressor manufacturing technology field, particularly relates to the improvement of the linkage structure of a kind of heavy combustion engine compressor disc and axle journal.
Background technique:
At present, introvert is all adopted on the installation limit of existing heavy combustion engine compressor disc and the installation limit of axle journal, promptly turns over to core place direction, as shown in Figure 1 and Figure 2.For bolt is connected, the comb ring gear with comb tooth is installed between the installation limit of the installation limit of compressor disc and axle journal, as shown in Figure 3 between compressor disc and the axle journal.Because the space of joint is narrow and small, causes nut check difficult unusually, the assembly technology complexity has been wasted a large amount of installation times; And can bring inconvenience to the R and M that the later stage is fired machine, and increased working strength of workers, prolonged the manufacturing cycle of combustion machine.
The model utility content:
At the linkage structure assembly technology complexity of existing heavy combustion engine compressor disc and axle journal, the R and M difficulty has increased working strength of workers, has prolonged the problem of the manufacturing cycle of combustion machine; The utility model provides a kind of maintainability that improves the outfield, alleviates working strength of workers, shortens the manufacturing cycle of combustion machine greatly, the linkage structure of simple heavy combustion engine compressor disc of assembly technology and axle journal.
To achieve these goals, the utility model adopts following technological scheme, the linkage structure of a kind of heavy combustion engine compressor disc and axle journal comprises compressor disc and axle journal, is characterized in that the installation limit of described compressor disc and the installation limit of axle journal all adopt the structure of turning up.
Outer rim place on the installation limit of axle journal is provided with the comb tooth, thereby reduces bolt, nut and comb ring gear, and the linkage structure of compressor disc and axle journal is simplified more.
The beneficial effects of the utility model:
1, because the structure of turning up is all adopted on the installation limit of compressor disc of the present utility model and the installation limit of axle journal, just increased the space of the joint of compressor disc and axle journal, reduced the complexity of assembly technology, shortened the manufacturing cycle of combustion machine greatly, improved the maintainability in outfield, saved maintenance cost, alleviated working strength of workers, to the also reduction greatly of requirement of manufacturing equipment;
2, owing to be provided with the comb tooth, thereby reduced bolt, nut and comb ring gear, the linkage structure of compressor disc and axle journal is simplified more at the outer rim place on the installation limit of axle journal of the present utility model.
Description of drawings:
Fig. 1 is the structural representation of existing compressor disc;
Fig. 2 is the structural representation of existing axle journal;
Fig. 3 is the example structure schematic representation that existing compressor disc is connected with axle journal;
Fig. 4 is the structural representation of compressor disc of the present utility model;
Fig. 5 is the structural representation of axle journal of the present utility model;
Fig. 6 is the example structure schematic representation that compressor disc of the present utility model is connected with axle journal;
Among the figure, 1-core, the installation limit of 2-compressor disc, 3-compressor disc, 4-web, 5-swallow-tail form tongue-and-groove, ring in the 6-axle journal, three grades of 7-, 8-fourth stage dish, 9-comb tooth, the installation limit of 10-axle journal, 11-comb ring gear.
Embodiment:
Below in conjunction with accompanying drawing the utility model is described further:
As Fig. 4, shown in Figure 5, the linkage structure of a kind of heavy combustion engine compressor disc and axle journal comprises compressor disc 3 and axle journal 6, and the structure of turning up is all adopted on the installation limit 2 of described compressor disc and the installation limit 10 of axle journal, promptly turns over to swallow-tail form tongue-and-groove 5 place directions.
Outer rim place on the installation limit 10 of axle journal is provided with comb tooth 9, thereby reduces bolt, nut and comb ring gear 11, and the compressor disc 3 and the linkage structure of axle journal 6 are simplified more.
Claims (2)
1. the linkage structure of heavy combustion engine compressor disc and axle journal comprises compressor disc and axle journal, it is characterized in that the installation limit of described compressor disc and the installation limit of axle journal all adopt the structure of turning up.
2. the linkage structure of a kind of heavy combustion engine compressor disc according to claim 1 and axle journal is characterized in that being provided with the comb tooth at the outer rim place on the installation limit of axle journal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201110612U CN201650665U (en) | 2010-02-10 | 2010-02-10 | Connecting structure of heavy duty gas turbine compressor disk and shaft neck |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201110612U CN201650665U (en) | 2010-02-10 | 2010-02-10 | Connecting structure of heavy duty gas turbine compressor disk and shaft neck |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201650665U true CN201650665U (en) | 2010-11-24 |
Family
ID=43115898
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010201110612U Expired - Fee Related CN201650665U (en) | 2010-02-10 | 2010-02-10 | Connecting structure of heavy duty gas turbine compressor disk and shaft neck |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201650665U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102330605A (en) * | 2011-09-05 | 2012-01-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Heavy combustion engine assembling method for assembling rotor and front and rear supports in combining manner |
| CN105402157A (en) * | 2015-12-25 | 2016-03-16 | 中国航空工业集团公司沈阳发动机设计研究所 | Integral type disk shaft structure |
| CN110926773A (en) * | 2019-11-27 | 2020-03-27 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for checking assembly flexibility of long bolts between high-pressure rotor disks |
-
2010
- 2010-02-10 CN CN2010201110612U patent/CN201650665U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102330605A (en) * | 2011-09-05 | 2012-01-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Heavy combustion engine assembling method for assembling rotor and front and rear supports in combining manner |
| CN102330605B (en) * | 2011-09-05 | 2013-06-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Heavy combustion engine assembling method for assembling rotor and front and rear supports in combining manner |
| CN105402157A (en) * | 2015-12-25 | 2016-03-16 | 中国航空工业集团公司沈阳发动机设计研究所 | Integral type disk shaft structure |
| CN105402157B (en) * | 2015-12-25 | 2018-06-05 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of monoblock type dish axle structure |
| CN110926773A (en) * | 2019-11-27 | 2020-03-27 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for checking assembly flexibility of long bolts between high-pressure rotor disks |
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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: 20101124 Termination date: 20160210 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |