CN204402580U - A kind of gas turbine turbine moving-stator blade axial clearance adjust structure - Google Patents
A kind of gas turbine turbine moving-stator blade axial clearance adjust structure Download PDFInfo
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- CN204402580U CN204402580U CN201420871751.6U CN201420871751U CN204402580U CN 204402580 U CN204402580 U CN 204402580U CN 201420871751 U CN201420871751 U CN 201420871751U CN 204402580 U CN204402580 U CN 204402580U
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Abstract
A kind of gas turbine turbine moving-stator blade axial clearance regulation structure, relates to the structural design of gas turbine.This turbine moving-stator blade axial clearance adjust structure comprises "T"-shapedly to be held ring mounting groove and is arranged on " convex " type adjustment ring in groove." convex " shape adjustment ring should load turbine and hold in the "T"-shaped mounting groove of ring, " convex " type adjustment ring and top turbine are held ring and are held together with ring with rear class turbine and be installed on combustion engine turbine cylinder, and the reconditioning face of " convex " type adjustment ring contacts with combustion engine turbine cylinder axis.During in-site installation, according to movable vane and the stator blade axial clearance of actual measurement, the reconditioning face of this adjustment ring of reconditioning, changes turbine and holds ring in turbine spindle position upwards, and then make the axial clearance of turbine moving-stator blade reach design load.
Description
Technical field
The utility model relates to a kind of gas turbine turbine moving-stator blade axial clearance adjust structure, belongs to gas turbine structure design field.
Background technique
In industry gas turbine, turbine is made up of stator assembly and rotor assembly.By the rotation of rotor, be mechanical work by the thermal energy of high-temperature high-pressure fuel gas.In the course of the work, because fuel gas temperature is high, stator assembly and rotor assembly are heated generation axial displacement, because the two displacement amount is different, the stator blade of stator and the movable vane of rotor there will be axial scratch, bring the damage of stator blade and movable vane, affect efficiency of turbine, reduce quiet movable vane working life, time serious, to threaten unit operation safety.
In traditional industry gas turbine, turbine moving-stator blade axial clearance can only be determined by design, but in the course of working of gas turbine components, the tolerance of size of parts axially can accumulate on stator part and rotor part, moving-stator blade axial clearance during installation may exceed design load, can only again add turbine and hold ring ear end face by machine in the case, amount of finish be large, and the design cycle is long.
Model utility content
The purpose of this utility model is to provide a kind of gas turbine turbine moving-stator blade axial clearance adjust structure, the axial scratch problem of industry gas turbine turbine moving-stator blade can be solved preferably, improve functional reliability, the stability of gas turbine turbine, and shorten the design cycle further.
The technical solution of the utility model is as follows:
This turbine moving-stator blade axial clearance adjust structure comprises and is separately positioned on top turbine and holds "T"-shaped that ring and rear class turbine hold on ring and hold ring mounting groove and be arranged on "T"-shaped " convex " type adjustment ring of holding in ring mounting groove." convex " shape adjustment ring should load turbine and hold in the "T"-shaped mounting groove of ring, " convex " type adjustment ring and top turbine are held ring and are held together with ring with rear class turbine and be installed on combustion engine turbine cylinder, and the reconditioning face of " convex " type adjustment ring contacts with combustion engine turbine cylinder axis.During in-site installation, according to movable vane and the stator blade axial clearance of actual measurement, the reconditioning face of this adjustment ring of reconditioning, changes turbine and holds ring in turbine spindle position upwards, and then make the axial clearance of turbine moving-stator blade reach design load.
The utility model compared with prior art, have the following advantages and beneficial effect: gas turbine turbine moving-stator blade axial clearance adjust structure provided by the utility model, can according to the axial clearance value of the movable vane of field measurement and stator blade, the reconditioning face of reconditioning " convex " type adjustment ring, can eliminate and accumulate owing to processing the axial tolerance brought and the error brought is installed, to reach the design load of moving-stator blade axial clearance, ensure that gas turbine reliably, stably works.
Accompanying drawing explanation
Fig. 1 is the gas turbine turbine moving-stator blade axial clearance adjust structure schematic diagram that the utility model provides.
Fig. 2 is the gas turbine turbine moving-stator blade axial clearance adjust structure enlarged view that the utility model provides.
Fig. 3 is the gas turbine turbine moving-stator blade axial clearance adjust structure generalized section that the utility model provides.
List of parts: 1-combustion engine turbine cylinder; Before 2-, ring held by turbine; After 3-, ring held by turbine; 4-turbine stator blade; 5-rotor assembly; 6-" convex " type adjustment ring; Moving-stator blade axial clearance before 7-; Moving-stator blade axial clearance after 8-; 9-" convex " type adjustment ring reconditioning face; The "T"-shaped mounting groove of ring held by 10-turbine.
Embodiment
Below in conjunction with accompanying drawing, structure of the present utility model, principle and working procedure are described further.
Gas turbine Turbine section structure as shown in Figure 1, with sprue fuel gas flow direction for turbine spindle to.Front turbine is held ring 2 and rear turbine and is held ring 3 and be arranged in the mounting groove of combustion engine turbine cylinder 1, and turbine stator blade 4 is arranged on turbine and holds on ring 3, and turbine stator blade 4 has the requirement of front axial clearance 7 and rear axial clearance 8 with the movable vane in rotor assembly 5.
Gas turbine turbine moving-stator blade axial clearance adjust structure comprises "T"-shapedly holds ring mounting groove 10 and " convex " type adjustment ring 6, "T"-shaped ring mounting groove 10 of holding is separately positioned on top turbine and holds ring 2 and rear class turbine is held on ring 3, and " convex " type adjustment ring 6 is arranged on "T"-shapedly holds in ring mounting groove; " convex " type adjustment ring 6 and top turbine should hold ring 2 and hold together with ring 3 with rear class turbine and be installed on combustion engine turbine cylinder 1, the reconditioning face 9 of " convex " type adjustment ring 6 contacts (see Fig. 2) with combustion engine turbine cylinder axis.
As shown in Figure 3, the reconditioning face 9 of " convex " type adjustment ring contacts axial with combustion engine turbine cylinder 1, according to the movable vane of field measurement and the axial clearance value of stator blade, the reconditioning face 9 of reconditioning " convex " type adjustment ring, namely the front turbine of adjustable holds ring 2 and the axial mounting point of ring 3 on combustion engine turbine cylinder 1 held by rear turbine, Indirect method front moving-stator blade axial clearance 7 and rear moving-stator blade axial clearance 8; Can eliminate and accumulate owing to processing the axial tolerance brought and the error brought is installed, to reach the design load of moving-stator blade axial clearance, ensure that gas turbine reliably, stably works.
Claims (1)
1. a gas turbine turbine moving-stator blade axial clearance adjust structure, it is characterized in that: described adjust structure comprises and is separately positioned on top turbine and holds "T"-shaped that ring (2) and rear class turbine hold on ring (3) and hold ring mounting groove (10) and be arranged on "T"-shaped " convex " type adjustment ring (6) held in ring mounting groove (10), " convex " type adjustment ring (6) and top turbine should hold ring (2) and rear class turbine and hold together with ring (3) and be installed on combustion engine turbine cylinder, the reconditioning face (9) of " convex " type adjustment ring (6) axially contacts with combustion engine turbine cylinder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420871751.6U CN204402580U (en) | 2014-12-31 | 2014-12-31 | A kind of gas turbine turbine moving-stator blade axial clearance adjust structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420871751.6U CN204402580U (en) | 2014-12-31 | 2014-12-31 | A kind of gas turbine turbine moving-stator blade axial clearance adjust structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204402580U true CN204402580U (en) | 2015-06-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420871751.6U Active CN204402580U (en) | 2014-12-31 | 2014-12-31 | A kind of gas turbine turbine moving-stator blade axial clearance adjust structure |
Country Status (1)
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| CN (1) | CN204402580U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107461224A (en) * | 2016-06-06 | 2017-12-12 | 曼柴油机和涡轮机欧洲股份公司 | Axial-flow turbine |
| CN109779701A (en) * | 2019-03-14 | 2019-05-21 | 中国船舶重工集团公司第七0四研究所 | Axis stream air turbine experimental rig |
| CN113756883A (en) * | 2021-09-26 | 2021-12-07 | 中国联合重型燃气轮机技术有限公司 | Active control device and method for gas turbine blade top clearance |
-
2014
- 2014-12-31 CN CN201420871751.6U patent/CN204402580U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107461224A (en) * | 2016-06-06 | 2017-12-12 | 曼柴油机和涡轮机欧洲股份公司 | Axial-flow turbine |
| CN109779701A (en) * | 2019-03-14 | 2019-05-21 | 中国船舶重工集团公司第七0四研究所 | Axis stream air turbine experimental rig |
| CN109779701B (en) * | 2019-03-14 | 2023-12-05 | 中国船舶重工集团公司第七0四研究所 | Axial flow air turbine test device |
| CN113756883A (en) * | 2021-09-26 | 2021-12-07 | 中国联合重型燃气轮机技术有限公司 | Active control device and method for gas turbine blade top clearance |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Structure for adjusting axial clearance between turbine dynamic and static blades of gas turbine Effective date of registration: 20161104 Granted publication date: 20150617 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20150617 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20191227 Address after: 102209 Beijing Changping District in the future of the national electric investment group Park in the future science city south of Beijing Patentee after: China United heavy-duty gas turbine technology Co., Ltd. Address before: 100084 No. 8, building 1, No. 1001, Zhongguancun East Road, Beijing, Haidian District Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. |