CN106089335B - Turbine blade trial assembly adapted bogey and its assembly method - Google Patents
Turbine blade trial assembly adapted bogey and its assembly method Download PDFInfo
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- CN106089335B CN106089335B CN201610585468.0A CN201610585468A CN106089335B CN 106089335 B CN106089335 B CN 106089335B CN 201610585468 A CN201610585468 A CN 201610585468A CN 106089335 B CN106089335 B CN 106089335B
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- layer grommet
- grommet
- internal layer
- blade
- outer layer
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
- F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
Abstract
Turbine blade trial assembly adapted bogey and its assembly method, belong to blade assembling servicing unit.Lack steam turbine gas channel blade installation auxiliary equipment at present, dismounting workload is big, progress is slow.Turbine blade trial assembly adapted bogey, the surface of annulus chassis (1), which has, places outer layer grommet (2) and internal layer grommet (3) formation bearing groove (7) in groove (4), groove (4)；There is inner ring shoulder (5) on the interior ring-side wall of outer layer grommet (2)；There is outer shroud shoulder (6) on the outer rim side wall of internal layer grommet (3).The method that turbine blade trial assembly is matched somebody with somebody, the outer layer grommet (2) and internal layer grommet (3) that selection matches with blade dimensions is installed in the groove (4) of annulus chassis (1)；Adjust outer layer grommet (2) and internal layer grommet (3) baseplane difference in height；By blade by being only put into bearing groove (7), the confined state of whole circle blade is detected, Product Assembly process is realized.The present invention has simple in construction, the convenient advantage installed.
Description
Technical field
The present invention relates to a kind of turbine blade trial assembly adapted bogey and its assembly method.
Background technology
Turbine Steam circulation road be by be assemblied on rotor on whole circle movable vane piece and dividing plate whole circle stator blade with along steam turbine
What group axis direction was realized apart from one another by the steam passage of composition, no matter the assembling of movable vane piece or stator blade welding can all have blade
The end surface dislocation of integral shroud or blade root between blade, and the integral shroud or the reconditioning quality of blade root due to single blade are excessive, cause
Last years even if reconditioning also without enough Space configurations, if such issues that occur in Product Assembly process, it is unnecessary to bring
Dismantlement work amount, and the manufacturing schedule of product is influenceed, a kind of turbine blade examination has thus been invented to solve the above problems
Assembling bogey.
The content of the invention
The invention aims to solve to lack steam turbine gas channel blade installation auxiliary equipment at present, cause
The problem of workload is big, progress is slow is dismounted, and proposes a kind of turbine blade trial assembly adapted bogey.
Turbine blade trial assembly adapted bogey, its composition includes：Annulus chassis, outer layer grommet and internal layer grommet, circle
Ring chassis is annular lamellar structure, and a side surface on annulus chassis has groove, and outer layer grommet is placed in the outer ring of inside grooves,
The inner ring of inside grooves places internal layer grommet；Wherein,
There is inner ring shoulder, the thickness of inner ring shoulder is less than the thickness of outer layer grommet, outer layer lining on the interior ring-side wall of outer layer grommet
Ring and inner ring shoulder constitute stepped construction；
There is outer shroud shoulder, the thickness of outer shroud shoulder is less than the thickness of internal layer grommet, internal layer lining on the outer rim side wall of internal layer grommet
Ring and outer shroud shoulder constitute stepped construction；
And placed in groove after outer layer grommet and internal layer grommet, shape between the inner ring of outer layer grommet and the outer shroud of internal layer grommet
Into bearing groove.
A kind of turbine blade trial assembly method of completing the square,
Step 1: annulus chassis is hung to trial assembly place by lifting screw hole；
Step 2: the outer layer grommet and internal layer grommet that are matched according to the size for the blade for wanting trial assembly, selection with blade dimensions,
Outer layer grommet and internal layer grommet are respectively installed to outside the outer shroud in the groove on annulus chassis and the position of inner ring, outer layer grommet
The outer shroud enclosed with groove is brought into close contact, and the inner ring of internal layer grommet and the inner ring of groove are brought into close contact；
Step 3: determining that outer layer grommet and internal layer are served as a contrast with the height difference under confined state by the integral shroud and leaf of blade
Ring baseplane difference in height；
Step 4: the integral shroud of the inner ring of outer layer grommet and the whole circle of blade is brought into close contact, the outer ring of internal layer grommet and blade are whole
The leaf of circle is held with being brought into close contact by the annulus chassis, outer layer grommet and internal layer grommet composition the annular of insertion that are adapted to size
Carry groove；
Step 5: by blade by being only put into bearing groove, detecting the confined state of whole circle blade, eliminating defect, realize production
Product assembling process
Beneficial effects of the present invention are：
The present invention is turbine blade trial assembly adapted bogey, includes annulus chassis, the outer layer of annular lamellar structure
Grommet and internal layer grommet, the surface on annulus chassis, which is set in groove, groove, places on outer layer grommet and internal layer grommet, outer layer grommet
With inner ring shoulder, there is outer shroud shoulder on internal layer grommet, stepped construction is constituted, carrying is formed between outer layer grommet and internal layer grommet
Groove, forms the space for carrying assembling blade, so as to easily carry out blade trial assembly；
In addition, by changing various sizes of outer layer grommet and internal layer grommet, it is possible to which various sizes of blade is carried out
Trial assembly is matched somebody with somebody；
By outer layer grommet and the making material Xuanwei copper of internal layer grommet, damage of colliding with during blade trial assembly can be prevented；
The present invention is simple in construction, and it is easy to manufacture, and cost is low, is easy to use on a large scale.
Brief description of the drawings
Fig. 1 is structural representation of the invention；
Fig. 2 is the structural representation on annulus chassis of the present invention；
Fig. 3 is the structural representation of outer layer grommet of the present invention；
Fig. 4 is the structural representation of internal layer grommet of the present invention；
Schematic diagram when Fig. 5 is present invention assembling blade；
Embodiment
Embodiment one：
The turbine blade trial assembly adapted bogey of present embodiment, with reference to shown in Fig. 1, its composition includes：Annulus bottom
Disk 1, outer layer grommet 2 and internal layer grommet 3, annulus chassis 1 are annular lamellar structure, and the side surface on annulus chassis 1 has recessed
The inner ring that outer ring inside groove 4, groove 4 places inside outer layer grommet 2, groove 4 places internal layer grommet 3；Wherein,
There is inner ring shoulder 5, the thickness of inner ring shoulder 5 is less than the thickness of outer layer grommet 2, outside on the interior ring-side wall of outer layer grommet 2
Layer grommet 2 and inner ring shoulder 5 constitute stepped construction；
There is outer shroud shoulder 6, the thickness of outer shroud shoulder 6 is less than the thickness of internal layer grommet 3, interior on the outer rim side wall of internal layer grommet 3
Layer grommet 3 and outer shroud shoulder 6 constitute stepped construction；
And placed in groove 4 after outer layer grommet 2 and internal layer grommet 3, the inner ring of outer layer grommet 2 and the outer shroud of internal layer grommet 3
Between formed bearing groove 7, the blade for carrying assembling.
Embodiment two：
From unlike embodiment one, the turbine blade trial assembly adapted bogey of present embodiment is described
Annulus chassis 1 is uniformly distributed one group of lifting screw hole 8 in the one side with groove 4 in circumferencial direction.
Embodiment three：
From unlike embodiment one or two, the turbine blade trial assembly adapted bogey of present embodiment,
The surface of the outer layer grommet 2 is uniformly distributed one group of suspension ring hole 9 in circumferencial direction.
Embodiment four：
From unlike embodiment three, the turbine blade trial assembly adapted bogey of present embodiment is described
The surface of internal layer grommet 3 is uniformly distributed one group of suspension ring hole 9 in circumferencial direction.
Embodiment five：
From unlike embodiment four, the turbine blade trial assembly adapted bogey of present embodiment is described
The One On The Chassis lifting screw hole 8 of annulus, and suspension ring hole 9 on outer layer grommet 2 and internal layer grommet 3 are all four.
Embodiment six：
From unlike embodiment four, the turbine blade trial assembly adapted bogey of present embodiment is described
The making material of outer layer grommet 2 and internal layer grommet 3 is copper, prevents from being collided with during blade trial assembly and causes damage.
Embodiment seven：
The assembly method of the utilization turbine blade trial assembly adapted bogey of present embodiment,
Step 1: annulus chassis 1 is hung to trial assembly place by lifting screw hole 8；
Step 2: according to the size for the blade 10 for wanting trial assembly, selection and the outer layer grommet 2 and internal layer of the matching size of blade 10
Grommet 3, is respectively installed to the outer shroud in the groove 4 on annulus chassis 1 and the position of inner ring, outside by outer layer grommet 2 and internal layer grommet 3
The outer ring of layer grommet 2 and the outer shroud of groove 4 are brought into close contact, and the inner ring of the inner ring and groove 4 of internal layer grommet 3 is brought into close contact；
Step 3: determining outer layer grommet 2 and interior with the height difference under confined state by the integral shroud of blade 10 and leaf
The layer baseplane difference in height of grommet 3；
Step 4: the integral shroud of the inner ring of outer layer grommet 2 and the whole circle of blade is brought into close contact, the outer ring of internal layer grommet 3 and blade
The leaf of whole circle constitutes the annular of insertion by being adapted to annulus chassis 1, outer layer grommet 2 and the internal layer grommet 3 of size with being brought into close contact
Bearing groove 7；
Step 5: by blade by being only put into bearing groove 7, detecting the confined state of whole circle blade 10, eliminating defect, smoothly
Realize Product Assembly process.
The present invention can also have other various embodiments, in the case of without departing substantially from spirit of the invention and its essence, this area
Technical staff works as can make various corresponding changes and deformation according to the present invention, but these corresponding changes and deformation should all belong to
The protection domain of appended claims of the invention.
Claims (7)
1. a kind of turbine blade trial assembly adapted bogey, it is characterised in that：Its composition includes：Annulus chassis (1), outer layer lining
Ring (2) and internal layer grommet (3), annulus chassis (1) is annular lamellar structure, and a side surface of annulus chassis (1) has groove
(4), outer layer grommet (2) is placed in the internal outer ring of groove (4), and the internal inner ring of groove (4) places internal layer grommet (3)；Wherein,
There is inner ring shoulder (5), the thickness of inner ring shoulder (5) is less than the thickness of outer layer grommet (2) on the interior ring-side wall of outer layer grommet (2)
Degree, outer layer grommet (2) and inner ring shoulder (5) constitute stepped construction；
There is outer shroud shoulder (6), the thickness of outer shroud shoulder (6) is less than the thickness of internal layer grommet (3) on the outer rim side wall of internal layer grommet (3)
Degree, internal layer grommet (3) and outer shroud shoulder (6) constitute stepped construction；
And placed in groove (4) after outer layer grommet (2) and internal layer grommet (3), the inner ring and internal layer grommet (3) of outer layer grommet (2)
Outer shroud between formed bearing groove (7).
2. turbine blade trial assembly adapted bogey according to claim 1, it is characterised in that：The annulus chassis (1)
In the one side with groove (4) one group of lifting screw hole (8) is uniformly distributed in circumferencial direction.
3. turbine blade trial assembly adapted bogey according to claim 1 or claim 2, it is characterised in that：The outer layer grommet
(2) surface is uniformly distributed one group of suspension ring hole (9) in circumferencial direction.
4. turbine blade trial assembly adapted bogey according to claim 3, it is characterised in that：The internal layer grommet (3)
Surface be uniformly distributed one group of suspension ring hole (9) in circumferencial direction.
5. turbine blade trial assembly adapted bogey according to claim 4, it is characterised in that：The annulus chassis (1)
On lifting screw hole (8), and suspension ring hole (9) on outer layer grommet (2) and internal layer grommet (3) is all four.
6. turbine blade trial assembly adapted bogey according to claim 4, it is characterised in that：The outer layer grommet (2)
Making material with internal layer grommet (3) is copper.
7. a kind of device using described in any of the above-described claim carries out the method that turbine blade trial assembly is matched somebody with somebody, its feature exists
In：
Step 1: annulus chassis (1) is hung to trial assembly place by lifting screw hole (8)；
Step 2: the outer layer grommet (2) and internal layer grommet that are matched according to the size for the blade for wanting trial assembly, selection with blade dimensions
(3) outer layer grommet (2) and internal layer grommet (3), are respectively installed to outer shroud in the groove of annulus chassis (1) (4) and inner ring
Position, the outer ring of outer layer grommet (2) and the outer shroud of groove (4) are brought into close contact, and the inner ring of internal layer grommet (3) is interior with groove (4)
Ring is brought into close contact；
Step 3: determining that outer layer grommet (2) and internal layer are served as a contrast with the height difference under confined state by the integral shroud and leaf of blade
Ring (3) baseplane difference in height；
Step 4: the integral shroud of the inner ring of outer layer grommet (2) and the whole circle of blade is brought into close contact, the outer ring of internal layer grommet (3) and blade
The leaf of whole circle constitutes insertion with being brought into close contact by the annulus chassis (1), outer layer grommet (2) and the internal layer grommet (3) that are adapted to size
Annular bearing groove (7)；
Step 5: by blade by being only put into bearing groove (7), detecting the confined state of whole circle blade, eliminating defect, realize product
Assembling process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610585468.0A CN106089335B (en) | 2016-07-22 | 2016-07-22 | Turbine blade trial assembly adapted bogey and its assembly method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610585468.0A CN106089335B (en) | 2016-07-22 | 2016-07-22 | Turbine blade trial assembly adapted bogey and its assembly method |
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| Publication Number | Publication Date |
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| CN106089335A CN106089335A (en) | 2016-11-09 |
| CN106089335B true CN106089335B (en) | 2017-09-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610585468.0A Active CN106089335B (en) | 2016-07-22 | 2016-07-22 | Turbine blade trial assembly adapted bogey and its assembly method |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109968241A (en) * | 2019-04-03 | 2019-07-05 | 哈尔滨汽轮机厂有限责任公司 | A kind of whole circle pre-assembled disk of steam turbine stator blade and prepackage method of completing the square |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4078812A (en) * | 1975-07-04 | 1978-03-14 | Bbc Brown Boveri & Company Limited | Combined seal and guide arrangement for two coaxially arranged machine parts |
| CN101749218A (en) * | 2008-12-05 | 2010-06-23 | 曼涡轮机股份公司 | Horizontally separated fluid machinery shell |
| CN103375180A (en) * | 2012-04-26 | 2013-10-30 | 阿尔斯通技术有限公司 | Turbine diaphragm construction |
| CN205823351U (en) * | 2016-07-22 | 2016-12-21 | 哈尔滨汽轮机厂有限责任公司 | Turbine blade trial assembly adapted bogey |
-
2016
- 2016-07-22 CN CN201610585468.0A patent/CN106089335B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4078812A (en) * | 1975-07-04 | 1978-03-14 | Bbc Brown Boveri & Company Limited | Combined seal and guide arrangement for two coaxially arranged machine parts |
| CN101749218A (en) * | 2008-12-05 | 2010-06-23 | 曼涡轮机股份公司 | Horizontally separated fluid machinery shell |
| CN103375180A (en) * | 2012-04-26 | 2013-10-30 | 阿尔斯通技术有限公司 | Turbine diaphragm construction |
| CN205823351U (en) * | 2016-07-22 | 2016-12-21 | 哈尔滨汽轮机厂有限责任公司 | Turbine blade trial assembly adapted bogey |
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| CN106089335A (en) | 2016-11-09 |
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Effective date of registration: 20221226 Address after: 150000 building 3, high tech production base, Nangang District, Harbin City, Heilongjiang Province Patentee after: HARBIN TURBINE Co.,Ltd. Patentee after: HADIAN POWER EQUIPMENT NATIONAL ENGINEERING RESEARCH CENTER CO.,LTD. Address before: 150046 No. three power road 345, Xiangfang District, Heilongjiang, Harbin Patentee before: HARBIN TURBINE Co.,Ltd. |
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