CN112548485A - Non-impact press-fitting method for stationary blade ring of gas turbine - Google Patents
Non-impact press-fitting method for stationary blade ring of gas turbine Download PDFInfo
- Publication number
- CN112548485A CN112548485A CN202011161299.0A CN202011161299A CN112548485A CN 112548485 A CN112548485 A CN 112548485A CN 202011161299 A CN202011161299 A CN 202011161299A CN 112548485 A CN112548485 A CN 112548485A
- Authority
- CN
- China
- Prior art keywords
- press
- stationary blade
- fitting
- tenon
- gas turbine
- 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.)
- Pending
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P11/00—Connecting or disconnecting metal parts or objects by metal-working techniques not otherwise provided for
- B23P11/02—Connecting or disconnecting metal parts or objects by metal-working techniques not otherwise provided for by first expanding and then shrinking or vice versa, e.g. by using pressure fluids; by making force fits
- B23P11/025—Connecting or disconnecting metal parts or objects by metal-working techniques not otherwise provided for by first expanding and then shrinking or vice versa, e.g. by using pressure fluids; by making force fits by using heat or cold
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention aims to provide a non-impact press-fitting method for a stationary blade ring of a gas turbine, which comprises the following steps: (1) adjusting the positions of the press-fitting tool and the stationary blade to enable the electrode to be in contact with the tongue piece of the stationary blade; (2) switching on a power supply, heating the tenon part, and gradually increasing the current until the tenon is in a softened state; (3) applying a short-time static load to the press-fitting tool to enable the softened tenon to be formed instantly; (4) performing crack-free inspection on the formed tongue structure; (5) and (4) carrying out gapless inspection on the formed tenon and the inner ring by adopting a knocking method. The invention has the advantages of small deformation, difficult crack generation, high stability and the like.
Description
Technical Field
The invention relates to a method for mounting a gas turbine, in particular to a method for mounting a stationary blade of the gas turbine.
Background
The static blade ring installed by adopting the non-impact press mounting method has the advantages of small deformation, difficult crack generation, high stability and the like relative to the static blade ring of the welding structure, the current value before press mounting and the short-time static load value of press mounting can be determined by a manufacturability test before installation, the press mounting has better stability, and the rejection rate caused by welding deformation and defects can be reduced to a greater extent.
Disclosure of Invention
The invention aims to provide a non-impact press-fitting method of a gas turbine stator blade ring, which enables the tongue part of the stator blade to generate plastic deformation and is fastened with an inner ring into a whole.
The purpose of the invention is realized as follows:
the invention discloses a non-impact press mounting method of a stationary blade ring of a gas turbine, which is characterized by comprising the following steps:
(1) adjusting the positions of the press-fitting tool and the stationary blade to enable the electrode to be in contact with the tongue piece of the stationary blade;
(2) switching on a power supply, heating the tenon part, and gradually increasing the current until the tenon is in a softened state;
(3) applying a short-time static load to the press-fitting tool to enable the softened tenon to be formed instantly;
(4) performing crack-free inspection on the formed tongue structure;
(5) and (4) carrying out gapless inspection on the formed tenon and the inner ring by adopting a knocking method.
The present invention may further comprise:
1. the fixed blades and the inner ring are fixedly connected by adopting a three-point press-fitting structural form, so that the success rate of impact-free press-fitting of the male dovetail is ensured.
2. After the tenon is formed, the forming part of the tenon covers the whole groove of the inner ring.
3. The voltage V of the press-fitting current is 2.3-2.5V, when the short-time static load F is 250-350kg, the male die is subjected to upsetting, after the male die is formed, the power supply is cut off, and the formed male die is naturally cooled in the air.
4. Static pressure acting on energizationThe power supply contact area of the heated tongue surface and the stationary blade is not less than 8mm2In order to avoid sparks and defects.
5. Each tongue is formed separately.
The invention has the advantages that: the invention has the advantages of small deformation, difficult crack generation, high stability and the like.
Drawings
FIG. 1 is a schematic view of the installation of the present invention;
FIG. 2 is a flow chart of the present invention;
FIG. 3 is a schematic view of a stationary blade tongue after press-fitting deformation;
FIG. 4 is a schematic view in direction D of FIG. 3 after press-fitting deformation of the stationary blade tongue.
Detailed Description
The invention will now be described in more detail by way of example with reference to the accompanying drawings in which:
with reference to fig. 1-4, the non-impact press-fitting method for the stationary blade ring of the gas turbine structurally comprises a press-fitting tool 1, stationary blades 2 and an inner ring 3. The stator blade 2 and the outer ring are connected through a tenon tongue structure, the stator blade 2 and the inner ring 3 are inserted into a groove of the inner ring through a tongue of the stator blade 2, and the stator blade 2 and the inner ring are fixed by adopting a method of pressing the tongue without impact to form a complete stator blade ring structure. The blade body of the static blade 2 is connected with one pole of a power supply, and the press-fitting tool 1 is connected with the other stage of the power supply.
Referring to fig. 2, after the press fitting tool 1 is contacted with the tongue part of the stationary blade 2, the power supply forms a path, the tongue part is heated to a softening state, and at this time, a short-time static load is applied to the press fitting tool 1 to instantly form the tongue of the softened stationary blade 2. And after press fitting, carrying out crack-free inspection on the deformed structure, and simultaneously, carrying out gapless inspection on the tongue piece of the deformed stationary blade 2 and the inner ring 3 by adopting a knocking method.
Referring to fig. 3, in order to ensure the success rate of non-impact press-fitting of the tongue, and to ensure the firm connection of the stationary blade and the inner ring, a three-point press-fitting structural form is adopted.
Referring to fig. 4, after the tongue of the stator blade 2 is pressed without impact, the forming part needs to cover the whole groove of the inner ring.
The working principle of this patent: the stator blade 2 and the inner ring 3 of the stator blade ring are integrally connected by a principle that the tongue of the stator blade 2 is electrically heated to a softened state by heating metal, is deformed by pressure by a short static load, and is formed by cooling to room temperature in air.
The tongue is heated by a resistance anode and formed by an electrode male die in a plastic state of the material.
The voltage V of the current of the press-fitting 1 is 2.3-2.5V, when the short-time static load F is 250-350kg, the male die of the electrode is subjected to upsetting, after the male die is formed, the power supply is automatically cut off, and the formed male die is naturally cooled in the air.
When the tongue is pressed without impact, the power supply contact area of the stationary blade 2 is not less than 8mm2 by applying static pressure to the tongue surface which is electrically heated, so as to avoid the generation of sparks and defects due to the too small contact area.
The heating temperature and the heating area of the tongue of the stationary blade, the parameters of the current, the static pressure applied to the tongue and the clearance between the tongue and the inner ring all influence the forming quality of the non-impact press-fitting tongue.
Each of its tongues is formed separately when the tongues are press fitted without impact.
The invention can be applied to the structural design aspect of the stator blade ring of the gas turbine.
Claims (6)
1. A non-impact press mounting method for a stationary blade ring of a gas turbine is characterized by comprising the following steps:
(1) adjusting the positions of the press-fitting tool and the stationary blade to enable the electrode to be in contact with the tongue piece of the stationary blade;
(2) switching on a power supply, heating the tenon part, and gradually increasing the current until the tenon is in a softened state;
(3) applying a short-time static load to the press-fitting tool to enable the softened tenon to be formed instantly;
(4) performing crack-free inspection on the formed tongue structure;
(5) and (4) carrying out gapless inspection on the formed tenon and the inner ring by adopting a knocking method.
2. The non-impact press-fitting method for the stationary blade ring of the gas turbine as set forth in claim 1, wherein: the fixed blades and the inner ring are fixedly connected by adopting a three-point press-fitting structural form, so that the success rate of impact-free press-fitting of the male dovetail is ensured.
3. The non-impact press-fitting method for the stationary blade ring of the gas turbine as set forth in claim 1, wherein: after the tenon is formed, the forming part of the tenon covers the whole groove of the inner ring.
4. The non-impact press-fitting method for the stationary blade ring of the gas turbine as set forth in claim 1, wherein: the voltage V of the press-fitting current is 2.3-2.5V, when the short-time static load F is 250-350kg, the male die is subjected to upsetting, after the male die is formed, the power supply is cut off, and the formed male die is naturally cooled in the air.
5. The non-impact press-fitting method for the stationary blade ring of the gas turbine as set forth in claim 1, wherein: static pressure acts on the surface of the tongue which is electrified and heated, and the power supply contact area of the static blade is not less than 8mm2In order to avoid sparks and defects.
6. The non-impact press-fitting method for the stationary blade ring of the gas turbine as set forth in claim 1, wherein: each tongue is formed separately.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011161299.0A CN112548485A (en) | 2020-10-27 | 2020-10-27 | Non-impact press-fitting method for stationary blade ring of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011161299.0A CN112548485A (en) | 2020-10-27 | 2020-10-27 | Non-impact press-fitting method for stationary blade ring of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112548485A true CN112548485A (en) | 2021-03-26 |
Family
ID=75042650
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011161299.0A Pending CN112548485A (en) | 2020-10-27 | 2020-10-27 | Non-impact press-fitting method for stationary blade ring of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112548485A (en) |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101464240A (en) * | 2009-01-14 | 2009-06-24 | 北京航空航天大学 | High temperature composite fatigue loading method and apparatus for turbine disc/blade joggled joint |
| US20110110783A1 (en) * | 2008-04-09 | 2011-05-12 | United Technologies Corporation | Trunnion hole repair utilizing interference fit inserts |
| CN102575581A (en) * | 2010-01-18 | 2012-07-11 | 三菱重工业株式会社 | Insert removal device for gas turbine stationary blade and insert removal method for gas turbine stationary blade |
| CN102837157A (en) * | 2012-08-23 | 2012-12-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Assembly and disassembly method for double-seam allowance matched super large size drum in heavy type gas turbine |
| CN202845609U (en) * | 2012-10-30 | 2013-04-03 | 哈尔滨汽轮机厂有限责任公司 | Gas turbine stationary guide blade inner ring vane false tongue hot riveting tool |
| CN205426522U (en) * | 2016-02-01 | 2016-08-03 | 浙江大学 | Heating of aeroengine blade flies disconnected device based on local heating principle |
| CN106091881A (en) * | 2016-06-15 | 2016-11-09 | 哈尔滨汽轮机厂有限责任公司 | Gas turbine fixed blade ring outer shroud dovetail groove survey tool and method |
| CN109108574A (en) * | 2017-06-23 | 2019-01-01 | 江苏亚飞机械制造有限公司 | A kind of induction heating hydraulic disassembling and assembling machine |
| CN109311132A (en) * | 2016-06-15 | 2019-02-05 | 奥林巴斯株式会社 | Joint method |
| CN111037208A (en) * | 2019-12-02 | 2020-04-21 | 芜湖东光大华机械制造有限公司 | Toothed ring heat seal device |
| CN111396140A (en) * | 2020-03-31 | 2020-07-10 | 中国航发动力股份有限公司 | Stationary blade ring with stopping structure and machining method thereof |
-
2020
- 2020-10-27 CN CN202011161299.0A patent/CN112548485A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110110783A1 (en) * | 2008-04-09 | 2011-05-12 | United Technologies Corporation | Trunnion hole repair utilizing interference fit inserts |
| CN101464240A (en) * | 2009-01-14 | 2009-06-24 | 北京航空航天大学 | High temperature composite fatigue loading method and apparatus for turbine disc/blade joggled joint |
| CN102575581A (en) * | 2010-01-18 | 2012-07-11 | 三菱重工业株式会社 | Insert removal device for gas turbine stationary blade and insert removal method for gas turbine stationary blade |
| CN102837157A (en) * | 2012-08-23 | 2012-12-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Assembly and disassembly method for double-seam allowance matched super large size drum in heavy type gas turbine |
| CN202845609U (en) * | 2012-10-30 | 2013-04-03 | 哈尔滨汽轮机厂有限责任公司 | Gas turbine stationary guide blade inner ring vane false tongue hot riveting tool |
| CN205426522U (en) * | 2016-02-01 | 2016-08-03 | 浙江大学 | Heating of aeroengine blade flies disconnected device based on local heating principle |
| CN106091881A (en) * | 2016-06-15 | 2016-11-09 | 哈尔滨汽轮机厂有限责任公司 | Gas turbine fixed blade ring outer shroud dovetail groove survey tool and method |
| CN109311132A (en) * | 2016-06-15 | 2019-02-05 | 奥林巴斯株式会社 | Joint method |
| CN109108574A (en) * | 2017-06-23 | 2019-01-01 | 江苏亚飞机械制造有限公司 | A kind of induction heating hydraulic disassembling and assembling machine |
| CN111037208A (en) * | 2019-12-02 | 2020-04-21 | 芜湖东光大华机械制造有限公司 | Toothed ring heat seal device |
| CN111396140A (en) * | 2020-03-31 | 2020-07-10 | 中国航发动力股份有限公司 | Stationary blade ring with stopping structure and machining method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 中国石油化工集团公司: "《炼油设备》", 31 December 2004, 中国石化出版社 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2325959B1 (en) | Spark plug | |
| CN102019540B (en) | Manufacturing method of fixed blade welding type clapboard of steam turbine | |
| CN101692590B (en) | Motor insulating bearing device and manufacturing method thereof | |
| CN109622770B (en) | Electrically-assisted sectional incremental forming device and method for titanium alloy sheet | |
| JP2013535335A (en) | Solid phase resistance welding to repair and fabricate airfoils | |
| EP1215005A3 (en) | Electrochemical machining process for forming surface roughness elements on a gas turbine shroud | |
| CN112548485A (en) | Non-impact press-fitting method for stationary blade ring of gas turbine | |
| EP2716975B1 (en) | Glow plug and method for manufacturing glow plug | |
| CN100452566C (en) | Electric contact crimping method and contact obtained according to said method | |
| KR102660358B1 (en) | Contact assembly for high-current applications | |
| CA2025299C (en) | Feeder lead wire of rotor for electric machine | |
| EP2166643A3 (en) | Method of manufacturing rotor for dynamoelectric machine | |
| US4784312A (en) | Method of producing a frame body for an electric motor | |
| CN110666323A (en) | Combined electrode suitable for resistance welding | |
| CN201429978Y (en) | Automobile horn | |
| CN109130195A (en) | A kind of fusion welding device of ball-type rolling bearing retainer | |
| JP2013204944A (en) | Glow plug, and method for manufacturing the same | |
| CN201799774U (en) | Silicone rubber padding electrode device for projection welding and positioning honey comb structure | |
| CN208783123U (en) | Electronic heater for electronic thermoregulator | |
| US4943687A (en) | Current collecting unit | |
| CN102069247B (en) | Tenon anti-corrosion method during blade electrochemical machining | |
| CN104753266A (en) | Motor rotor assembling process | |
| US20150240874A1 (en) | Method to mount a rolling bearing on a wind turbine shaft and a wind turbine bearing assembly | |
| CN202384860U (en) | Motor stator with locating plate | |
| CN210668931U (en) | Integrated collecting ring |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20210326 |