CN1990165A - Renovation technique of combustion turbine retaining ring - Google Patents
Renovation technique of combustion turbine retaining ring Download PDFInfo
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- CN1990165A CN1990165A CN 200510130877 CN200510130877A CN1990165A CN 1990165 A CN1990165 A CN 1990165A CN 200510130877 CN200510130877 CN 200510130877 CN 200510130877 A CN200510130877 A CN 200510130877A CN 1990165 A CN1990165 A CN 1990165A
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- loose piece
- retaining ring
- combustion turbine
- pin
- renovation technique
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Abstract
The invention provides a gas turbine retaining ring repair art, its steps are as follows: laser fusion covering repair of cracks and defects parts and the parameters are: the fusion pool size 2 ~ 5mm diameter when laser fusion covering, depth is 0.1 to 0.2mm, the heating time is 0.001 ~ 0. 1s; processing overall inner round with special equipments, special equipment includes base 7, loose piece 4, draw rod 2, press plate 12 and pin 8; loose piece 4 is fixed on the base 7 with bolt 5 and positioned with the positioning pin 6; screw bolt 9 is welded on the loose piece 4, press plate 12 presses the loose piece 4 through screw cap 10 and screw bolt 9; the pin 8 insert into the hole of draw rod 2 through loose piece and moving pin 8 with adjusting screw cap 1.The advantages of the process are: achieving repair of retaining rings, covering the blank of retaining rings only can be prepared and not be repaired, the adaptability of the repair process is strong, operation is simple, thermal deformation is small, standard capability is strong, and the processing error is small after machining and installing .
Description
Technical field
The present invention relates to the maintenance technique of gas turbine, provide a kind of maintenance process of combustion turbine retaining ring and machine to add especially and used frock.
Background technology
Because gas turbine power generation has that factory building is little, floor space is little, the construction period is short, disposal of pollutants is low, reduced investment, efficient height, start fast, not water or few water, can extraneous power supply, advantage such as equipment is simple, maintenance cost is lower, easy to operate, in nearly more than ten years, China has successively set up tens of gas turbines and circulating power station, according to incompletely statistics, national so far total installation of generating capacity has surpassed 1,000 ten thousand KW, and share shared in power industry is increasing.
Gas turbine is that the heat energy that fuel combustion produces is directly changed into the externally swinging dynamic power machine of output of mechanical power, is made up of compressor, combustion chamber and turbine.Turbine is the significant components that in the gas turbine energy of high-temperature fuel gas is transformed into mechanical power.First order jet nozzle is the critical piece of turbine acting, is made up of parts such as interior ring, outer shroud, blades.Retaining ring is fixed on stator blade on the cylinder with holding ring.Retaining ring is the sector structure, is contained in the movable vane top.Adopting the sector structure, is in order to solve thermal expansion and hot centering problem.The segments of sector, the fuel gas temperature height at the first order place of turbine, segments is many, and the level of back is along with the reduction segments of fuel gas temperature reduces.Unit model difference, segments also is not quite similar.Each sector is used radially pin location, and the end face that sector is adjacent is made rectangular teeth and embedded mutually, and with protective ring front and back leak gas, increment leaves the gap for its circumferential thermal expansion.Except that the one-level retaining ring, other other retaining ring of level also is provided with diaphragm seal, in case leak gas from increment end play.
Because the inlet gas temperature reaches as high as about 1500 ℃, has produced a series of problems that Yin Gaowen causes thus, as thermal expansion, hot centering, thermal shock and heat erosion etc.Retaining ring also produces fatigue crack thus, and piece is fallen in the serious meeting of chapping.The retaining ring that the user generally takes more to renew solves problem.
At present, the most of import unit that adopts of the gas turbine of China, though retaining ring can be made at home, the manufacturing cycle was also taken about 3～6 months, adopted heat-resisting alloy steel in addition, and manufacturing cost is higher, and a cover is worth about more than 40 ten thousand RMB.So this just brings the long in time limit and cost of making again than higher.
Summary of the invention
The object of the present invention is to provide a kind of combustion turbine retaining ring renovation technique with actual effect.
The invention provides a kind of renovation technique of combustion turbine retaining ring, it is characterized in that processing step is as follows:
1) the laser melting coating reparation of crackle and defect: the parameter in the specific operation process is: the pool size diameter is that 2～5mm, the degree of depth are 0.1～0.2mm during laser melting coating, and be 0.001～0.1s heat time heating time; Can guarantee little deflection well like this, other position is not had obvious influence, and repair easy;
2) circle in the whole processing: combustion turbine retaining ring is made up of a plurality of fan-shaped section, embed mutually with the rectangular teeth on each fan-shaped section adjacent side, pendulum circularizes, process for 4 li so each fan-shaped section of combustion turbine retaining ring must be bumped into the loose piece of special tooling respectively, to guarantee to have precision after less mismachining tolerance and the higher reparation.
In the renovation technique of combustion turbine retaining ring provided by the invention, special tooling mainly comprises base 7, loose piece 4, pull bar 2, pressing plate 12 and sells 8; Loose piece 4 usefulness bolts 5 are fixed on the base 7, with alignment pin 6 location; Screw rod 9 is welded on the loose piece 4, and pressing plate 12 is pressed on the loose piece 4 by nut 10 and screw rod 9; Pin 8 inserts in the hole of pull bars 2, and pull bar 2 passes loose piece 4, and with adjusting nut 1 moving pin 8.
In the renovation technique of combustion turbine retaining ring provided by the invention, before the laser melting coating reparation of described crackle and defect, can carry out the cleaning of crackle and defect.
In the renovation technique of combustion turbine retaining ring provided by the invention, in described whole processing, can carry out coating spraying behind the circle.
The renovation technique of combustion turbine retaining ring provided by the invention, its advantage is: realized retaining ring is repaired, domestic can't the maintenance before having remedied, can only make the blank of retaining ring, and this renovation technique adaptability is strong, easy and simple to handle, thermal deformation is little, standardization is strong, use machined dress back mismachining tolerance little, has very big value.
Description of drawings
Fig. 1 is the assembling schematic diagram of combustion turbine retaining ring machined dress;
Fig. 2 is that the M-M of combustion turbine retaining ring machined dress is to profile;
Fig. 3 is that the K-K of combustion turbine retaining ring machined dress is to profile.
The specific embodiment
Combustion turbine retaining ring is made up of a plurality of fan-shaped section, embeds mutually with the rectangular teeth on each fan-shaped section adjacent side, and pendulum circularizes.The maintenance process step of combustion turbine retaining ring is as follows:
1, combustion turbine retaining ring is carried out Non-Destructive Testing.
2, the crackle and the defect of combustion turbine retaining ring fan-shaped section are cleared up.Crackle will be cleaned out.
3, crackle and defect after the cleaning are controlled the laser melting coating reparation automatically, the about 3mm of laser melting coating molten bath diameter, pool depth is about 0.1～0.2mm, and be 0.001～0.1s heat time heating time.
4, each fan-shaped section of the combustion turbine retaining ring after the cladding reparation is bumped into 4 li of the loose pieces of special tooling respectively, carries out mechanical correction of the flank shape processing, described mechanical correction of the flank shape processing is that the combustion turbine retaining ring after utilizing frock to cladding carries out vertical lathe.
Special tooling mainly comprises base 7, loose piece 4, pull bar 2, pressing plate 12 and sells 8; Loose piece 4 usefulness bolts 5 are fixed on the base 7, with alignment pin 6 location; Screw rod 9 is welded on the loose piece 4, and pressing plate 12 is pressed in combustion turbine retaining ring on the base 7 by nut 10 (nut has packing ring 11 10 times) and screw rod 9, guarantees the axial location of combustion turbine retaining ring fan-shaped section; Pin 8 inserts in the hole of the hole of combustion turbine retaining rings and pull bar 2, and pull bar 2 passes loose piece 4, and with adjusting nut 1 (nut has packing ring 31 time) moving pin 8, the location radially of assurance combustion turbine retaining ring fan-shaped section.
5, the combustion turbine retaining ring after the correction of the flank shape is detected, detect content and comprise Non-Destructive Testing, appearance and size detection etc.
6, coating spraying.
Claims (5)
1, a kind of renovation technique of combustion turbine retaining ring is characterized in that processing step is as follows:
1) the laser melting coating reparation of crackle and defect: the parameter in the specific operation process is: the pool size diameter is that 2～5mm, the degree of depth are 0.1～0.2mm during laser melting coating, and be 0.001～0.1s heat time heating time;
2) circle in the whole processing: loose piece (4) lining that each fan-shaped section of combustion turbine retaining ring is bumped into special tooling respectively processes.
2, according to the renovation technique of the described combustion turbine retaining ring of claim 1, it is characterized in that: mainly comprise base (7), loose piece (4), pull bar (2), pressing plate (12) and pin (8) at described special tooling; Loose piece (4) is fixed on the base (7) with bolt (5), with alignment pin (6) location; Screw rod (9) is welded on the loose piece (4), and pressing plate (12) is pressed on the loose piece (4) by nut (10) and screw rod (9); Pin (8) inserts in the hole of pull bars (2), and pull bar (2) passes loose piece (4), and with adjusting nut (1) moving pin (8).
3, according to the renovation technique of claim 1 or 2 described combustion turbine retaining rings, it is characterized in that: before the laser melting coating reparation of described crackle and defect, carry out the cleaning of crackle and defect.
4, according to the renovation technique of claim 1 or 2 described combustion turbine retaining rings, it is characterized in that: in described whole processing, carry out coating spraying behind the circle.
5, according to the renovation technique of the described combustion turbine retaining ring of claim 3, it is characterized in that: in described whole processing, carry out coating spraying behind the circle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2005101308773A CN100462189C (en) | 2005-12-26 | 2005-12-26 | Renovation technique of combustion turbine retaining ring |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2005101308773A CN100462189C (en) | 2005-12-26 | 2005-12-26 | Renovation technique of combustion turbine retaining ring |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1990165A true CN1990165A (en) | 2007-07-04 |
| CN100462189C CN100462189C (en) | 2009-02-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2005101308773A Expired - Fee Related CN100462189C (en) | 2005-12-26 | 2005-12-26 | Renovation technique of combustion turbine retaining ring |
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| Country | Link |
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| CN (1) | CN100462189C (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102021562B (en) * | 2009-09-17 | 2012-07-11 | 沈阳大陆激光技术有限公司 | Method for repairing damage of wheel disc of turbocharger of internal combustion engine |
| CN104511856A (en) * | 2013-09-30 | 2015-04-15 | 哈尔滨飞机工业集团有限责任公司 | Rotating seal ring detection tooling |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5269057A (en) * | 1991-12-24 | 1993-12-14 | Freedom Forge Corporation | Method of making replacement airfoil components |
| US5732468A (en) * | 1996-12-05 | 1998-03-31 | General Electric Company | Method for bonding a turbine engine vane segment |
| CN1185074C (en) * | 2001-06-15 | 2005-01-19 | 沈阳大陆激光技术有限公司 | Laser repairing process for failed gas compressor rotor |
| US20040086635A1 (en) * | 2002-10-30 | 2004-05-06 | Grossklaus Warren Davis | Method of repairing a stationary shroud of a gas turbine engine using laser cladding |
| CN100505476C (en) * | 2004-03-26 | 2009-06-24 | 沈阳大陆激光技术有限公司 | Electric power generator, steam turbine rotor spindle repaired by laser and repairing method thereof |
-
2005
- 2005-12-26 CN CNB2005101308773A patent/CN100462189C/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102021562B (en) * | 2009-09-17 | 2012-07-11 | 沈阳大陆激光技术有限公司 | Method for repairing damage of wheel disc of turbocharger of internal combustion engine |
| CN104511856A (en) * | 2013-09-30 | 2015-04-15 | 哈尔滨飞机工业集团有限责任公司 | Rotating seal ring detection tooling |
| CN104511856B (en) * | 2013-09-30 | 2016-08-24 | 哈尔滨飞机工业集团有限责任公司 | Rotating ring detecting tool |
Also Published As
| Publication number | Publication date |
|---|---|
| CN100462189C (en) | 2009-02-18 |
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Granted publication date: 20090218 Termination date: 20111226 |