CN106271378A - Moving vane assembly method on turbine rotor - Google Patents
Moving vane assembly method on turbine rotor Download PDFInfo
- Publication number
- CN106271378A CN106271378A CN201510311736.5A CN201510311736A CN106271378A CN 106271378 A CN106271378 A CN 106271378A CN 201510311736 A CN201510311736 A CN 201510311736A CN 106271378 A CN106271378 A CN 106271378A
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- CN
- China
- Prior art keywords
- moving vane
- distance piece
- blade
- blade root
- moving
- Prior art date
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Classifications
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- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The moving vane assembly method on a kind of turbine rotor that the present invention provides, all moving vanes on turbine rotor are all standard films, and the method assembling all moving vanes includes: one), arrange a voussoir positioning the blade root of first blade in the race of impeller of steam turbine rotor wheel rim；Two) all moving vanes are navigated in described race one by one, and be provided with process gasket between adjacent two moving vanes；Three) all process gaskets are replaced to distance piece, make to plug a distance piece between the whole adjacent moving vane of circle moving vane, complete the assembling of moving vane.Whole circle moving vane in the present invention can all use rule blade, need not additionally design final blage, wheel rim also need not offer mounting groove, the installation of whole circle moving vane can be completed by process gasket and distance piece, not only reduce design cost, also reduce whole circle moving vane and the manufacturing cost of wheel rim simultaneously.
Description
Technical field
The present invention relates to the rotor fabrication techniques field of steam turbine, particularly relate to the moving vane assembling side on a kind of turbine rotor
Method.
Background technology
Steam turbine, as the core drive device in power station, is the rotary power machinery that the energy of steam is converted into mechanical power.
It is mainly used as prime mover of generating, it is possible to directly drive various pumps, blower fan, compressor and propeller for vessels etc..Can also profit
Steam discharge or intermediate extraction with steam turbine meet production and heat supply needs in life.
In steam turbine, by moving vane and rotor, steam thermal energy is efficiently converted into mechanical energy.Moving vane is arranged on rotor
On impeller or rotary drum, accept the high velocity air of nozzle blade cascade injection, the kinetic energy of steam is converted into mechanical energy, makes rotor rotate.
In prior art, the assembly method that moving vane is installed to impeller of rotor is to be rotated a certain angle by moving vane one by one,
The blade root making moving vane is inserted in the race of wheel rim, after blade root is inserted in race, then makes moving vane both rotate back to
Determine angle；Such installation method makes final blage when finally installing, and does not has unnecessary space to rotate, thus needs
Opening a mounting groove on wheel rim vertically, make mounting groove communicate with race, final blage is inserted directly in race by mounting groove,
Axially positioning final blage with pin, need to drive thread groove on blade root, thus final blage also needs to specialized designs, this is not
But the workload making moving vane design is big, manufacturing cost is high, in addition it is also necessary to process mounting groove at wheel rim, so that wheel rim
Manufacturing cost the highest.
Summary of the invention
The shortcoming of prior art in view of the above, the technical problem to be solved in the present invention is to provide one to make whole circle moving vane shape
Shape is identical and makes wheel rim need not offer mounting groove thus the assembly method of the moving vane of low cost of manufacture, to overcome existing skill
The drawbacks described above of art.
In order to solve above-mentioned technical problem, the moving vane assembly method on a kind of turbine rotor that the present invention provides, described steamer
All moving vanes on machine rotor are identical, are all standard films, and the method assembling all moving vanes includes:
One), a voussoir positioning the blade root of first blade is set in the race of described impeller of steam turbine rotor wheel rim；
Two), all moving vanes are navigated in described race one by one, particularly as follows: rotated to an angle by head blade, make first blade
Blade root insert in described race, then head blade is rotated back to first retainer, makes the side of head blade root be close at described wedge
On block, then process gasket on the opposite side pad of first blade root；Then second piece of moving vane it is installed, makes second piece of moving vane
The side of blade root is close to the process gasket of the opposite side of described first blade root, and at the opposite side pad of second piece of moving vane blade root
Upper process gasket；By that analogy, until secondary final blage is arranged in described race, finally described voussoir is taken from race
Go out, be further continued for being installed in race the blade root of final blage；
Three), after installing final blage, between blade root and the blade root of final blage of first blade, distance piece, described interval are inserted
The shape of sheet is consistent with the blade-root molded line of described moving vane, and the blade root of described first blade, interval are close in the side of described distance piece
The opposite side of sheet is close to the blade root of described final blage；The most again pull out the process gasket between final blage and secondary final blage, at end
Insert distance piece between blade and secondary final blage, make the both sides of the distance piece blade root respectively with secondary final blage and final blage be close to, suitable
All process gaskets are replaced to distance piece by sequence, till first blade is replaced with described second piece of interlobate process gasket,
The most all moving vanes have assembled.
Preferably, when the replacement of described process gasket is mounted to described distance piece, between the blade root of adjacent two described moving vanes
Gap can not meet described distance piece rotate to an angle insertion time, described distance piece is cut into two pieces along center line, the anglec of rotation
After be sequentially inserted in described race, then by spot welding two pieces are combined into a monoblock, and make each described distance piece and each described movable vane
It is adjacent between the blade root of sheet.
Preferably, after described distance piece is cut into two pieces along center line, it is inserted into adjacent two described moving vanes still without sufficient space
During gap between blade root, described distance piece being cut into three pieces, wherein intermediate mass is rectangular block, is first inserted directly into by two lateral mass
In described race, the most again intermediate mass is inserted between two lateral mass, then make intermediate mass and two lateral mass connect into one by sleeving and riveting technique
Body.
Preferably, described step 2) in when positioning described all moving vanes, the circumference of described race is divided at least three parts,
It is intended to the radiation of the moving vane after detecting all installations behind moving vane location in every part of corresponding race, determines that its installation is
No correctly.
Preferably, described step 3) in when replacing clipping room partition, the circumference of described race is divided at least three parts, every part
After the corresponding described process gasket in race is replaced by described distance piece, it is intended to all moving vanes after assay intervals sheet is replaced
Radiation, determine that its installation is the most correct.
Preferably, described process gasket is rectangular washer, and the thickness of described process gasket is less than the thickness of described distance piece.
Preferably, the thickness of described distance piece is 1mm 4mm.
As it has been described above, the moving vane assembly method on the turbine rotor of the present invention, have the advantages that
Whole circle moving vane can all use rule blade, it is not necessary to additionally designs final blage, and wheel rim also need not offer mounting groove,
The installation of whole circle moving vane can be completed by process gasket and distance piece, not only reduce design cost, also reduce simultaneously
Whole circle moving vane and the manufacturing cost of wheel rim.Furthermore, it is possible to make moving vane have certain pretwist amount, to guarantee movable vane
Sheet forms whole circle formation, substantially increases the integral rigidity of moving vane, improves security performance.
Accompanying drawing explanation
Fig. 1 is shown as the scheme of installation of the blade root of moving vane and the race of wheel rim.
Element numbers explanation
100 moving vanes
110 blade roots
120 blades
130 shrouds
200 races
Detailed description of the invention
Below by way of specific instantiation, embodiments of the present invention being described, those skilled in the art can be by disclosed by this specification
Content understand other advantages and effect of the present invention easily.The present invention can also be added by the most different detailed description of the invention
To implement or application, the every details in this specification can also be based on different viewpoints and application, in the essence without departing from the present invention
Various modification or change is carried out under god.
Refer to Fig. 1.It should be noted that the diagram provided in the present embodiment illustrates that the present invention's is basic the most in a schematic way
Conception, the most graphic in component count, shape and size time only display with relevant assembly in the present invention rather than is implemented according to reality
Drawing, during its actual enforcement, the kenel of each assembly, quantity and ratio can be a kind of random change, and its assembly layout kenel is also
It is likely more complexity.
The moving vane assembly method on a kind of turbine rotor that the present invention provides, the molded line of all moving vanes on turbine rotor
Thickness is identical, is illustrated in figure 1 the schematic diagram after moving vane is installed, and wherein moving vane 100 includes blade 120 and blade root 110,
With the race 200 that the blade root 110 of moving vane is inserted on wheel rim, it is additionally provided with all movable vanes on the top of blade 120
The shroud 130 that sheet is connected.Wherein, the method assembling all moving vanes includes:
One), a voussoir positioning the blade root 110 of first blade is set in the race 200 of impeller of steam turbine rotor wheel rim；
Two), all moving vanes are navigated in race 200 one by one, particularly as follows: rotated to an angle by head blade, make first blade
Blade root insert in race 200, then head blade is rotated back to first retainer, makes the side of head blade root be close on voussoir,
Process gasket on the opposite side pad of first blade root again；Then second piece of moving vane it is installed, makes second piece of moving vane blade root
Side is close to the process gasket of the opposite side of first blade root, and craftwork pad on the opposite side pad of second piece of moving vane blade root
Sheet；By that analogy, until being arranged in race 200 by secondary final blage, final blage is finally installed, by described voussoir from race
Take out in 200, be further continued for rotating to an angle final blage, make the blade root of final blage be inserted in race 200, then by end
Blade rotates back to first retainer, when not having enough spaces to install the blade root of final blage in race, can be carried out by final blage
Rounding and cutting；
Three), after installing final blage, between blade root and the blade root of final blage of first blade, distance piece is inserted, distance piece
Shape is consistent with the blade-root molded line of moving vane, and the blade root of first blade is close in the side of distance piece, and the opposite side of distance piece is close to end
The blade root of blade；The most again pull out the process gasket between final blage and secondary final blage, insert between final blage and secondary final blage
Entering distance piece, make the both sides of the distance piece blade root respectively with secondary final blage and final blage be close to, all process gaskets are replaced by order
Sheet at interval, till first blade and second piece of interlobate process gasket are replaced, the most all moving vanes have assembled.
In the present invention, the molded line thickness of all moving vanes is identical, and the most whole circle moving vane can all use rule blade, it is not necessary to additionally sets
Meter final blage, wheel rim also need not be offered mounting groove, can be completed the peace of whole circle moving vane by process gasket and distance piece
Dress, not only reduces design cost, also reduces whole circle moving vane and the manufacturing cost of wheel rim simultaneously.Furthermore, it is possible to
Make moving vane have certain pretwist amount, to guarantee that moving vane forms whole circle formation, substantially increase the integral rigidity of moving vane,
Improve security performance.
The present invention when process gasket is replaced to distance piece, the replacement of process gasket order and step 2) in the peace of process gasket
Dress order is contrary, even positions each moving vane, then step 3 in step 2 the most successively) in depend on counterclockwise
The each process gasket of secondary replacement.
For preferably process gasket being replaced to distance piece, above-mentioned steps three) in, it is mounted to interval being replaced by each process gasket
During sheet, if the gap between the blade root of adjacent two moving vanes can not meet distance piece rotate to an angle insertion time, by distance piece
It is cut into two pieces along center line, is sequentially inserted in race after the anglec of rotation, then by spot welding, two pieces are combined into a monoblock, and make each
It is adjacent between the blade root of partition and each moving vane.And it is inserted into adjacent after distance piece is cut into two pieces along center line still without sufficient space
During gap between the blade root of two moving vanes, distance piece being cut into three pieces, wherein intermediate mass is rectangular block, first by two lateral mass
It is inserted directly in race, the most again intermediate mass is inserted between two lateral mass, then make intermediate mass and two lateral mass connect by sleeving and riveting technique
Integral.
For improve whole circle moving vane installation accuracy, above-mentioned steps two) in position all moving vanes time, the circumference of race is divided equally
Become at least three arc length, behind the moving vane location in the race corresponding to each arc length, be intended to the moving vane after detecting all installations
Radiation is the most consistent.As the circumference of race being divided into three parts, the radian of i.e. every part is 120 °, installs one 120 °
During corresponding race, i.e. the moving vane after all installations is carried out primary radiation detection, determine that its installation is the most correct.With
Sample, when replacing clipping room partition in step 3, is also divided at least three arc length, corresponding to each arc length by the circumference of race
Race in process gasket replaced by distance piece after, be intended to the radiation of all moving vanes after assay intervals sheet is replaced, determine
Its installation is the most correct.The generally rectangular cross-section pad of above-mentioned process gasket, the thickness of process gasket is less than the thickness of distance piece.Interval
The thickness of sheet is 1mm 4mm.
In sum, the moving vane assembly method on the turbine rotor of the present invention, its moving vane can all use rule blade,
Need not additionally design final blage, wheel rim also need not offer mounting groove, can complete whole circle by process gasket and distance piece
The installation of moving vane, not only reduces design cost, also reduces whole circle moving vane and the design of wheel rim and system simultaneously
Cause this.Furthermore, it is possible to make moving vane have certain pretwist amount, to guarantee that moving vane forms whole circle formation, greatly increase
The integral rigidity of moving vane, improves security performance.So, the present invention effectively overcome various shortcoming of the prior art and
Tool high industrial utilization.
The principle of above-described embodiment only illustrative present invention and effect thereof, not for limiting the present invention.Any it is familiar with this skill
Above-described embodiment all can be modified under the spirit and the scope of the present invention or change by the personage of art.Therefore, such as
All that in art, tool usually intellectual is completed under without departing from disclosed spirit and technological thought etc.
Effect is modified or changes, and must be contained by the claim of the present invention.
Claims (7)
1. the moving vane assembly method on a turbine rotor, it is characterised in that all moving vanes on described turbine rotor are identical,
Being all standard film, the method assembling all moving vanes includes:
One), a voussoir positioning the blade root of first blade is set in the race of described impeller of steam turbine rotor wheel rim；
Two), all moving vanes are navigated in described race one by one, particularly as follows: rotated to an angle by head blade, make first blade
Blade root insert in described race, then head blade is rotated back to first retainer, makes the side of head blade root be close at described wedge
On block, then process gasket on the opposite side pad of first blade root；Then second piece of moving vane it is installed, makes second piece of moving vane
The side of blade root is close to the process gasket of the opposite side of described first blade root, and at the opposite side pad of second piece of moving vane blade root
Upper process gasket；By that analogy, until secondary final blage is arranged in described race, finally described voussoir is taken from race
Go out, be further continued for being installed in race the blade root of final blage；
Three), after installing final blage, between blade root and the blade root of final blage of first blade, distance piece, described distance piece are inserted
Shape consistent with the blade-root molded line of described moving vane, the blade root of described first blade, interval are close in the side of described distance piece
The opposite side of sheet is close to the blade root of described final blage；The most again pull out the process gasket between final blage and secondary final blage,
Inserting distance piece between final blage and secondary final blage, the both sides making distance piece are tight with the blade root of secondary final blage and final blage respectively
Patch, all process gaskets are replaced to distance piece by order, until first blade is replaced with described second piece of interlobate process gasket
Only being changed to, the most all moving vanes have assembled.
Moving vane assembly method on turbine rotor the most according to claim 1, it is characterised in that: by described process gasket
When replacement is mounted to described distance piece, the gap between the blade root of adjacent two described moving vanes can not meet the rotation of described distance piece
When turning certain angle insertion, described distance piece is cut into two pieces along center line, is sequentially inserted into after the anglec of rotation in described race, then
By spot welding, two pieces are combined into a monoblock, and make to be adjacent between the blade root of each described distance piece and each described moving vane.
Moving vane assembly method on turbine rotor the most according to claim 2, it is characterised in that: when in described distance piece edge
Line is inserted into the gap between the blade root of adjacent two described moving vanes still without sufficient space after being cut into two pieces time, between described
Partition is cut into three pieces, and wherein intermediate mass is rectangular block, is first inserted directly in described race by two lateral mass, the most again by centre
Block inserts between two lateral mass, then makes intermediate mass and two lateral mass link into an integrated entity by sleeving and riveting technique.
Moving vane assembly method on turbine rotor the most according to claim 1, it is characterised in that: described step 2) in fixed
During the described all moving vanes in position, the circumference of described race is divided at least three parts, the moving vane in every part of corresponding race
It is intended to the radiation of the moving vane after detecting all installations behind location, determines that its installation is the most correct.
Moving vane assembly method on turbine rotor the most according to claim 1, it is characterised in that: described step 3) in replace
When changing clipping room partition, the circumference of described race is divided at least three parts, the described craftwork pad in every part of corresponding race
After sheet is replaced by described distance piece, it is intended to the radiation of all moving vanes after assay intervals sheet is replaced, determines whether it installs
Correctly.
Moving vane assembly method on turbine rotor the most according to claim 1, it is characterised in that: described process gasket is square
Shape pad, the thickness of described process gasket is less than the thickness of described distance piece.
Moving vane assembly method on turbine rotor the most according to claim 1, it is characterised in that: the thickness of described distance piece
For 1mm 4mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510311736.5A CN106271378B (en) | 2015-06-09 | 2015-06-09 | Movable vane piece assembly method on turbine rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510311736.5A CN106271378B (en) | 2015-06-09 | 2015-06-09 | Movable vane piece assembly method on turbine rotor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106271378A true CN106271378A (en) | 2017-01-04 |
| CN106271378B CN106271378B (en) | 2018-08-21 |
Family
ID=57658717
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510311736.5A Active CN106271378B (en) | 2015-06-09 | 2015-06-09 | Movable vane piece assembly method on turbine rotor |
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| Country | Link |
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| CN (1) | CN106271378B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108895030A (en) * | 2018-08-06 | 2018-11-27 | 无锡市海星船舶动力有限公司 | The compressor impeller of blade detachable type |
| CN109779695A (en) * | 2019-02-01 | 2019-05-21 | 哈尔滨汽轮机厂有限责任公司 | A kind of assembly method for the small enthalpy drop blade of steam turbine |
| CN109931112A (en) * | 2019-04-28 | 2019-06-25 | 杭州汽轮机股份有限公司 | A kind of free blade construction of steam turbine and its assembly method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2772854A (en) * | 1951-02-27 | 1956-12-04 | Rateau Soc | Vibration damping means for bladings of turbo-machines |
| US3545882A (en) * | 1968-01-17 | 1970-12-08 | Rolls Royce | Pressure exchanger rotor |
| CN1529788A (en) * | 2002-06-07 | 2004-09-15 | 三菱重工业株式会社 | Turbine bucket assembly and its assembling method |
| CN101517200A (en) * | 2006-09-25 | 2009-08-26 | 西门子公司 | Turbine rotor with locking plates and corresponding assembly method |
-
2015
- 2015-06-09 CN CN201510311736.5A patent/CN106271378B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2772854A (en) * | 1951-02-27 | 1956-12-04 | Rateau Soc | Vibration damping means for bladings of turbo-machines |
| US3545882A (en) * | 1968-01-17 | 1970-12-08 | Rolls Royce | Pressure exchanger rotor |
| CN1529788A (en) * | 2002-06-07 | 2004-09-15 | 三菱重工业株式会社 | Turbine bucket assembly and its assembling method |
| CN101517200A (en) * | 2006-09-25 | 2009-08-26 | 西门子公司 | Turbine rotor with locking plates and corresponding assembly method |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108895030A (en) * | 2018-08-06 | 2018-11-27 | 无锡市海星船舶动力有限公司 | The compressor impeller of blade detachable type |
| CN109779695A (en) * | 2019-02-01 | 2019-05-21 | 哈尔滨汽轮机厂有限责任公司 | A kind of assembly method for the small enthalpy drop blade of steam turbine |
| CN109931112A (en) * | 2019-04-28 | 2019-06-25 | 杭州汽轮机股份有限公司 | A kind of free blade construction of steam turbine and its assembly method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106271378B (en) | 2018-08-21 |
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