CN101680304A - Arrangement for axially securing rotating blades in a rotor, and gas turbine having such an arrangement - Google Patents
Arrangement for axially securing rotating blades in a rotor, and gas turbine having such an arrangement Download PDFInfo
- Publication number
- CN101680304A CN101680304A CN200880016327.0A CN200880016327A CN101680304A CN 101680304 A CN101680304 A CN 101680304A CN 200880016327 A CN200880016327 A CN 200880016327A CN 101680304 A CN101680304 A CN 101680304A
- Authority
- CN
- China
- Prior art keywords
- groove
- working blade
- brake component
- sealing
- rotor
- 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.)
- Granted
Links
- 238000007789 sealing Methods 0.000 claims abstract description 51
- 238000013461 design Methods 0.000 claims description 10
- 238000003780 insertion Methods 0.000 claims description 3
- 230000037431 insertion Effects 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 238000012856 packing Methods 0.000 claims description 3
- 201000007094 prostatitis Diseases 0.000 claims 3
- 230000000903 blocking effect Effects 0.000 abstract 2
- 238000006073 displacement reaction Methods 0.000 abstract 2
- 239000007789 gas Substances 0.000 description 7
- 230000002349 favourable effect Effects 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000659 freezing mixture Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 238000006116 polymerization reaction Methods 0.000 description 1
- 238000007781 pre-processing Methods 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
Images
Classifications
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/30—Retaining components in desired mutual position
- F05B2260/301—Retaining bolts or nuts
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to an arrangement (10) of rotating blades (14) in a rotor, having a shaft collar (21), on the outer circumference (52) of which blade retaining grooves (12) are provided, whereinrotating blades (14) are disposed in said blade retaining grooves, having a projection disposed on an end side surface (56) of the shaft collar (21) in the region of the retaining grooves, wherein acircumferential groove (20) being open radially toward the outside is provided in said projection, and having securing grooves (24) that are radially open toward the inside disposed in each rotating blade (14), said securing grooves being positioned radially opposite the circumferential groove (20), wherein sheet metal-shaped sealing elements (42), each engaging in the circumferential groove (20)and in the securing groove (24), are provided for axially securing the rotating blades (14). In order to propose an alternative securing of the sealing elements (42) against displacement in the circumferential direction within the groove (20), the invention provides that a blocking element (67) inserted in a recess (65) from the end side of the shaft collar (21) blocks the displacement path of thesealing element (42). In order for the blocking element (67) to be secured against unintentional releasing, the same is fastened on the rotor disk by means of a plastic deformation.
Description
Technical field
The present invention relates to a kind of working blade at epitrochanterian axial relief device, comprise an axle collar, on its excircle, be provided with axially extended working blade fixed groove along rotor, working blade is installed in these working blade fixed grooves by the blade root corresponding with the working blade fixed groove respectively, also comprise a projection that in working blade fixed groove zone, is located at the distolateral side of the axle collar, in projection, be provided with radially outwardly open annular groove, and comprise and be laid in each working blade radially the safety groove of opening inwardly, it is radially mutually opposed with annular groove respectively, wherein, axial relief for working blade, the lamellar Sealing of insertion is set at annular groove with in safety groove respectively, and these Sealings are along circumferentially constituting distolateral seal ring, wherein, for fixing seals prevents that at least one Sealing is porose along circumferentially moving.The present invention relates to a kind of gas turbine in addition with this device.
Background technique
The rotor of gas turbine is known, and wherein, the working blade of installing in the working blade fixed groove on excircle prevents to move axially by diaphragm seal.For example known in this respect by US3957393, this diaphragm seal by riveted fixing on rotor.
Known in addition device according to Fig. 1.Fig. 1 represents a kind of plan view of this type of device, and Fig. 2 represents the cross-sectional view according to cutting line II-II among Fig. 1.Will prevent for axially movable working blade 14 in its working blade fixed groove 12 for each, adopt two diaphragm seals 16 that a small amount of is overlapping as Sealing, they respectively block half of 12 distolateral mouthfuls of working blade fixed grooves.Each diaphragm seal 16 its inners 18 are radially inserted one and are located in the distolateral circular groove 20 of rotor disk 19, with and radially outer end 22 insert in the safety groove 24 on the downside 26 of a platform 28 that is located at working blade 14.For preventing that any diaphragm seal 16 from moving along circumferential U, on each diaphragm seal 16, fix a straight line shape lath 30, it is basically along the radially extension of rotor 23.Its of each lath 30 outer end 32 radially terminates as a tip 34 of polymerization gradually.On the platform 28 of working blade 14, there is the seamed edge of splaying 36, wherein, the opposed seamed edge 36 of the moving turbine blade 14 of per two direct neighbors, form a space that comes to a point gradually 38, the tip 34 of lath 30 can be stretched into and abut in this space 38, prevents that diaphragm seal 16 from moving along circumferential U.
For lath 30 is fixed on the diaphragm seal 16, on diaphragm seal 16, be provided with two open parallel 40, the lath 30 that has been pre-bent to U-shaped is packed into by them.Lath 30 and most advanced and sophisticated 34 opposed ends 41 before being installed in diaphragm seal 16 on the rotor disk 19, have bent to the position that is used for fixing lath 30 shown in Figure 2.
After working blade 14 is installed on the rotor disk 19, diaphragm seal 16 with preassembled lath 30, is penetrated in the annular groove 20 that is located at continued circling on the rotor disk 19 in succession and is located in the safety groove 24 on platform 28 downsides 26.Diaphragm seal 16 becomes along the circumferential registration of annular groove 20, makes each lath 30 mutually opposed with a space 38.Then, the tip 34 of lath 30 bend in this space 38, in case diaphragm seal 16 moves along circumferential U.
Because lath requires only to allow bending once based on very high machinery, so under the situation of maintenance and replacing working blade, must replace the crooked lath of crossing with new lath.In addition, be located at the opening that is used to install lath in the diaphragm seal and weakened diaphragm seal.
Summary of the invention
The technical problem to be solved in the present invention is to provide another kind to prevent the device that the dangerous ground of Sealing circumferentially moves, the time that it can shorten assembling and decompose.Another technical problem that will solve of the present invention is to prepare a kind of gas turbine with this device.
Relate to the technical problem of working blade at epitrochanterian axial relief device, the feature by claim 1 is solved.
The present invention regulation prevents Sealing along the device that circumferentially moves in this type of device, comprise a brake component that is located at fixed-site in hole in the Sealing and groove that is located at axle collar side and this hole general alignment and pack into a groove and the hole.The present invention is different with design so far, and a lath shape sealing ground that connects with the Sealing hook inserts in the space there.Replace lath now and adopt brake component, it can insert and be located in the distolateral groove of the axle collar.Brake component locking Sealing, extends transverse to the annular groove ground that Sealing wherein is installed because it is contained in the zone of Sealing along circumferential moving, and meanwhile inserts in the hole that is located on the Sealing.Sealing along annular groove in a small amount with tolerable gap, only just possible along the width of circumferentially observing along the width of circumferentially seeing greater than brake component in the hole.
Use in a kind of hole of inserting Sealing and be fixed in the brake component of the axle collar on distolateral, can reach Sealing and especially reliably and simply prevent the axial relief that moves along circumferentially by the ca(u)lk that makes its plastic deformation.In addition, assembling can realize rapidly and easily.For this reason, with a kind of suitable caulking tool, for example hammer and chisel class instrument, make the distolateral plastic deformation of brake component, thereby brake component is abutted in the groove under pressure, cause a kind of friction very reliably to be connected between the wall of groove and brake component thus, this friction connection stops when gas turbine operation brake component to be thrown off unintentionally reliably.In order to dismantle brake component, the texturing zone of brake component can be removed by polishing, and unclamps the friction connection thus to take out brake component.
Adopt in addition according to design of the present invention and cancelled the opening that weakens Sealing so far, and these openings are used for safety plate is fixed on Sealing.Therefore further increase the rigidity and the sealing effect thereof of Sealing.
Favourable design is described in the dependent claims.
By favourable design of the present invention, brake component with regard to its state of packing in the zone of groove cross section be designed to wedge shape, and comprise one in addition from the distolateral pin that stretches out, it can insert in the hole of Sealing.Wedge shape by brake component and corresponding to the wedge shape of the groove of this wedge shape has been stipulated brake component definite position in rotor.In addition, select the orientation of the wedge shape of groove like this, make the sidewall of walking close to mutually, just as the corresponding with it outside finger in side of brake component.Thus, the brake component of wedge shape is outwards attempted under centrifugal action, further wedging or clamping in groove in this case, and this has further strengthened the side and has been connected with friction between the sidewall, and the more difficult generation of disengagement unintentionally that makes brake component.A kind of ultra-safe device consequently can be provided thus.
By another design of the present invention, the radially outside opening of groove of brake component is installed.In this case, the brake component that is installed in the groove can plastic deformation on the circumference with regard to rotor, replaces distolateral distortion.If the additional recess that is located on the circumference also is provided in the sidewall of groove this moment, the part deformable material of brake component can be dodged in recess, then except clamping brake component, also additionally constitutes a kind of shape sealing and connects, and is used for the fixed-site of brake component.Prevent especially reliably that thus brake component from losing.
By another favourable design, the groove that extends along rotor axial in axle collar side is arranged as, and it is extended in the annular groove always.The rotor disk of avoiding weakening the axle collar in this case or preferably constituting the axle collar.Therefore, will be located at hole on the Sealing built in Sealing the inner radially.This zone of Sealing heating when work is minimum, so do not influence the rigidity and the high-temperature capability of Sealing because of described hole.
Confirmed already particularly advantageously to be that per second or each Sealing all had the safty device that prevent that Sealing from moving.Described rightly device adopts on the land-based gas turbine engine rotor of axial flow.
Description of drawings
The various embodiments of representing by accompanying drawing illustrates elaboration the present invention below.By drawing other advantages and feature in the described explanation.Wherein:
Fig. 1 represents that working blade according to prior art is at epitrochanterian axial relief device;
Fig. 2 represents the cross section according to cutting line II-II among Fig. 1;
Fig. 3 represents rotor disk and is contained in the partial top view of the working blade above it, by the axial relief device of Sealing as working blade;
Fig. 4 represents the perspective view according to brake component of the present invention;
Fig. 5 represents according to pack into the perspective view of the brake component in the rotor of second kind of design.
Embodiment
Fig. 3 represents the local distolateral plan view of the axle collar 21 that is made of rotor disk 19 of gas turbine rotor 23.Can be around running shaft 50 rotor rotated 23, the working blade fixed groove 12 that distributes along circumference U, extend vertically be arranged on its excircle 52, wherein can insert working blade 14 and the blade roots 54 12 corresponding designs of working blade fixed groove respectively.Be illustrated in the working blade fixed groove 12 of Fig. 3 central authorities and inserted a working blade 14.The same with the prior art of representing among Fig. 1 and Fig. 2, distolateral or on the distolateral side 56 of the axle collar 21 at rotor disk 19, lay a projection 58 or an expanding section that extends vertically, it has radially outwardly open annular groove 20.Annular groove 20 for example is located at than working blade fixed groove 12 radially more by on the position of lining.Working blade 14 has a platform 28 that is between blade root 54 and the profile blade, is provided with towards the safety groove 24 of annular groove 20 openings also mutually opposed with it at its downside.According to the similar mode of prior art, Sealing 42 inserts in the continuous annular groove 20 and safety groove 24, it prevents working blade 14 moving along the working blade fixed groove.
Different with above-mentioned prior art, Sealing 42 blocks the distolateral hole of one of them working blade fixed groove 12 fully.Therefore always only a working blade 14 is fixing by one of them Sealing 42, prevents that it from moving along working blade fixed groove 12.
But Sealing 42 also can circumferentially be the Sealing of two direct neighbors to be distinguished half ground insert in the safety groove 24 of working blade 14 as prior art.This moment, two adjacent Sealings prevented that the working blade 14 from moving axially.
Be similar to prior art, the overlapping slightly respectively Sealing 42 of a circle that is fully assembled forms a seal ring, and it separates with another the zone 37 that can flow through freezing mixture in the zone 39 that can flow into hot combustion gas in some cases.
Itself do not move along circumferential in order to ensure Sealing 42, be provided with a hole 63 in the inner radially 61 of Sealing 42, it can be a jet-bedding, but also can be a boring.
In addition, in projection 58 zones, be respectively equipped with a groove 65 on the end face 56 of the axle collar 21, it basically along rotor 23 axially, that is be parallel to running shaft 50 ground and extend.Each groove 65 has two opposed sides 66, and these two sides are walked close to with outwards observing mutual wedge shape, but form a discontiguous gap.
Also can replace outwardly open groove 65, establish a groove outer closure.Two sidewalls of walking close to mutually 66 are in the contact of the top of cavetto in this case.
In groove 65, can insert the brake component 67 of perspective representation among Fig. 4.Brake component 67 comprises a wedge-shaped segment with side 70 of each other walking close to corresponding with groove 65, and one is located at the distolateral pin of wedge-shaped segment 69.In the time of in brake component 67 is packed groove 65 into, pin 69 inserts in the hole 63 of Sealing 42.
Therefore, prevent Sealing 42, comprise hole 63 on the Sealing 42 on the whole, be located at the distolateral groove 65 of rotor disk 19 and wherein the brake component 67 of can packing into along the safty device that circumferential U moves.
Have only when hole 63 along the width of circumferentially seeing greater than pin during along width of circumferentially seeing or diameter, Sealing 42 just has a small amount of and tolerable gap along annular groove 20.In order to reach area of isolation 37 and zone 39, preferably the diameter basically identical of the width in hole 63 and pin 69 especially hermetically.
After in groove 65 that brake component 67 is packed into, make brake component plastic deformation in a small amount by the ca(u)lk operation.The plastic deformation in zone 71 of brake component 67 this moment.Eliminate thus for gap that brake component 67 still exists but in a small amount is installed, thereby cause a kind of more firm cooperation of brake component 67.By eliminating the gap, side 70 is pressed against on the sidewall 66.Form reliably between the side 70 of the sidewall 66 of groove 65 and brake component 67 that friction is connected thus, it prevents that reliably brake component from throwing off unintentionally.
The ca(u)lk operation can by a suitable tip slightly the chisel of cavetto carry out, be placed on chisel in the zone 71 on the brake component and apply hammer force.In order to control the location of chisel, brake component has a preprocessing at distolateral recess 71, and chisel should be placed in this recess.
Fig. 5 represents the perspective view of the another kind of design of the present invention.Here, the brake component that only slightly changes 67 shown in Figure 4 is packed in the groove 65.Replace distolateral recess 71, the brake component 67 that is used for Fig. 5 have two with regard to rotor in the outside recess 71 of (circumference), be used to assist the enforcement of ca(u)lk operation, as long as brake component 67 is packed in the groove 65 according to Fig. 5, they are just mutually opposed with the recess 72 in circumference is located at sidewall 66 respectively.By implementing the ca(u)lk operation according to the above mode, near the material of brake component recess can enter in the recess 72, thereby causes a kind of shape sealing to connect, and brake component 67 reliably is positioned in the groove 65.
In a word, adopt and the invention provides a kind of device, wherein, the shift motion by the brake component shutoff Sealing in the distolateral insertion groove of the axle collar overcomes by the known shortcoming of prior art.Can not throw off unintentionally in order to ensure brake component itself, brake component is fixed on the rotor disk by plastic deformation.
Claims (8)
1. the axial relief device (10) of a working blade (14) on rotor (23),
Comprise the axle collar (21), go up laying along the axially extended working blade fixed groove of rotor (23) (12) at the excircle (52) of this axle collar, working blade (14) is installed in these working blade fixed grooves (12) by the blade root (54) corresponding with working blade fixed groove (12) respectively;
Be included in the working blade fixed groove, (12) be located at the axle collar in the zone, (21) distolateral side, (56) projection, (58), at projection, (58) establish a radially outwardly open annular groove in, (20), and comprise and be located at each working blade, (14) safety groove of opening inwardly radially in, (24), it respectively with annular groove, (20) radially mutually opposed, wherein, for working blade, (14) axial relief, respectively at annular groove, (20) with at safety groove, the lamellar Sealing of insertion is set (24), (42), these Sealings are along circumferential, (U) constitute distolateral seal ring, it is characterized by
For fixing seals (42) prevents to move along circumferential (U), at least one Sealing (42) porose (63), and establish one in the side (56) of the axle collar (21) with the groove (65) of hole (63) general alignment with adopt the brake component (67) that has that is installed in this groove (65) from the distolateral pin that stretches out (69), pin (69) inserts in the described hole (63), and wherein said brake component (67) prevents to lose by the ca(u)lk that makes its plastic deformation.
2. according to the described device of claim 1 (10), wherein, described brake component (67) with regard to its state of packing in the zone of described groove (65) cross section be designed to wedge shape.
3. according to the described device of claim 2 (10), wherein, described groove (65) designs corresponding to the wedge shape of described brake component (67), and wherein, the sidewall (66) of described groove (65) is outwards seen and inclined towards each other.
4. according to the described device of one of all claims in prostatitis (10), wherein, described groove (65) is outside opening radially.
5. according to the described device of claim 4 (10), wherein, be provided with the recess on the circumference in the sidewall (66) of described groove (65) with regard to rotor, the material of brake component (67) can enter in these recesses to small part by plastic deformation.
6. according to the described device of one of all claims in prostatitis (10), wherein, the described axle collar (21) is made of rotor disk (19).
7. according to the described device of one of all claims in prostatitis (10), wherein, per at least second Sealing (42) has and is used to the safty device that prevent that Sealing (42) from moving.
8. one kind has according to the described gas turbine that is used for the safty device (10) of working blade (14) of one of claim 1 to 6.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP07007088.3 | 2007-04-04 | ||
| EP07007088A EP1978211A1 (en) | 2007-04-04 | 2007-04-04 | Assembly for axial protection on rotor blades in a rotor and gas turbine with such an assembly |
| PCT/EP2008/053271 WO2008122492A1 (en) | 2007-04-04 | 2008-03-19 | Arrangement for axially securing rotating blades in a rotor, and gas turbine having such an arrangement |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101680304A true CN101680304A (en) | 2010-03-24 |
| CN101680304B CN101680304B (en) | 2013-09-04 |
Family
ID=38372409
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200880016327.0A Expired - Fee Related CN101680304B (en) | 2007-04-04 | 2008-03-19 | Arrangement for axially securing rotating blades in a rotor, and gas turbine having such an arrangement |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US20110027092A1 (en) |
| EP (2) | EP1978211A1 (en) |
| JP (1) | JP4942844B2 (en) |
| CN (1) | CN101680304B (en) |
| RU (1) | RU2427713C2 (en) |
| WO (1) | WO2008122492A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102220885A (en) * | 2010-04-16 | 2011-10-19 | 通用电气公司 | Locking spacer assembly for circumferential attachment |
| CN105065065A (en) * | 2015-08-07 | 2015-11-18 | 山东青能动力股份有限公司 | Fir type blade root moving blade locking device and assembly process thereof |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2218873A1 (en) * | 2009-02-17 | 2010-08-18 | Siemens Aktiengesellschaft | Rotor section for a rotor of a turbo machine, rotor blade for a turbo machine and blocking element |
| US8251668B2 (en) * | 2009-06-30 | 2012-08-28 | General Electric Company | Method and apparatus for assembling rotating machines |
| CN104285040B (en) | 2012-05-08 | 2016-09-07 | 西门子公司 | Axial rotor segment and turbine rotor blade for gas turbine |
| EP2860350A1 (en) * | 2013-10-10 | 2015-04-15 | Siemens Aktiengesellschaft | Turbine blade and gas turbine |
| EP2940249A1 (en) * | 2014-04-29 | 2015-11-04 | Siemens Aktiengesellschaft | Wheel disc assembly and method for mounting a wheel disc assembly |
| FR3021691B1 (en) * | 2014-06-03 | 2016-06-24 | Snecma | ROTOR FOR TURBOMACHINE COMPRISING AUBES WITH REPORTED PLATFORMS |
| EP3048256A1 (en) * | 2015-01-20 | 2016-07-27 | Siemens Aktiengesellschaft | Rotor comprising a turbine blade with a locking device |
| EP3611344A1 (en) * | 2018-08-16 | 2020-02-19 | Siemens Aktiengesellschaft | Rotor with peripheral securing of sealing elements |
| US11021974B2 (en) * | 2018-10-10 | 2021-06-01 | Rolls-Royce North American Technologies Inc. | Turbine wheel assembly with retainer rings for ceramic matrix composite material blades |
Family Cites Families (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB739870A (en) * | 1954-04-07 | 1955-11-02 | Parsons C A & Co Ltd | Improvements in and relating to locking devices for rotor blades of turbines and the like |
| US3266770A (en) * | 1961-12-22 | 1966-08-16 | Gen Electric | Turbomachine rotor assembly |
| DE1258662B (en) * | 1964-10-28 | 1968-01-11 | Goerlitzer Maschb Veb | Cover plate for the cooling gas supply of gas turbine rotors |
| US3501249A (en) * | 1968-06-24 | 1970-03-17 | Westinghouse Electric Corp | Side plates for turbine blades |
| US3572966A (en) * | 1969-01-17 | 1971-03-30 | Westinghouse Electric Corp | Seal plates for root cooled turbine rotor blades |
| US3832092A (en) * | 1973-10-19 | 1974-08-27 | Gen Electric | Device for locking turbomachinery blades |
| US3957393A (en) * | 1974-10-29 | 1976-05-18 | United Technologies Corporation | Turbine disk and sideplate construction |
| US4344740A (en) * | 1979-09-28 | 1982-08-17 | United Technologies Corporation | Rotor assembly |
| FR2524933B1 (en) * | 1982-04-13 | 1987-02-20 | Snecma | AXIAL LOCKING DEVICE FOR TURBINE OR COMPRESSOR ROTOR BLADES |
| US4725200A (en) * | 1987-02-24 | 1988-02-16 | Westinghouse Electric Corp. | Apparatus and method for reducing relative motion between blade and rotor in steam turbine |
| JPH02140403A (en) * | 1988-11-18 | 1990-05-30 | Toshiba Corp | Mounting support structure for turbine rotor blade |
| US4846628A (en) * | 1988-12-23 | 1989-07-11 | United Technologies Corporation | Rotor assembly for a turbomachine |
| JPH0658102A (en) * | 1992-08-05 | 1994-03-01 | Hitachi Ltd | Gas turbine moving blade |
| DE19516694C2 (en) * | 1995-05-06 | 2001-06-28 | Mtu Aero Engines Gmbh | Device for fixing blades to the impeller, in particular a turbine of a gas turbine engine |
| JPH09177502A (en) * | 1995-12-22 | 1997-07-08 | Toshiba Corp | Method for fixing turbine blade |
| JP4498964B2 (en) * | 2005-03-30 | 2010-07-07 | 株式会社日立製作所 | Turbine blade and turbine equipment using the same |
-
2007
- 2007-04-04 EP EP07007088A patent/EP1978211A1/en not_active Withdrawn
-
2008
- 2008-03-19 RU RU2009140744/06A patent/RU2427713C2/en not_active IP Right Cessation
- 2008-03-19 JP JP2010501467A patent/JP4942844B2/en not_active Expired - Fee Related
- 2008-03-19 EP EP08717999A patent/EP2129871A1/en not_active Withdrawn
- 2008-03-19 US US12/594,353 patent/US20110027092A1/en not_active Abandoned
- 2008-03-19 CN CN200880016327.0A patent/CN101680304B/en not_active Expired - Fee Related
- 2008-03-19 WO PCT/EP2008/053271 patent/WO2008122492A1/en active Application Filing
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102220885A (en) * | 2010-04-16 | 2011-10-19 | 通用电气公司 | Locking spacer assembly for circumferential attachment |
| CN105065065A (en) * | 2015-08-07 | 2015-11-18 | 山东青能动力股份有限公司 | Fir type blade root moving blade locking device and assembly process thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| US20110027092A1 (en) | 2011-02-03 |
| EP1978211A1 (en) | 2008-10-08 |
| RU2009140744A (en) | 2011-05-10 |
| JP4942844B2 (en) | 2012-05-30 |
| EP2129871A1 (en) | 2009-12-09 |
| RU2427713C2 (en) | 2011-08-27 |
| WO2008122492A1 (en) | 2008-10-16 |
| CN101680304B (en) | 2013-09-04 |
| JP2010523873A (en) | 2010-07-15 |
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