US20110027092A1 - Arrangement for axially securing rotating blades in arotor, and gas turbine having such an arrangement - Google Patents
Arrangement for axially securing rotating blades in arotor, and gas turbine having such an arrangement Download PDFInfo
- Publication number
- US20110027092A1 US20110027092A1 US12/594,353 US59435308A US2011027092A1 US 20110027092 A1 US20110027092 A1 US 20110027092A1 US 59435308 A US59435308 A US 59435308A US 2011027092 A1 US2011027092 A1 US 2011027092A1
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- United States
- Prior art keywords
- blocking element
- recess
- rotor
- arrangement
- slot
- 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.)
- Abandoned
Links
- 238000007789 sealing Methods 0.000 claims abstract description 78
- 230000000903 blocking effect Effects 0.000 claims abstract description 70
- 238000006073 displacement reaction Methods 0.000 claims abstract description 23
- 238000000034 method Methods 0.000 claims description 8
- 239000002184 metal Substances 0.000 description 16
- 238000011161 development Methods 0.000 description 6
- 230000018109 developmental process Effects 0.000 description 6
- 230000008901 benefit Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000002826 coolant Substances 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
- 230000001771 impaired effect Effects 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
Images
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
- 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
Definitions
- the invention refers to an arrangement for axial locking of rotor blades in a rotor, with a shaft collar, on the outer periphery of which provision is made for rotor blade retaining slots which extend in the axial direction of the rotor and in which rotor blades, with blade roots which correspond to the rotor blade retaining slot, are arranged in each case, with a projection which is arranged on an end-face side surface of the shaft collar in the region of the retaining slots, in which projection a radially outwardly open encompassing slot is provided and with radially inwardly open locking slots which are arranged in each rotor blade and which lie radially opposite the encompassing slot in each case, wherein for axial locking of the rotor blades provision is made for plate-like sealing elements which in each case engage in the encompassing slot and in the locking slot, forming an end-face sealing ring in the circumferential direction, wherein at least one of the sealing elements has a means for securing the sealing elements against displacement in the circumfer
- Rotors of gas turbines are known in which turbine rotor blades, which are arranged on the outer periphery in rotor blade retaining slots, are secured against axial displacement by means of sealing plates.
- to fasten these sealing plates on the rotor by means of riveting is known for example from U.S. Pat. No. 3,957,393.
- FIG. 1 shows a generic-type arrangement in a plan view
- FIG. 2 shows an arrangement in a cross section according to the line of intersection II-II in FIG. 1 .
- two slightly overlapping sealing plates 16 are provided as sealing elements which in each case cover by half the end-face opening of the rotor blade retaining slot 12 .
- Each sealing plate 16 by its radially inner end 18 is inserted in an encompassing slot 20 which is provided on a rotor disk 19 on the end face, and by its radially outer end 22 is inserted in a locking slot 24 which is provided on the underside 26 of a platform 28 of the rotor blade 14 .
- a rectilinear metal strip 30 which extends essentially in the radial direction of the rotor 23 , is fastened on each sealing plate.
- Each metal strip 30 terminates at its radially outer end 32 in a uniformly converging point 34 .
- Chamfered edges 36 are provided on the platforms 28 of the rotor blades 14 , wherein two oppositely disposed edges 36 of directly adjacent turbine rotor blades 14 form in each case a recess 38 which tapers to a point and into which the point 34 of the metal strip 30 can project and abut for securing the sealing plate 16 against displacement in the circumferential direction U.
- the sealing plates 16 furthermore cater for separation of two regions 37 , 39 in which on the one hand cooling air can enter and on the other hand some of the hot gas can possibly enter.
- two parallel slots 40 are provided in the last-named, through which the metal strip 30 , which is already pre-bent into a U-shape, is inserted.
- the end 41 of the metal strip 30 opposite the point 34 is already bent into the position which is shown in FIG. 2 for the fastening of the metal strip 30 .
- the sealing plates 16 with the pre-installed metal strips 30 are threaded one after the other into the endlessly encompassing slot 20 which is arranged on the rotor disk 19 , and into the locking slot 24 which is arranged on the underside 26 of the platform 28 .
- the sealing plates 16 are positioned along the circumference of the encompassing slot 20 so that each metal strip 30 lies opposite a recess 38 .
- the points 34 of the metal strips 30 are then bent into the recesses 38 in order to exclude displacement of the sealing plates 16 in the circumferential direction U.
- the metal strips may be bent only once on account of the enormously high mechanical requirements, when exchanging a rotor blade in the event of a service the metal strip which is then bent up is to be replaced by a new metal strip. Furthermore, the slots which are provided for accommodating the metal strips in the sealing plates weaken the said sealing plates.
- the provision of a gas turbine with such an arrangement is a further object of the invention.
- the invention provides that in the case of the generic-type arrangement the means for securing the sealing elements against displacement in the circumferential direction comprise an opening which is provided in the sealing element and also a recess which is provided in the side surface of the shaft collar and approximately aligns with the opening, and a positionally locked blocking element which is seated in the recess and in the opening.
- the invention avoids the previous configuration in which a metal strip which is hooked into the sealing element engages in a form-fitting manner in a recess. Instead of the metal strip, a blocking element is now provided which can be inserted into the recess which is provided on the shaft collar on the end face.
- the blocking element blocks displacement of the sealing element in the circumferential direction since, being arranged in the region of the sealing element, it extends transversely to the encompassing slot in which the sealing element is seated and in the process engages in the opening which is provided on the sealing element.
- a negligible and tolerable clearance of the sealing element along the encompassing slot is possible only insofar as the width of the opening as seen in the circumferential direction is larger than the width of the blocking element which is to be considered in the circumferential direction.
- the blocking element By using a blocking element which engages in the opening of the sealing element and is fastened on the end face on the shaft collar by means of caulking which plastically deforms the blocking element, a particularly reliable and simple axial securing of the sealing element against displacement in the circumferential direction can be achieved. Furthermore, installation is to be accomplished quickly and simply.
- the blocking element is to be plastically deformed on the end face with a suitable caulking tool, for example a tool in the style of a hammer and chisel, so that it abuts in the recess under tension.
- the blocking element is formed in the shape of a wedge in cross section in the region of the recess and moreover comprises a bolt which projects on the end face and which can be inserted into the opening of the sealing element.
- a defined position of the blocking element in the rotor is predetermined.
- the orientation of the wedge shape of the recess is selected so that the converging side walls point outwards, in the same way as the flanks of the blocking element which correspond to them.
- the wedge-shaped blocking element is braced outwards under centrifugal force action and in the process wedges or jams further in the recess which further increases the frictional engagement between the flanks and the side walls and makes an unwanted loosening of the blocking element more difficult. Consequently, a particularly reliable arrangement can be disclosed as a result of this.
- the recess which accommodates the blocking element is open as seen in the radially outward direction.
- the blocking element which is inserted therein can be plastically deformed on the circumferential side, with regard to the rotor, instead of the end-face deformation.
- a form-fit for positional locking of the blocking element can additionally also be provided in addition to the caulking of the blocking element.
- the recess extending in the axial direction of the rotor, is arranged in the side surface of the shaft ring in such a way that it extends right into the encompassing slot. Weakening of the shaft collar or of a rotor disk which preferably forms the shaft collar is avoided in this case. Therefore, the opening which is provided on the sealing element is then provided on the radial inner end of the sealing element. This region of the sealing element heats up the least during operation so that the rigidity and the temperature resistance of the sealing element are not impaired as a result of the opening.
- every other sealing element, or each sealing element has the means for securing the sealing elements against displacement.
- the arrangement is expediently provided on a rotor of a stationary gas turbine which is exposed to throughflow in the axial direction.
- FIG. 1 shows the arrangement for axial locking of rotor blades in a rotor according to the prior art
- FIG. 2 shows the cross-sectional view according to FIG. 1 along the line of intersection II-II
- FIG. 3 shows the detail of a plan view of a rotor disk with a rotor blade arranged thereupon as an arrangement for axial locking of the rotor blade by means of a sealing element
- FIG. 4 shows a perspective view of a blocking element according to the invention
- FIG. 5 shows a perspective view of a blocking element which is inserted into the recess of the rotor according to a second development.
- FIG. 3 shows a detail of the end-face plan view of the shaft collar 21 , which is formed by a rotor disk 19 , of a rotor 23 of a gas turbine.
- the rotor 23 which is rotatable around the rotational axis 50 , has rotor blade retaining slots 12 which are distributed on its outer periphery 52 along the circumference U and extend in the axial direction, into which slots a rotor blade 14 , with a blade root 54 which is constructed corresponding to the rotor blade retaining slot 12 , in each case can be inserted.
- a rotor blade 14 is already inserted in the rotor blade retaining slot 12 which is shown in the middle in FIG. 3 .
- FIG. 3 shows a detail of the end-face plan view of the shaft collar 21 , which is formed by a rotor disk 19 , of a rotor 23 of a gas turbine.
- the rotor 23 which is rotatable around the rotational axis 50 , has
- a projection 58 or widening, with a radially outwardly open encompassing slot 20 therein, which extends in the axial direction, is arranged on an end face of the rotor disk 19 or on an end-face side surface 56 of the shaft collar 21 .
- the encompassing slot 20 for example is arranged radially further inwards than the rotor blade retaining slots 12 .
- the rotor blade 14 has a platform 28 which is arranged between blade root 54 and the profiled blade airfoil and on the underside of which provision is made for a locking slot 24 which is open towards the encompassing slot 20 and in this case lies opposite this.
- a sealing element 42 is inserted into the endlessly encompassing slot 20 and in the locking slot 24 and secures the rotor blade 14 against displacement along the rotor blade retaining slot.
- the sealing element 42 completely covers the end-face opening of one of the rotor blade slots 12 . In this way, only one of the rotor blades 14 is secured in each case by one of the sealing elements 42 against displacement along the rotor blade retaining slot 12 .
- sealing elements 42 can be distributed over the circumference so that two directly adjacent sealing elements engage by half in the locking slot 24 of the rotor blade 14 in each case. Then two adjacent sealing elements secure one of the rotor blades 14 against axial displacement.
- a completely installed ring of sealing elements 42 which slightly overlap in each case, forms a sealing ring which separates a region 37 which is exposed to throughflow by a cooling medium from a further region 39 in which a hot gas can possibly be encountered ( FIG. 2 ).
- an opening 63 which can be a cutout but also a hole, is provided on the radially inner end 61 of the sealing element 42 .
- a recess 65 which extends essentially in the axial direction of the rotor 23 , i.e. parallel to its rotational axis 50 , is provided on the side surface 56 of the shaft collar 21 in the region of the projection 58 in each case.
- Each recess 65 has two oppositely disposed side surfaces 66 which, as seen in the outward direction, extend towards each other in a wedge-like manner, but do not touch, forming a gap.
- an outwardly closed recess can also be provided.
- the two side walls 66 which extend towards each other meet in a rounded point.
- the blocking element 67 which is perspectively shown in FIG. 4 can be inserted into the recess 65 .
- the blocking element 67 comprises a section with a wedge shape which corresponds to the recess 65 , with flanks 70 which extend towards each other, and a bolt 69 which is arranged on the wedge-shaped section on the end face. With the blocking element 67 inserted in the recess 65 , its bolt 69 engages in the opening 63 of the sealing element 42 .
- the means for securing the sealing element 42 against displacement in the circumferential direction U comprises the opening 63 in the sealing element 42 , the recess 65 which is arranged in the end face of the rotor disk 19 , and also the blocking element 67 which can be inserted into the recess.
- a negligible and tolerable clearance of the sealing element 42 along the encompassing slot 20 is possible only insofar as the width of the opening 63 as seen in the circumferential direction is larger than the width or the diameter of the bolt which is to be considered in the circumferential direction.
- the width of the opening 63 preferably corresponds essentially to the diameter of the bolt 69 .
- the blocking element 67 After inserting the blocking element 67 in the recess 65 , the blocking element is slightly plastically deformed by means of a caulking process.
- the blocking element 67 in this case is plastically deformed in the region 71 .
- the still existing, but negligible, clearance for inserting the blocking element 67 is removed so that a secure seating of the blocking element 67 results.
- the flanks 70 are pressed onto the sidewalls 66 .
- a reliable frictional engagement is created between the walls 66 of the recess 65 and the flanks 70 of the blocking element 67 which reliably prevents the unwanted loosening of the blocking element.
- the caulking process can be carried out by means of a suitable chisel which is slightly rounded at the point, which when placed on the blocking element in the region 71 is provided with a hammer blow.
- the blocking element has an end-face premachined depression 71 in which the chisel is to be placed.
- FIG. 5 An alternative development of the invention is shown perspectively in FIG. 5 .
- the blocking element 67 which is shown from FIG. 4 is inserted in the recess 65 with only a slight alteration.
- the blocking element 67 which is to be used for FIG. 5 has two depressions 71 on the generated surface side (circumferential side), with regard to the rotor, as an aid for the caulking process and which, providing the blocking element 67 is inserted in the recess 65 according to FIG. 5 , in each case lie opposite a pocket 72 which is provided in the sidewalls 66 on the circumferential side.
- the material of the blocking element which is adjacent to the depressions 71 can be introduced into the pockets 72 so that a form-fit results for secure positioning of the blocking element 67 in the recess 65 .
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
An arrangement for axial locking of rotating blades in a rotor is provided. The arrangement includes a shaft collar, a projection, plate-like sealing elements, and a blocking element. The sealing elements are provided for axially securing the rotating blades. At least one sealing element has an opening for securing the sealing elements against displacement in the circumferential direction. The blocking element is inserted in a recess from the end side of the shaft collar and blocks the displacement path of the sealing element. In order for the blocking element to be secured against unintentional releasing, the blocking element is fastened on the rotor disk using plastic deformation.
Description
- This application is the US National Stage of International Application No. PCT/EP2008/053271, filed Mar. 19, 2008 and claims the benefit thereof. The International Application claims the benefits of European Patent Office application No. 07007088.3 EP filed Apr. 4, 2007, both of the applications are incorporated by reference herein in their entirety.
- The invention refers to an arrangement for axial locking of rotor blades in a rotor, with a shaft collar, on the outer periphery of which provision is made for rotor blade retaining slots which extend in the axial direction of the rotor and in which rotor blades, with blade roots which correspond to the rotor blade retaining slot, are arranged in each case, with a projection which is arranged on an end-face side surface of the shaft collar in the region of the retaining slots, in which projection a radially outwardly open encompassing slot is provided and with radially inwardly open locking slots which are arranged in each rotor blade and which lie radially opposite the encompassing slot in each case, wherein for axial locking of the rotor blades provision is made for plate-like sealing elements which in each case engage in the encompassing slot and in the locking slot, forming an end-face sealing ring in the circumferential direction, wherein at least one of the sealing elements has a means for securing the sealing elements against displacement in the circumferential direction. In addition, the invention refers to a gas turbine with such an arrangement.
- Rotors of gas turbines are known in which turbine rotor blades, which are arranged on the outer periphery in rotor blade retaining slots, are secured against axial displacement by means of sealing plates. In this case, to fasten these sealing plates on the rotor by means of riveting is known for example from U.S. Pat. No. 3,957,393.
- Furthermore, an arrangement according to
FIG. 1 is known. It shows a generic-type arrangement in a plan view, andFIG. 2 shows an arrangement in a cross section according to the line of intersection II-II inFIG. 1 . For eachrotor blade 14 which is to be secured against axial displacement inside its rotorblade retaining slot 12, two slightly overlappingsealing plates 16 are provided as sealing elements which in each case cover by half the end-face opening of the rotorblade retaining slot 12. Eachsealing plate 16 by its radiallyinner end 18 is inserted in anencompassing slot 20 which is provided on a rotor disk 19 on the end face, and by its radiallyouter end 22 is inserted in alocking slot 24 which is provided on theunderside 26 of aplatform 28 of therotor blade 14. In order to secure eachsealing plate 16 against displacement in the circumferential direction U, arectilinear metal strip 30, which extends essentially in the radial direction of therotor 23, is fastened on each sealing plate. Eachmetal strip 30 terminates at its radially outer end 32 in a uniformly converging point 34. Chamferededges 36 are provided on theplatforms 28 of therotor blades 14, wherein two oppositely disposededges 36 of directly adjacentturbine rotor blades 14 form in each case arecess 38 which tapers to a point and into which the point 34 of themetal strip 30 can project and abut for securing thesealing plate 16 against displacement in the circumferential direction U. - The
sealing plates 16 furthermore cater for separation of tworegions - For fastening the
metal strip 30 on thesealing plate 16, twoparallel slots 40 are provided in the last-named, through which themetal strip 30, which is already pre-bent into a U-shape, is inserted. Before installing thesealing plate 16 on the rotor disk 19, theend 41 of themetal strip 30 opposite the point 34 is already bent into the position which is shown inFIG. 2 for the fastening of themetal strip 30. - After installing the
rotor blades 14 in the rotor disks 19, thesealing plates 16 with thepre-installed metal strips 30 are threaded one after the other into the endlessly encompassingslot 20 which is arranged on the rotor disk 19, and into thelocking slot 24 which is arranged on theunderside 26 of theplatform 28. Thesealing plates 16 are positioned along the circumference of theencompassing slot 20 so that eachmetal strip 30 lies opposite arecess 38. The points 34 of themetal strips 30 are then bent into therecesses 38 in order to exclude displacement of thesealing plates 16 in the circumferential direction U. - Since the metal strips may be bent only once on account of the enormously high mechanical requirements, when exchanging a rotor blade in the event of a service the metal strip which is then bent up is to be replaced by a new metal strip. Furthermore, the slots which are provided for accommodating the metal strips in the sealing plates weaken the said sealing plates.
- It is the object of the present invention to disclose an alternative arrangement for securing the sealing elements against a rotating displacement in the circumferential direction, in which the installation and removal times are improved. The provision of a gas turbine with such an arrangement is a further object of the invention.
- The object which is focused upon the arrangement for axial locking of rotor blades in a rotor is achieved by means of the features of the claims.
- The invention provides that in the case of the generic-type arrangement the means for securing the sealing elements against displacement in the circumferential direction comprise an opening which is provided in the sealing element and also a recess which is provided in the side surface of the shaft collar and approximately aligns with the opening, and a positionally locked blocking element which is seated in the recess and in the opening. The invention avoids the previous configuration in which a metal strip which is hooked into the sealing element engages in a form-fitting manner in a recess. Instead of the metal strip, a blocking element is now provided which can be inserted into the recess which is provided on the shaft collar on the end face. The blocking element blocks displacement of the sealing element in the circumferential direction since, being arranged in the region of the sealing element, it extends transversely to the encompassing slot in which the sealing element is seated and in the process engages in the opening which is provided on the sealing element. A negligible and tolerable clearance of the sealing element along the encompassing slot is possible only insofar as the width of the opening as seen in the circumferential direction is larger than the width of the blocking element which is to be considered in the circumferential direction.
- By using a blocking element which engages in the opening of the sealing element and is fastened on the end face on the shaft collar by means of caulking which plastically deforms the blocking element, a particularly reliable and simple axial securing of the sealing element against displacement in the circumferential direction can be achieved. Furthermore, installation is to be accomplished quickly and simply. For this purpose, the blocking element is to be plastically deformed on the end face with a suitable caulking tool, for example a tool in the style of a hammer and chisel, so that it abuts in the recess under tension. As a result, an exceptionally reliable frictional engagement between the wall of the recess and the blocking element is brought about, which reliably prevents the unwanted loosening of the blocking element during operation of the gas turbine. For removing the blocking element, the deformed region of the blocking element can be removed by grinding and in this way the frictional engagement is loosened for removal.
- In addition, with the construction according to the invention the slots which were provided for fastening the locking plate on the sealing element and previously weakened the sealing element are dispensed with. The rigidity of the sealing element is subsequently further increased, also its sealing effect.
- Advantageous developments are disclosed in the dependent claims.
- In an advantageous development of the invention, the blocking element, with regard to its installed position, is formed in the shape of a wedge in cross section in the region of the recess and moreover comprises a bolt which projects on the end face and which can be inserted into the opening of the sealing element. As a result of the wedge shape of the blocking element and of the recess which corresponds to the wedge shape a defined position of the blocking element in the rotor is predetermined. Furthermore, the orientation of the wedge shape of the recess is selected so that the converging side walls point outwards, in the same way as the flanks of the blocking element which correspond to them. As a result, the wedge-shaped blocking element is braced outwards under centrifugal force action and in the process wedges or jams further in the recess which further increases the frictional engagement between the flanks and the side walls and makes an unwanted loosening of the blocking element more difficult. Consequently, a particularly reliable arrangement can be disclosed as a result of this.
- According to an alternative development of the invention, the recess which accommodates the blocking element is open as seen in the radially outward direction. In this case, the blocking element which is inserted therein can be plastically deformed on the circumferential side, with regard to the rotor, instead of the end-face deformation. As long as provision is then still made for pockets which are additionally arranged in the sidewalls of the recess on the circumferential side, into which parts of the deformed material of the blocking element can deflect, a form-fit for positional locking of the blocking element can additionally also be provided in addition to the caulking of the blocking element. As a result of this, the blocking element is especially reliably safeguarded against loss.
- According to a further advantageous development, the recess, extending in the axial direction of the rotor, is arranged in the side surface of the shaft ring in such a way that it extends right into the encompassing slot. Weakening of the shaft collar or of a rotor disk which preferably forms the shaft collar is avoided in this case. Therefore, the opening which is provided on the sealing element is then provided on the radial inner end of the sealing element. This region of the sealing element heats up the least during operation so that the rigidity and the temperature resistance of the sealing element are not impaired as a result of the opening.
- It has been proved to be especially advantageous if every other sealing element, or each sealing element, has the means for securing the sealing elements against displacement. The arrangement is expediently provided on a rotor of a stationary gas turbine which is exposed to throughflow in the axial direction.
- The invention is explained based on a plurality of exemplary embodiments which are shown in a drawing. Further advantages and features result from the explanation. In the drawing:
-
FIG. 1 shows the arrangement for axial locking of rotor blades in a rotor according to the prior art, -
FIG. 2 shows the cross-sectional view according toFIG. 1 along the line of intersection II-II, -
FIG. 3 shows the detail of a plan view of a rotor disk with a rotor blade arranged thereupon as an arrangement for axial locking of the rotor blade by means of a sealing element, -
FIG. 4 shows a perspective view of a blocking element according to the invention, and -
FIG. 5 shows a perspective view of a blocking element which is inserted into the recess of the rotor according to a second development. -
FIG. 3 shows a detail of the end-face plan view of the shaft collar 21, which is formed by a rotor disk 19, of arotor 23 of a gas turbine. Therotor 23, which is rotatable around therotational axis 50, has rotorblade retaining slots 12 which are distributed on itsouter periphery 52 along the circumference U and extend in the axial direction, into which slots arotor blade 14, with ablade root 54 which is constructed corresponding to the rotorblade retaining slot 12, in each case can be inserted. Arotor blade 14 is already inserted in the rotorblade retaining slot 12 which is shown in the middle inFIG. 3 . As in the case of the prior art which is shown inFIG. 1 andFIG. 2 , aprojection 58 or widening, with a radially outwardly open encompassingslot 20 therein, which extends in the axial direction, is arranged on an end face of the rotor disk 19 or on an end-face side surface 56 of the shaft collar 21. The encompassingslot 20 for example is arranged radially further inwards than the rotorblade retaining slots 12. Therotor blade 14 has aplatform 28 which is arranged betweenblade root 54 and the profiled blade airfoil and on the underside of which provision is made for alocking slot 24 which is open towards the encompassingslot 20 and in this case lies opposite this. In a similar manner to the prior art, a sealingelement 42 is inserted into the endlessly encompassingslot 20 and in the lockingslot 24 and secures therotor blade 14 against displacement along the rotor blade retaining slot. - In contrast to the nearest prior art, the sealing
element 42 completely covers the end-face opening of one of therotor blade slots 12. In this way, only one of therotor blades 14 is secured in each case by one of the sealingelements 42 against displacement along the rotorblade retaining slot 12. - The sealing
elements 42, however, as in the case of the prior art, can be distributed over the circumference so that two directly adjacent sealing elements engage by half in the lockingslot 24 of therotor blade 14 in each case. Then two adjacent sealing elements secure one of therotor blades 14 against axial displacement. - Similar to the prior art, a completely installed ring of sealing
elements 42, which slightly overlap in each case, forms a sealing ring which separates aregion 37 which is exposed to throughflow by a cooling medium from afurther region 39 in which a hot gas can possibly be encountered (FIG. 2 ). - In order to secure the sealing
element 42 itself against displacement in the circumferential direction, anopening 63, which can be a cutout but also a hole, is provided on the radiallyinner end 61 of the sealingelement 42. - Furthermore, a
recess 65, which extends essentially in the axial direction of therotor 23, i.e. parallel to itsrotational axis 50, is provided on theside surface 56 of the shaft collar 21 in the region of theprojection 58 in each case. Eachrecess 65 has two oppositely disposed side surfaces 66 which, as seen in the outward direction, extend towards each other in a wedge-like manner, but do not touch, forming a gap. - Instead of an outwardly
open recess 65, an outwardly closed recess can also be provided. In this case, the twoside walls 66 which extend towards each other meet in a rounded point. - The blocking
element 67 which is perspectively shown inFIG. 4 can be inserted into therecess 65. The blockingelement 67 comprises a section with a wedge shape which corresponds to therecess 65, withflanks 70 which extend towards each other, and abolt 69 which is arranged on the wedge-shaped section on the end face. With the blockingelement 67 inserted in therecess 65, itsbolt 69 engages in theopening 63 of the sealingelement 42. - In total, therefore, the means for securing the sealing
element 42 against displacement in the circumferential direction U comprises theopening 63 in the sealingelement 42, therecess 65 which is arranged in the end face of the rotor disk 19, and also the blockingelement 67 which can be inserted into the recess. - A negligible and tolerable clearance of the sealing
element 42 along the encompassingslot 20 is possible only insofar as the width of theopening 63 as seen in the circumferential direction is larger than the width or the diameter of the bolt which is to be considered in the circumferential direction. In order to achieve an especially impermeable separation of theregion 37 from theregion 39, the width of theopening 63 preferably corresponds essentially to the diameter of thebolt 69. - After inserting the blocking
element 67 in therecess 65, the blocking element is slightly plastically deformed by means of a caulking process. The blockingelement 67 in this case is plastically deformed in theregion 71. As a result of this, the still existing, but negligible, clearance for inserting the blockingelement 67 is removed so that a secure seating of the blockingelement 67 results. As a result of removing the clearance, theflanks 70 are pressed onto thesidewalls 66. As a result of this, a reliable frictional engagement is created between thewalls 66 of therecess 65 and theflanks 70 of the blockingelement 67 which reliably prevents the unwanted loosening of the blocking element. - The caulking process can be carried out by means of a suitable chisel which is slightly rounded at the point, which when placed on the blocking element in the
region 71 is provided with a hammer blow. For controlled positioning of the chisel the blocking element has an end-face premachined depression 71 in which the chisel is to be placed. - An alternative development of the invention is shown perspectively in
FIG. 5 . In this case, the blockingelement 67 which is shown fromFIG. 4 is inserted in therecess 65 with only a slight alteration. Instead of the end-face depression 71 the blockingelement 67 which is to be used forFIG. 5 has twodepressions 71 on the generated surface side (circumferential side), with regard to the rotor, as an aid for the caulking process and which, providing the blockingelement 67 is inserted in therecess 65 according toFIG. 5 , in each case lie opposite apocket 72 which is provided in the sidewalls 66 on the circumferential side. By means of a caulking process according to the aforesaid manner the material of the blocking element which is adjacent to thedepressions 71 can be introduced into thepockets 72 so that a form-fit results for secure positioning of the blockingelement 67 in therecess 65. - In all, an arrangement is disclosed by the invention in which the disadvantages which are known from the prior art are eliminated by a blocking element, which is inserted from the end face of the shaft collar into a recess, blocking the displacement path of the sealing element. So that the blocking element itself is secured against unwanted loosening this is fastened on the rotor disk by means of plastic deformation.
Claims (19)
1.-8. (canceled)
9. An arrangement for axial locking of rotor blades in a rotor, comprising:
a shaft collar;
a projection, arranged on an end-face side surface of the shaft collar in a region of a plurality of rotor blade retaining slots;
a plurality of plate-like sealing elements; and
a blocking element,
wherein on an outer periphery of the shaft collar the plurality of rotor blade retaining slots are provided, each rotor blade retaining slot extends in an axial direction of the rotor,
wherein the plurality of rotor blades are arranged in the shaft collar, each blade root corresponding to a rotor blade retaining slot,
wherein a radially outwardly open encompassing slot is provided in the projection,
wherein a radially inwardly open locking slot is arranged in each rotor blade and lies radially opposite the encompassing slot,
wherein the plurality of plate-like sealing elements are provided for axial locking of the plurality of rotor blades, each rotor blade engages in the encompassing slot and in the locking slot, forming an end-face sealing ring in a circumferential direction,
wherein at least one of the plurality of sealing elements includes an opening for securing the plurality of sealing elements against a displacement in a circumferential direction,
wherein a recess is disposed in a side surface of the shaft collar, the recess approximately aligns with the opening,
wherein the blocking element is seated in the recess and includes a bolt which projects on a first end face of the blocking element and engages in the opening, and
wherein the blocking element is safeguarded against loss using caulking which plastically deforms the blocking element.
10. The arrangement as claimed in claim 9 , wherein the blocking element includes a section that is formed in a shape of a wedge in cross section in a region of the recess.
11. The arrangement as claimed in claim 10 ,
wherein the recess is formed corresponding to the wedge shape of the blocking element, and
wherein two sidewalls of the recess are inclined towards each other as seen in a radially outward direction.
12. The arrangement as claimed in claim 9 , wherein the recess is open in the radially outward direction.
13. The arrangement as claimed in claim 12 ,
wherein a plurality of depressions are provided in the sidewalls of the recesses on the circumferential side of the rotor, and
wherein the blocking element is at least partially introduced into the plurality of depressions as a result of the plastic deformation.
14. The arrangement as claimed in claim 9 , wherein the recess is closed in the radially outward direction.
15. The arrangement as claimed in claim 9 , wherein the shaft collar is formed by a rotor disk.
16. The arrangement as claimed in claim 9 , wherein at least every other sealing element includes an opening for securing the plurality of sealing elements against displacement.
17. The arrangement as claimed in claim 9 , wherein a depression is disposed in a second end-face of the blocking element, and wherein the depression is used as a predetermined position at which a chisel may be used to strike the blocking element in order to assist in a caulking process.
18. A gas turbine, comprising:
an arrangement, comprising:
a shaft collar,
a projection, arranged on an end-face side surface of the shaft collar in a region of a plurality of rotor blade retaining slots,
a plurality of plate-like sealing elements, and
a blocking element,
wherein on an outer periphery of the shaft collar the plurality of rotor blade retaining slots are provided, each rotor blade retaining slot extends in an axial direction of the rotor,
wherein the plurality of rotor blades are arranged in the shaft collar, each blade root corresponding to a rotor blade retaining slot,
wherein a radially outwardly open encompassing slot is provided in the projection,
wherein a radially inwardly open locking slot is arranged in each rotor blade and lies radially opposite the encompassing slot,
wherein the plurality of plate-like sealing elements are provided for axial locking of the plurality of rotor blades, each rotor blade engages in the encompassing slot and in the locking slot, forming an end-face sealing ring in a circumferential direction,
wherein at least one of the plurality of sealing elements includes an opening for securing the plurality of sealing elements against a displacement in a circumferential direction,
wherein a recess is disposed in a side surface of the shaft collar, the recess approximately aligns with the opening,
wherein the blocking element is seated in the recess and includes a bolt which projects on a first end face of the blocking element and engages in the opening, and
wherein the blocking element is safeguarded against loss using caulking which plastically deforms the blocking element.
19. The gas turbine as claimed in claim 18 , wherein the blocking element includes a section that is foamed in a shape of a wedge in cross section in a region of the recess.
20. The gas turbine as claimed in claim 19 ,
wherein the recess is fanned corresponding to the wedge shape of the blocking element, and
wherein two sidewalls of the recess are inclined towards each other as seen in a radially outward direction.
21. The gas turbine as claimed in claim 18 , wherein the recess is open in the radially outward direction.
22. The gas turbine as claimed in claim 21 ,
wherein a plurality of depressions are provided in the sidewalls of the recesses on the circumferential side of the rotor, and
wherein the blocking element is at least partially introduced into the plurality of depressions as a result of the plastic deformation.
23. The gas turbine as claimed in claim 18 , wherein the recess is closed in the radially outward direction.
24. The gas turbine as claimed in claim 18 , wherein the shaft collar is fanned by a rotor disk.
25. The gas turbine as claimed in claim 18 , wherein at least every other sealing element includes an opening for securing the plurality of sealing elements against displacement.
26. The gas turbine as claimed in claim 18 , wherein a depression is disposed in a second end-face of the blocking element, and wherein the depression is used as a predetermined position at which a chisel may be used to strike the blocking element in order to assist in a caulking process.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
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 (1)
Publication Number | Publication Date |
---|---|
US20110027092A1 true US20110027092A1 (en) | 2011-02-03 |
Family
ID=38372409
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/594,353 Abandoned US20110027092A1 (en) | 2007-04-04 | 2008-03-19 | Arrangement for axially securing rotating blades in arotor, 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 (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20170037736A1 (en) * | 2014-04-29 | 2017-02-09 | Siemens Aktiengesellschaft | Wheel disk assembly and method for assembling a wheel disk assembly |
US9745852B2 (en) | 2012-05-08 | 2017-08-29 | Siemens Aktiengesellschaft | Axial rotor portion and turbine rotor blade for a gas turbine |
US10487674B2 (en) | 2015-01-20 | 2019-11-26 | Siemens Aktiengesellschaft | Blade fastening mechanism having a securing device for turbine blades |
US20200116034A1 (en) * | 2018-10-10 | 2020-04-16 | Rolls-Royce North American Technologies Inc. | Turbine wheel assembly with retainer rings for ceramic matrix composite material blades |
Families Citing this family (7)
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 |
US20110255978A1 (en) * | 2010-04-16 | 2011-10-20 | Brian Denver Potter | Locking Assembly For Circumferential Attachments |
EP2860350A1 (en) * | 2013-10-10 | 2015-04-15 | Siemens Aktiengesellschaft | Turbine blade and gas turbine |
FR3021691B1 (en) * | 2014-06-03 | 2016-06-24 | Snecma | ROTOR FOR TURBOMACHINE COMPRISING AUBES WITH REPORTED PLATFORMS |
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 |
EP3611344A1 (en) * | 2018-08-16 | 2020-02-19 | Siemens Aktiengesellschaft | Rotor with peripheral securing of sealing elements |
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- 2008-03-19 US US12/594,353 patent/US20110027092A1/en not_active Abandoned
- 2008-03-19 WO PCT/EP2008/053271 patent/WO2008122492A1/en active Application Filing
- 2008-03-19 EP EP08717999A patent/EP2129871A1/en not_active Withdrawn
- 2008-03-19 JP JP2010501467A patent/JP4942844B2/en not_active Expired - Fee Related
- 2008-03-19 RU RU2009140744/06A patent/RU2427713C2/en not_active IP Right Cessation
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US3266770A (en) * | 1961-12-22 | 1966-08-16 | Gen Electric | Turbomachine rotor assembly |
US3832092A (en) * | 1973-10-19 | 1974-08-27 | Gen Electric | Device for locking turbomachinery blades |
US5727927A (en) * | 1995-05-06 | 1998-03-17 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh | Device for securing rotor blades to a rotor, especially of a gas turbine propulsion plant |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
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US9745852B2 (en) | 2012-05-08 | 2017-08-29 | Siemens Aktiengesellschaft | Axial rotor portion and turbine rotor blade for a gas turbine |
US20170037736A1 (en) * | 2014-04-29 | 2017-02-09 | Siemens Aktiengesellschaft | Wheel disk assembly and method for assembling a wheel disk assembly |
US10487674B2 (en) | 2015-01-20 | 2019-11-26 | Siemens Aktiengesellschaft | Blade fastening mechanism having a securing device for turbine blades |
US20200116034A1 (en) * | 2018-10-10 | 2020-04-16 | Rolls-Royce North American Technologies Inc. | Turbine wheel assembly with retainer rings for ceramic matrix composite material blades |
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 |
Also Published As
Publication number | Publication date |
---|---|
CN101680304A (en) | 2010-03-24 |
RU2009140744A (en) | 2011-05-10 |
JP4942844B2 (en) | 2012-05-30 |
JP2010523873A (en) | 2010-07-15 |
EP1978211A1 (en) | 2008-10-08 |
RU2427713C2 (en) | 2011-08-27 |
CN101680304B (en) | 2013-09-04 |
WO2008122492A1 (en) | 2008-10-16 |
EP2129871A1 (en) | 2009-12-09 |
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Legal Events
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AS | Assignment |
Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:ENGLE, DARREN T.;REEL/FRAME:023316/0981 Effective date: 20090716 |
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STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |