US20020085917A1 - System and method for securing a radially inserted integral closure bucket to a turbine rotor wheel assembly having axially inserted buckets - Google Patents
System and method for securing a radially inserted integral closure bucket to a turbine rotor wheel assembly having axially inserted buckets Download PDFInfo
- Publication number
- US20020085917A1 US20020085917A1 US09/749,446 US74944600A US2002085917A1 US 20020085917 A1 US20020085917 A1 US 20020085917A1 US 74944600 A US74944600 A US 74944600A US 2002085917 A1 US2002085917 A1 US 2002085917A1
- Authority
- US
- United States
- Prior art keywords
- bucket
- buckets
- trailing
- leading
- dovetails
- 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
- 238000000034 method Methods 0.000 title claims abstract description 40
- 230000007480 spreading Effects 0.000 claims description 17
- 230000007246 mechanism Effects 0.000 claims description 9
- 230000000712 assembly Effects 0.000 claims 3
- 238000000429 assembly Methods 0.000 claims 3
- 238000003780 insertion Methods 0.000 abstract description 18
- 230000037431 insertion Effects 0.000 abstract description 18
- 230000008569 process Effects 0.000 description 5
- 238000010276 construction Methods 0.000 description 3
- 230000013011 mating Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 150000001875 compounds Chemical class 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007812 deficiency 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
- F01D5/32—Locking, e.g. by final locking blades or keys
-
- 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
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/326—Locking of axial insertion type blades by other means
-
- 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
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
-
- 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
- F01D5/005—Repairing methods or devices
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
- Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
Definitions
- the present invention relates to a system and method for securing an integral closure bucket to a rotor wheel assembly.
- the integral closure bucket is inserted in a direction coincident with a radius of the rotor wheel assembly, where the remaining buckets have been previously inserted in a direction parallel to the axis of the turbine rotor wheel.
- the present invention relates to a system and method for securing a closure bucket, having an integral shroud or closure, into a turbine rotor wheel assembly in which the remaining buckets can be axially inserted.
- the buckets adjacent the closure bucket may be spread apart both tangentially and axially to provide sufficient clearance for the radial insertion of the integral closure bucket. Since the closure bucket is inserted radially, both the closure bucket and the adjacent buckets cannot be secured together with keys in the normal fashion, to prevent axial movement of the buckets. As a result, twist locks can be utilized to keep the buckets adjacent to the closure bucket from moving axially after assembly.
- the rotor blades also known as buckets can be attached to the turbine rotor wheel by moving the buckets axially so that male dovetails on the buckets slide into mating female dovetails on the turbine rotor wheel. Both the male and female dovetails may be oriented to be parallel to the axis of the turbine rotor wheel.
- Turbines wheels with buckets having integral covers or shrouds formed on their distal ends are known, as shown in U.S. Pat. No. 6,030,178, to Caruso, and assigned to Assignee of the present application, which is incorporated herein by reference.
- the shrouds have an approximately Z-shaped configuration so that the shroud of adjacent buckets nest with one another. As a result, when all the buckets are assembled on the turbine rotor wheel, the shrouds nest tightly with the adjacent shrouds creating a continuous circumferential coupling.
- the buckets experience vibrational stresses that can reduce the turbine's efficiency and lower the life expectancy of the bucket.
- One method for reducing the vibrational stress is to interlock the ends of the buckets with shrouds.
- the shrouds should maintain sufficient contact between adjacent shrouds all the way around the circumference of the turbine rotor wheel.
- centrifugal forces cause the radial growth and twisting of the buckets.
- the buckets and their covers can be assembled with compressive contact force between adjacent buckets.
- the patent to Caruso et al. teaches securing the closure bucket by employing an axial entry dovetail segment having generally radially opposite male dovetails extending generally in the axial direction.
- the turbine rotor wheel has conventional female dovetails at spaced positions about its circumference for receiving the male dovetails on the buckets or the axial entry dovetail segment.
- the closure bucket has a female dovetail to accept the male dovetail of the axial entry dovetail segment.
- the buckets are prevented from moving axially out of the female dovetails in the turbine rotor wheel by keys disposed in grooves in the outer circumference of the turbine rotor wheel and recesses in the sides of the buckets.
- the present invention relates to a system and method for securing a radially inserted integral closure bucket to a turbine rotor wheel assembly.
- the buckets adjacent the closure bucket location on the turbine rotor wheel, can be spread apart from one another in both an axial and tangential direction to provide sufficient clearance for the radial insertion of the closure bucket.
- a spreading fixture may be employed. The spreading fixture attaches to each of the adjacent buckets and can be adjusted to exert outward tangential force on each of the adjacent buckets so that the tangential clearance between the adjacent buckets increases enough to allow insertion of the closure bucket.
- hydraulic jacks may be employed to move the adjacent buckets in opposing axial directions.
- One hydraulic jack moves a trailing bucket in a first axial direction while a second hydraulic jack moves a leading bucket in an opposite axial direction.
- the spreading fixture and hydraulic jack open sufficient tangential and axial clearance between the leading and trailing buckets to allow radial insertion of the closure bucket. Once the closure bucket is properly situated, the spreading fixture and hydraulic jacks can be removed.
- the conventional locking keys are not used. Instead, channels may be milled in the bottoms of the female dovetails in the turbine rotor wheel. Twist locks can be inserted in these channels. Prior to insertion of the closure bucket, the twist locks can be unlocked, so that the trailing and leading buckets can be spread apart. Once the closure bucket is properly situated, the twist locks may be rotated 180 degrees to prevent the leading and trailing buckets from moving axially. A twist lock is also used to secure the closure bucket. In order to provide enough play between the leading and trailing buckets to obtain sufficient clearance for the closure bucket, up to three leading and three trailing buckets may have twist locks provided in milled channels.
- FIG. 1 is a fragmentary perspective view illustrating the connections between the buckets and turbine rotor wheel, axial entry dovetail segment, and twist locks according to an exemplary embodiment of the present invention used to secure the leading, trailing and closure buckets;
- FIG. 2 is a fragmentary perspective view illustrating a trailing and two leading buckets connected to the turbine rotor wheel with a spreading fixture attached to the trailing and leading buckets, with the closure bucket removed according to an exemplary embodiment of the present invention
- FIG. 3 is the same fragmentary perspective view shown in FIG. 2 with a hydraulic jack positioned adjacent the trailing bucket according to an exemplary embodiment of the present invention.
- FIG. 4 is a partial cross-sectional view showing the turbine rotor wheel, trailing bucket, spreading fixture, and opposing hydraulic jacks disposed between fixture plates and the leading and trailing buckets according to an exemplary embodiment of the present invention.
- FIG. 1 a portion of a turbine rotor wheel 10 having female dovetails 12 is shown.
- the female dovetails 12 may be spaced at even intervals around the entire circumference of the rotor wheel 10 .
- the female dovetails 12 extend in an axial direction, e.g., parallel to the axis of the rotor wheel 10 .
- the female dovetails 12 receive mating male dovetails 14 formed on the inner ends of the buckets 16 .
- the male dovetails 14 on the radial inner ends of the buckets 16 slide axially into the mating female dovetails 12 on the rotor wheel 10 .
- the buckets 16 have integral shrouds or covers 18 at the radial outer or distal ends that on completion of the assembly process contact one another to maintain a continuous circumferential shroud assembly.
- centrifugal forces cause radial growth and twisting of the buckets 16 .
- each shroud 18 should maintain sufficient contact with adjacent shrouds 18 all the way around the circumference of the turbine rotor wheel 10 .
- the buckets 16 and their shrouds 18 may be assembled with compressive contact force between adjacent buckets 16 .
- the shrouds 18 have an approximately or generally Z-shaped configuration as viewed in a radial direction.
- the shrouds 18 interlock or nest with the adjacent shrouds 18 .
- Earlier designs used covers that were peaned onto buckets. As a consequence, the thickness of the covers was limited. If the covers were too thick they could not be peaned on.
- the provision of integral shrouds 18 eliminated the thickness limitation.
- the shrouds may have grooves 60 formed in their outer face. When the turbine rotor wheel is fully assembled, the shrouds 18 form a continuous ring, and the grooves 60 form corresponding continuous circumferential grooves. Such continuous circumferential grooves allow the insertion of seals on the outer circumferential face.
- the buckets 16 are assembled serially around the rotor wheel 10 .
- the bucket 16 a is the first bucket attached to the rotor wheel 10 , followed by a bucket 16 b , until bucket 18 y is attached.
- Adjacent shrouds 18 a , 18 b , etc. nest with one another upon the axial insertion of buckets 16 a , 16 b , etc.
- FIG. 2 shows buckets 16 y , 16 a , and 16 b attached to the rotor 10 .
- the remaining buckets 16 c - 16 x are not shown.
- the number of buckets on the turbine is not limited to twenty-six, and can be greater or fewer, the reference numbering herein is merely used for illustrative purposes.
- the closure bucket 16 z shown in FIG. 1 is not yet inserted in FIG. 2. From FIG. 2 it can be seen that the closure bucket 16 z cannot be inserted into the gap between leading bucket 16 a and trailing bucket 16 y from either axial direction because the shroud 18 z cannot pass through the opening defined by the adjacent covers 18 a and 18 y . Consequently, the closure bucket is inserted radially.
- the closure bucket 16 z can be provided with an axially extending female dovetail 20 along its radial inner end.
- An axial entry dovetail segment 22 is provided for joining the closure bucket 16 z to the rotor 10 .
- the axial entry dovetail segment 22 has male projecting dovetails on radially opposite sides.
- the closure bucket 16 z in inserted radially between the leading bucket 16 a and the trailing bucket 16 y , until the base of the closure bucket 16 z is disposed between the base of leading bucket 16 a and the base of the trailing bucket 16 y .
- the shroud 18 z will likewise nest between the shrouds 18 a and 18 y of the leading and trailing buckets 16 a and 16 y , respectively.
- the closure bucket can be secured by inserting the axial entry segment axially so that the male dovetails of the axial entry segment mate with female dovetails 20 and 12 z.
- an exemplary embodiment of the present invention moves the leading bucket 16 a and trailing bucket 16 y apart both tangentially and axially.
- a spreading mechanism 40 shown in FIGS. 2 - 4 , can be provided to move the leading bucket 16 a and trailing bucket 16 y apart tangentially.
- the spreading mechanism 40 has a pair of clamps 42 and 44 , which attach to the shroud 18 a of the leading bucket 16 a and the shroud 18 y of the trailing bucket 16 y , respectively.
- a spreading fixture that includes a pair of threaded rods 46 and nuts 48 threaded on the rods 46 connects the clamps 42 and 44 .
- the clamps 42 and 44 can be attached to the shroud 18 a of the leading bucket 16 a and the shroud 18 y of the trailing bucket 16 y , respectively, with the rods 46 extending through pairs holes in each of the clamps 42 and 44 .
- the nuts 48 may be threaded onto the rods 46 before the insertion of the rods 46 into the holes in the clamps 42 and 44 .
- the nuts 48 are rotated until they contact the clamps 42 and 44 .
- Each turn of the nuts 48 that moves the nuts outward towards the ends of the rods 46 exerts force tangentially onto the clamps 42 and 44 in the direction of arrows S 1 and S 2 .
- the shrouds 18 a and 18 y move apart tangentially thereby increasing the tangential space between the shrouds 18 a and 18 y.
- the spreading mechanism 40 can be loosened by turning the nuts 48 so that they move away from the ends of the rods 46 .
- the shroud 18 a of the leading bucket 16 a and the trailing shroud 18 y of the trailing bucket 16 y are moved apart axially, using the hydraulic jacks 52 and 58 shown in FIGS. 3 and 4.
- leverage plates 50 may be attached to the rotor 10 .
- an adjacent rotor wheel (not shown) may be employed to provide the base against which a hydraulic jack can push.
- the hydraulic jack 52 can be positioned so that the tip 54 presses against the male dovetail 14 of the trailing bucket 16 y .
- the hydraulic jack 58 can be positioned so that the tips 54 , shown in FIG. 4, can be disposed against the male dovetail 14 of the leading bucket 16 a .
- the hydraulic jacks 52 and 58 When the hydraulic jacks 52 and 58 are activated, they exert force in opposing axial directions as indicated by arrows f 1 and f 2 in FIG. 4.
- the shroud 18 a of the leading bucket 16 a and the shroud 18 y of the trailing bucket 16 y are moved apart axially as their respective buckets 16 a and 16 y are moved by the hydraulic jacks 58 and 52 ,respectively.
- the leading bucket 16 a and the trailing bucket 16 y cannot be secured using conventional keys disposed in grooves formed in the outer circumference of the rotor 10 and recesses in the sides of the bases of the buckets 16 .
- Such keys cannot be fitted between the trailing bucket 16 y and the closure bucket 16 z or the closure bucket 16 z and the leading bucket 16 a due to the radial insertion of the closure bucket 16 z .
- Such keys do permit sufficient axial movement to allow axial expansion of the space between the leading bucket 16 a and the trailing bucket 16 y.
- the present invention eliminates some of the standard keys, utilizing instead twist locks 30 .
- the female dovetails 12 below the closure bucket 16 z , the leading bucket 16 a and the trailing bucket 16 y have axially oriented channels 24 formed at the bottom of each female dovetail.
- the twist locks 30 each has a shaft 36 , a full head 32 at one end of the shaft 36 and a partial head 34 at an opposite end of the shaft 36 .
- the twist locks 30 may be inserted into the channels 24 before the male dovetails 14 , or axial entry segment 22 may be slid axially into the female dovetails 12 .
- the partial head 34 can be substantially semicircular with one flat side 38 .
- the twist locks 30 can be positioned as shown in FIG. 2, so that the partial head 34 has a first orientation, with the flat side 38 lying parallel to a tangent to the circumference of the rotor wheel 10 .
- the male dovetails 12 on the buckets 16 can be slid into the female dovetails 14 on the rotor wheel 10 over the partial heads 34 .
- the twist locks 30 can be rotated 180° so that the partial head prevents the male dovetails 12 on the leading and trailing buckets 16 a and 16 y , respectively, and the axial entry segment 22 cannot move axially out of engagement with the female dovetails 14 on the rotor wheel 10 .
- the female dovetails 14 underneath the leading bucket 16 a , trailing bucket 16 y and the closure bucket 16 z have channels 24 milled therein with twist locks 30 placed inside the channels 24 to lock the leading bucket 16 a , trailing bucket 16 y and the closure bucket 16 z after insertion of the closure bucket 16 z.
- the two leading buckets 12 a and 12 b , and the two trailing buckets 12 x and 12 y can have channels 24 with twist locks 30 provided underneath the male dovetails 12 .
- twist locks 30 can be employed, three under the three leading buckets, one under the closure bucket 12 z , and three under the three trailing buckets.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A system and method for securing an integral closure bucket to a rotor wheel assembly. The integral closure bucket is inserted in a direction coincident with a radius of the rotor wheel assembly, where the remaining buckets have been previously inserted in a direction parallel to the axis of the turbine rotor wheel. The closure bucket has an integral shroud and is connected to a turbine rotor wheel assembly in which the remaining buckets have been previously inserted in an axial direction. The buckets adjacent the closure bucket are spread apart both tangentially and axially to provide sufficient clearance for the radial insertion of the integral closure bucket. To prevent axial movement of the closure bucket and adjacent buckets, twist locks are utilized in channels provided in the bottom of the female dovetails in the rotor wheel.
Description
- The present invention relates to a system and method for securing an integral closure bucket to a rotor wheel assembly. The integral closure bucket is inserted in a direction coincident with a radius of the rotor wheel assembly, where the remaining buckets have been previously inserted in a direction parallel to the axis of the turbine rotor wheel. More particularly, the present invention relates to a system and method for securing a closure bucket, having an integral shroud or closure, into a turbine rotor wheel assembly in which the remaining buckets can be axially inserted.
- The buckets adjacent the closure bucket may be spread apart both tangentially and axially to provide sufficient clearance for the radial insertion of the integral closure bucket. Since the closure bucket is inserted radially, both the closure bucket and the adjacent buckets cannot be secured together with keys in the normal fashion, to prevent axial movement of the buckets. As a result, twist locks can be utilized to keep the buckets adjacent to the closure bucket from moving axially after assembly.
- In the assembly of a turbine rotor wheel, the rotor blades, also known as buckets can be attached to the turbine rotor wheel by moving the buckets axially so that male dovetails on the buckets slide into mating female dovetails on the turbine rotor wheel. Both the male and female dovetails may be oriented to be parallel to the axis of the turbine rotor wheel.
- Turbines wheels with buckets having integral covers or shrouds formed on their distal ends are known, as shown in U.S. Pat. No. 6,030,178, to Caruso, and assigned to Assignee of the present application, which is incorporated herein by reference. The shrouds have an approximately Z-shaped configuration so that the shroud of adjacent buckets nest with one another. As a result, when all the buckets are assembled on the turbine rotor wheel, the shrouds nest tightly with the adjacent shrouds creating a continuous circumferential coupling.
- In operation, the buckets experience vibrational stresses that can reduce the turbine's efficiency and lower the life expectancy of the bucket. One method for reducing the vibrational stress is to interlock the ends of the buckets with shrouds. In order to be effective, the shrouds should maintain sufficient contact between adjacent shrouds all the way around the circumference of the turbine rotor wheel. During operation of the turbine, centrifugal forces cause the radial growth and twisting of the buckets. To counteract these effects, the buckets and their covers can be assembled with compressive contact force between adjacent buckets.
- Construction of turbine rotor wheels having radial-entry buckets is accomplished by assembling the buckets serially around the turbine rotor wheel so that the approximately Z-shaped shrouds nest with one another. However, when all the buckets, except the bucket, are assembled the shrouds on the first and next to buckets prevent axial insertion of the closure bucket. Consequently, the closure bucket must be inserted radially.
- The patent to Caruso et al. teaches securing the closure bucket by employing an axial entry dovetail segment having generally radially opposite male dovetails extending generally in the axial direction. The turbine rotor wheel has conventional female dovetails at spaced positions about its circumference for receiving the male dovetails on the buckets or the axial entry dovetail segment. Instead of having a male dovetail, the closure bucket has a female dovetail to accept the male dovetail of the axial entry dovetail segment.
- The foregoing construction has drawbacks. In particular, the z-shaped shrouds are designed to fit together very tightly. As a result, the clearance between the shrouds on the buckets adjacent the closure bucket location is insufficient to permit radial insertion of the closure bucket. The clearance is insufficient in both the axial and tangential directions.
- Furthermore, in the turbine rotor wheel configuration taught in Caruso et al., the buckets are prevented from moving axially out of the female dovetails in the turbine rotor wheel by keys disposed in grooves in the outer circumference of the turbine rotor wheel and recesses in the sides of the buckets.
- However, due to the radial insertion of the closure bucket, it may not be possible to insert the keys the recesses of the closure bucket. Furthermore, while such keys can be used to secure most of he buckets around the circumference of the turbine rotor wheel, and the use of these keys further limits any axial movement of the buckets, they compound the radial insertion problem of the closure bucket.
- The foregoing and other deficiencies of the conventional techniques are addressed by the system and method for securing an integral closure bucket to a turbine rotor wheel assembly of the present invention.
- The present invention relates to a system and method for securing a radially inserted integral closure bucket to a turbine rotor wheel assembly. According to the assembly method the buckets, adjacent the closure bucket location on the turbine rotor wheel, can be spread apart from one another in both an axial and tangential direction to provide sufficient clearance for the radial insertion of the closure bucket. To provide the necessary clearance between the adjacent buckets in the tangential direction, a spreading fixture may be employed. The spreading fixture attaches to each of the adjacent buckets and can be adjusted to exert outward tangential force on each of the adjacent buckets so that the tangential clearance between the adjacent buckets increases enough to allow insertion of the closure bucket. Simultaneously, hydraulic jacks may be employed to move the adjacent buckets in opposing axial directions. One hydraulic jack moves a trailing bucket in a first axial direction while a second hydraulic jack moves a leading bucket in an opposite axial direction. Thus, the spreading fixture and hydraulic jack open sufficient tangential and axial clearance between the leading and trailing buckets to allow radial insertion of the closure bucket. Once the closure bucket is properly situated, the spreading fixture and hydraulic jacks can be removed.
- In order to ensure that the leading and trailing buckets can be moved a sufficient distance to permit the insertion of the closure bucket, the conventional locking keys are not used. Instead, channels may be milled in the bottoms of the female dovetails in the turbine rotor wheel. Twist locks can be inserted in these channels. Prior to insertion of the closure bucket, the twist locks can be unlocked, so that the trailing and leading buckets can be spread apart. Once the closure bucket is properly situated, the twist locks may be rotated 180 degrees to prevent the leading and trailing buckets from moving axially. A twist lock is also used to secure the closure bucket. In order to provide enough play between the leading and trailing buckets to obtain sufficient clearance for the closure bucket, up to three leading and three trailing buckets may have twist locks provided in milled channels.
- The structure, operation and advantages of the presently preferred embodiment of this invention will become apparent upon consideration of the following description, taken in conjunction with the accompanying drawings in which:
- FIG. 1 is a fragmentary perspective view illustrating the connections between the buckets and turbine rotor wheel, axial entry dovetail segment, and twist locks according to an exemplary embodiment of the present invention used to secure the leading, trailing and closure buckets;
- FIG. 2 is a fragmentary perspective view illustrating a trailing and two leading buckets connected to the turbine rotor wheel with a spreading fixture attached to the trailing and leading buckets, with the closure bucket removed according to an exemplary embodiment of the present invention;
- FIG. 3 is the same fragmentary perspective view shown in FIG. 2 with a hydraulic jack positioned adjacent the trailing bucket according to an exemplary embodiment of the present invention; and
- FIG. 4 is a partial cross-sectional view showing the turbine rotor wheel, trailing bucket, spreading fixture, and opposing hydraulic jacks disposed between fixture plates and the leading and trailing buckets according to an exemplary embodiment of the present invention.
- Referring to FIG. 1, a portion of a
turbine rotor wheel 10 havingfemale dovetails 12 is shown. Thefemale dovetails 12 may be spaced at even intervals around the entire circumference of therotor wheel 10. Thefemale dovetails 12 extend in an axial direction, e.g., parallel to the axis of therotor wheel 10. Thefemale dovetails 12 receive matingmale dovetails 14 formed on the inner ends of thebuckets 16. In the construction process of the complete turbine rotor wheel, themale dovetails 14 on the radial inner ends of thebuckets 16 slide axially into the matingfemale dovetails 12 on therotor wheel 10. - The
buckets 16 have integral shrouds or covers 18 at the radial outer or distal ends that on completion of the assembly process contact one another to maintain a continuous circumferential shroud assembly. During operation of the turbine, centrifugal forces cause radial growth and twisting of thebuckets 16. To counteract such forces, eachshroud 18 should maintain sufficient contact withadjacent shrouds 18 all the way around the circumference of theturbine rotor wheel 10. To counteract these effects, thebuckets 16 and theirshrouds 18 may be assembled with compressive contact force betweenadjacent buckets 16. - The
shrouds 18 have an approximately or generally Z-shaped configuration as viewed in a radial direction. Theshrouds 18 interlock or nest with the adjacent shrouds 18. Earlier designs used covers that were peaned onto buckets. As a consequence, the thickness of the covers was limited. If the covers were too thick they could not be peaned on. The provision ofintegral shrouds 18 eliminated the thickness limitation. As a result, the shrouds may havegrooves 60 formed in their outer face. When the turbine rotor wheel is fully assembled, theshrouds 18 form a continuous ring, and thegrooves 60 form corresponding continuous circumferential grooves. Such continuous circumferential grooves allow the insertion of seals on the outer circumferential face. - The
buckets 16 are assembled serially around therotor wheel 10. In particular, thebucket 16 a is the first bucket attached to therotor wheel 10, followed by abucket 16 b, untilbucket 18 y is attached.Adjacent shrouds buckets - FIG. 2 shows
buckets rotor 10. The remaining buckets 16 c- 16 x, are not shown. The number of buckets on the turbine is not limited to twenty-six, and can be greater or fewer, the reference numbering herein is merely used for illustrative purposes. Theclosure bucket 16 z shown in FIG. 1 is not yet inserted in FIG. 2. From FIG. 2 it can be seen that theclosure bucket 16 z cannot be inserted into the gap between leadingbucket 16 a and trailingbucket 16 y from either axial direction because theshroud 18 z cannot pass through the opening defined by the adjacent covers 18 a and 18 y. Consequently, the closure bucket is inserted radially. - Instead of providing the
closure bucket 16 z with a male dovetail similar to the dovetails 14 on the inner ends of theother buckets 16, theclosure bucket 16 z can be provided with an axially extendingfemale dovetail 20 along its radial inner end. An axialentry dovetail segment 22 is provided for joining theclosure bucket 16 z to therotor 10. The axialentry dovetail segment 22 has male projecting dovetails on radially opposite sides. - In the assembly process, the
closure bucket 16 z in inserted radially between the leadingbucket 16 a and the trailingbucket 16 y, until the base of theclosure bucket 16 z is disposed between the base of leadingbucket 16 a and the base of the trailingbucket 16 y. Theshroud 18 z will likewise nest between theshrouds buckets - The foregoing assembly process would be sufficient if the
shrouds 18 nested together loosely. This is not the case. Rather theshrouds 18 nest together in an extremely tight fashion upon completion of the assembly process. Theshrouds 18 exert significant pressure on adjacent shrouds both tangentially and axially. As a consequence, the gap between theshroud 18 a of the leadingbucket 16 a and theshroud 18 y of the trailingbucket 16 y may be insufficient to permit radial insertion of theclosure bucket 16 z. - To overcome this problem, an exemplary embodiment of the present invention moves the leading
bucket 16 a and trailingbucket 16 y apart both tangentially and axially. A spreadingmechanism 40, shown in FIGS. 2-4, can be provided to move the leadingbucket 16 a and trailingbucket 16 y apart tangentially. The spreadingmechanism 40 has a pair ofclamps shroud 18 a of the leadingbucket 16 a and theshroud 18 y of the trailingbucket 16 y, respectively. A spreading fixture that includes a pair of threadedrods 46 andnuts 48 threaded on therods 46 connects theclamps - In operation, the
clamps shroud 18 a of the leadingbucket 16 a and theshroud 18 y of the trailingbucket 16 y, respectively, with therods 46 extending through pairs holes in each of theclamps rods 46 before the insertion of therods 46 into the holes in theclamps clamps rods 46 exerts force tangentially onto theclamps shrouds shrouds - After the
closure bucket 16 z is inserted between the leadingbucket 16 a and trailingbucket 16 y, the spreadingmechanism 40 can be loosened by turning the nuts 48 so that they move away from the ends of therods 46. - Similarly, the
shroud 18 a of the leadingbucket 16 a and the trailingshroud 18 y of the trailingbucket 16 y are moved apart axially, using thehydraulic jacks hydraulic jacks 52 and 58 a base to push against,leverage plates 50 may be attached to therotor 10. In an instance where the multiple rotor wheels are mounted on the same axis, an adjacent rotor wheel (not shown) may be employed to provide the base against which a hydraulic jack can push. - Referring to FIG. 3, the
hydraulic jack 52 can be positioned so that thetip 54 presses against themale dovetail 14 of the trailingbucket 16 y. Similarly, thehydraulic jack 58 can be positioned so that thetips 54, shown in FIG. 4, can be disposed against themale dovetail 14 of the leadingbucket 16 a. When thehydraulic jacks shroud 18 a of the leadingbucket 16 a and theshroud 18 y of the trailingbucket 16 y are moved apart axially as theirrespective buckets hydraulic jacks - In order to ensure that the leading and trailing
buckets bucket 16 a and the trailingbucket 16 y cannot be secured using conventional keys disposed in grooves formed in the outer circumference of therotor 10 and recesses in the sides of the bases of thebuckets 16. Such keys cannot be fitted between the trailingbucket 16 y and theclosure bucket 16 z or theclosure bucket 16 z and the leadingbucket 16 a due to the radial insertion of theclosure bucket 16 z. Furthermore, such keys do permit sufficient axial movement to allow axial expansion of the space between the leadingbucket 16 a and the trailingbucket 16 y. - As shown in FIGS.1-3, the present invention eliminates some of the standard keys, utilizing instead twist locks 30. At least, the female dovetails 12 below the
closure bucket 16 z, the leadingbucket 16 a and the trailingbucket 16 y have axially orientedchannels 24 formed at the bottom of each female dovetail. - The twist locks30 each has a
shaft 36, afull head 32 at one end of theshaft 36 and apartial head 34 at an opposite end of theshaft 36. The twist locks 30 may be inserted into thechannels 24 before the male dovetails 14, oraxial entry segment 22 may be slid axially into the female dovetails 12. Thepartial head 34 can be substantially semicircular with oneflat side 38. At first, the twist locks 30 can be positioned as shown in FIG. 2, so that thepartial head 34 has a first orientation, with theflat side 38 lying parallel to a tangent to the circumference of therotor wheel 10. In this manner, the male dovetails 12 on thebuckets 16 can be slid into the female dovetails 14 on therotor wheel 10 over the partial heads 34. After theclosure bucket 16 z is in place and theaxial entry segment 22 has been inserted, the twist locks 30 can be rotated 180° so that the partial head prevents the male dovetails 12 on the leading and trailingbuckets axial entry segment 22 cannot move axially out of engagement with the female dovetails 14 on therotor wheel 10. - In order to be able to move the leading
bucket 16 a and the trailingbucket 16 y apart a sufficient distance to allow axial entry of theclosure bucket 16 z, the female dovetails 14 underneath the leadingbucket 16 a, trailingbucket 16 y and theclosure bucket 16 z havechannels 24 milled therein withtwist locks 30 placed inside thechannels 24 to lock the leadingbucket 16 a, trailingbucket 16 y and theclosure bucket 16 z after insertion of theclosure bucket 16 z. - It may be possible that providing
channels 24 underneath the leadingbucket 16 a, trailingbucket 16 y and theclosure bucket 16 z will not provide sufficient freedom to move the leadingbucket 16 a and trailingbucket 16 y apart a sufficient distance to permit the insertion of theclosure bucket 16 z. In such case, the two leading buckets 12 a and 12 b, and the two trailing buckets 12 x and 12 y can havechannels 24 withtwist locks 30 provided underneath the male dovetails 12. Furthermore, it is contemplated that up to seventwist locks 30 can be employed, three under the three leading buckets, one under theclosure bucket 12 z, and three under the three trailing buckets. - Having described several embodiments of the system and method for securing a radially inserted integral closure bucket to a turbine rotor wheel assembly having axially inserted buckets, according to the present invention, it is believed that other modifications, variations and changes will be suggested to those skilled in the art in view of the description set forth above, such as using other devices besides hydraulic jacks to apply axial force to the trailing and leading buckets. Such devices might include camming mechanisms, threaded mechanisms, or other mechanical devices. It is therefore to be understood that all such variations, modifications and changes are believed to fall within the scope of the invention as defined in the appended claims
Claims (31)
1. In a turbine having a rotor wheel with a plurality of female dovetails disposed around a circumference of the rotor wheel and a plurality of buckets having male dovetails and integral shrouds, a method of assembling the buckets comprising the steps of:
attaching said plurality of buckets serially to said rotor wheel by sliding said male dovetails into said female dovetails on said rotor wheel so that said integral shrouds on adjacent ones of said buckets nest together, leaving one female dovetail empty between a leading bucket and a trailing bucket;
providing a spreading fixture comprising first and second clamp assemblies, and spreading mechanism;
attaching said first clamp assembly to an integral shroud on said trailing bucket;
attaching said second clamp assembly to an integral shroud on said leading bucket;
disposing said spreading mechanism between said first and second clamp assemblies;
actuating said spreading mechanism to increase a space in a tangential direction between said first and second clamp assemblies and said leading and trailing buckets;
inserting a closure bucket, having an integral shroud at one end and a female dovetail on an opposite end, radially into said space between said leading and trailing buckets; and
securing said closure bucket to said rotor wheel by inserting a dovetail segment, having generally radially opposing male dovetails, into said female dovetail on said closure bucket and said empty female dovetail between said leading bucket and said trailing bucket.
2. A method of assembling as recited in claim 1 , further comprising the steps of:
applying force to said leading bucket in a first axial direction; and
applying force to said trailing bucket in a second opposite axial direction, to increase said space in a tangential direction prior to inserting said closure bucket.
3. A method of assembling as recited in claim 2 , wherein said step of applying force to said leading bucket in said first axial direction comprises the steps of:
positioning a hydraulic jack adjacent said trailing bucket; and
actuating said hydraulic jack.
4. A method of assembling as recited in claim 2 , wherein said step of applying force to said trailing bucket in said second opposite axial direction comprises the steps of:
positioning a hydraulic jack adjacent said leading bucket; and
actuating said hydraulic jack.
5. A method of assembling as recited in claim 3 , wherein said hydraulic jack applies said force to a side of said male dovetail of said leading bucket.
6. A method of assembling as recited in claim 4 , wherein said hydraulic jack applies said force to a side of said male dovetail of said trailing bucket.
7. A method of assembling as recited in claim 3 , further comprising the step of attaching a leverage plate to said rotor wheel to provide a base that said hydraulic jack pushes against.
8. A method of assembling as recited in claim 4 , further comprising the step of attaching a leverage plate to said rotor wheel to provide a base that said hydraulic jack pushes against.
9. A method of assembling as recited in claim 1 , further comprising the steps of:
providing a channel in the bottom of said empty female dovetail between said leading bucket and said trailing bucket, and the bottoms of said female dovetails adjacent said empty female dovetail between said leading bucket and said trailing bucket, into which said leading and trailing buckets are attached;
inserting twist locks into each of said channels, said twist locks each having a shaft with a full head at one end of said shaft and a partial head at an opposite end of said shaft, so that said male dovetails on said buckets can be slid into said female dovetails on said rotor wheel over said partial head; and
after said step of inserting said closure bucket, rotating said twist locks so that said partial head prevents said male dovetails on said buckets and said dovetail segment from moving out of said female dovetails on said rotor wheel.
10. A method of assembling as recited in claim 9 , wherein said partial heads of said twist locks are substantially semicircular.
11. A method of assembling as recited in claim 2 , further comprising the steps of:
providing a channel in the bottom of said empty female dovetail between said leading bucket and said trailing bucket, and the bottoms of said female dovetails adjacent said empty female dovetail between said leading bucket and said trailing bucket, into which said leading and trailing buckets are attached;
inserting twist locks into each of said channels, said twist locks each having a shaft with a full head at one end of said shaft and a partial head at an opposite end of said shaft, so that said male dovetails on said buckets can be slid into said female dovetails on said rotor wheel over said partial head; and
after said step of inserting said closure bucket, rotating said twist locks so that said partial head prevents said male dovetails on said buckets from moving out of said female dovetails on said rotor wheel.
12. A method of assembling as recited in claim 11 , wherein said partial heads of said twist locks are substantially semicircular.
13. A method of assembling as recited in claim 1 , further comprising the steps of releasing said spreading fixture after said step of inserting said closure bucket.
14. A method of assembling as recited in claim 2 , further comprising the step of releasing said spreading fixture after said step of inserting said closure bucket.
15. A method of assembling as recited in claim 2 , further comprising the step of releasing said forces applied to said leading bucket in said first axial direction and said trailing bucket in said second opposite axial direction.
16. A method of assembling as recited in claim 14 , further comprising the step of releasing said forces applied to said leading bucket in said first axial direction and said trailing bucket in said second opposite axial direction.
17. A method of assembling as recited in claim 1 , wherein said spreading mechanism comprises a pair of threaded rods and four nuts, said pair of rods extending through holes in each of said first and second clamps, said nuts being threaded on said threaded rods, a first pair of nuts, one nut threaded on each of said pair of threaded rods, being disposed adjacent said first clamp and a second pair of nuts, one nut threaded on each of said pair of threaded rods, being disposed adjacent said second clamp,
wherein said actuating step comprises rotating said nuts on said pair of rods so that the distance between said pair of nuts adjacent said first clamp and said pair of nuts adjacent said second clamp increases to increase said space in said tangential direction.
18. In a turbine having a rotor wheel with a plurality of female dovetails disposed around a circumference of said rotor wheel and a plurality of buckets having male dovetails and integral shrouds, a method of assembling the buckets comprising the steps of:
attaching said plurality of buckets serially to said rotor wheel by sliding said male dovetails into said female dovetails on said rotor wheel so that said integral shrouds on adjacent ones of said buckets nest together, leaving one female dovetail empty between a leading bucket and a trailing bucket;
applying force to said leading bucket in a first axial direction; and
applying force to said trailing bucket in a second opposite axial direction, to increase a space between said leading and trailing buckets in an axial direction; and
inserting a closure bucket, having an integral shroud at one end and a female dovetail on an opposite end, radially into said space between said leading and trailing buckets; and
securing said closure bucket to said rotor wheel by inserting a dovetail segment, having generally radially opposing male dovetails, into said female dovetail on said closure bucket and said empty female dovetail between said leading bucket and said trailing bucket.
19. A method of assembling as recited in claim 18 , wherein said step of applying force to said trailing bucket in said second opposite axial direction comprises the steps of:
positioning a hydraulic jack adjacent said trailing bucket; and
actuating said hydraulic jack.
20. A method of assembling as recited in claim 19 , wherein said hydraulic jack applies said force to a side of said male dovetail of said leading bucket.
21. A method of assembling as recited in claim 18 , wherein said step of applying force to said leading bucket in said first axial direction comprises the steps of:
positioning a hydraulic jack adjacent said leading bucket; and
actuating said hydraulic jack.
22. A method of assembling as recited in claim 21 , wherein said hydraulic jack applies said force to a side of said male dovetail of said trailing bucket.
23. A method of assembling as recited in claim 9 , wherein said step of providing said channels comprises providing said channels in said bottom of said empty female dovetail between said leading bucket and said trailing bucket, and bottoms of said female dovetails underneath at least two leading buckets and at least two trailing buckets.
24. A method of assembling as recited in claim 9 , wherein said step of providing said channels comprises providing said channels in said bottom of said empty female dovetail between said leading bucket and said trailing bucket, and bottoms of said female dovetails underneath at least three leading buckets and at least three trailing buckets.
25. A method of assembling as recited in claim 11 , wherein said step of providing said channels comprises providing said channels in said bottom of said empty female dovetail between said leading bucket and said trailing bucket, and bottoms of said female dovetails underneath at least two leading buckets and at least two trailing buckets.
26. A method of assembling as recited in claim 11 , wherein said step of providing said channels comprises providing said channels in said bottom of said empty female dovetail between said leading bucket and said trailing bucket, and bottoms of said female dovetails underneath at least three leading buckets and at least three trailing buckets.
27. In a turbine having a rotor wheel assembly comprising:
a plurality of female dovetails disposed around a circumference of said rotor wheel;
a plurality of buckets having male dovetails and integral shrouds, said plurality of buckets being attached serially to said rotor wheel by sliding said male dovetails into said female dovetails on said rotor wheel so that said integral shroud on adjacent ones of said buckets nest together, leaving one female dovetail empty between a leading bucket and a trailing bucket,
a plurality of twist locks each comprising a shaft having a full head at one end of said shaft and a partial head at an opposite end of said shaft; and
a plurality of channels disposed in the bottom of said empty female dovetail between said leading bucket and trailing bucket, and the bottoms of said female dovetails adjacent said empty female dovetail between said leading bucket and said trailing bucket, into which said leading and trailing buckets are attached; and
a dovetail segment having opposing male dovetails;
wherein after a closure bucket is attached with said dovetail segment, said male dovetails on said buckets and said dovetail segment slide into said female dovetails on said rotor wheel over said partial heads, and
said male dovetails on said buckets and said dovetail segment are prevented from moving axially out of said female dovetails on said rotor wheel by rotation of said twist locks so that said partial head overlaps a portion of said male dovetails on said buckets and said axial entry dovetail segment.
28. A system of securing said buckets as recited in claim 27 , wherein said partial heads of said twist locks are substantially semicircular.
29. A system of securing said buckets as recited in claim 27 , wherein said full heads of said twist locks are substantially circular.
30. A system of securing said buckets as recited in claim 27 , wherein said channels are provided in said bottom of said empty female dovetail between said leading bucket and said trailing bucket, and bottoms of said female dovetails underneath at least two leading buckets and at least two trailing buckets.
31. A system of securing said buckets as recited in claim 27 , wherein said channels are provided in said bottom of said empty female dovetail between said leading bucket and said trailing bucket, and bottoms of said female dovetails underneath at least three leading buckets and at least three trailing buckets.
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/749,446 US6416286B1 (en) | 2000-12-28 | 2000-12-28 | System and method for securing a radially inserted integral closure bucket to a turbine rotor wheel assembly having axially inserted buckets |
EP01985552A EP1348066B1 (en) | 2000-12-28 | 2001-12-12 | Assembly method for integrally covered axially inserted bucket blades |
PCT/US2001/048133 WO2002053875A1 (en) | 2000-12-28 | 2001-12-12 | Assembly method and jig for integrally covered axially inserted bucket blades |
JP2002554360A JP3814581B2 (en) | 2000-12-28 | 2001-12-12 | System and method for securing an integral closure blade inserted radially into a turbine rotor wheel assembly having blades inserted axially |
KR1020027011254A KR20020075457A (en) | 2000-12-28 | 2001-12-12 | Assembly method and jig for integrally covered axially inserted bucket blades |
RU2002123045/06A RU2002123045A (en) | 2000-12-28 | 2001-12-12 | METHOD OF INSTALLING SHOVELS AND SYSTEM OF THEIR FASTENING |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/749,446 US6416286B1 (en) | 2000-12-28 | 2000-12-28 | System and method for securing a radially inserted integral closure bucket to a turbine rotor wheel assembly having axially inserted buckets |
Publications (2)
Publication Number | Publication Date |
---|---|
US20020085917A1 true US20020085917A1 (en) | 2002-07-04 |
US6416286B1 US6416286B1 (en) | 2002-07-09 |
Family
ID=25013791
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US09/749,446 Expired - Fee Related US6416286B1 (en) | 2000-12-28 | 2000-12-28 | System and method for securing a radially inserted integral closure bucket to a turbine rotor wheel assembly having axially inserted buckets |
Country Status (6)
Country | Link |
---|---|
US (1) | US6416286B1 (en) |
EP (1) | EP1348066B1 (en) |
JP (1) | JP3814581B2 (en) |
KR (1) | KR20020075457A (en) |
RU (1) | RU2002123045A (en) |
WO (1) | WO2002053875A1 (en) |
Cited By (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2406144A (en) * | 2003-09-19 | 2005-03-23 | Rolls Royce Plc | Gas turbine engine blade retention system using a key |
EP1703078A1 (en) * | 2005-03-17 | 2006-09-20 | Siemens Aktiengesellschaft | Caulking device and method of caulking the locking tabs in a compressor or turbine |
US20070084050A1 (en) * | 2005-10-13 | 2007-04-19 | Siemens Power Generation, Inc. | Turbine vane airfoil reconfiguration method |
US20070084048A1 (en) * | 2005-10-13 | 2007-04-19 | Siemens Westinghouse Power Corporation | Turbine vane airfoil reconfiguration system |
US20070248464A1 (en) * | 2006-04-25 | 2007-10-25 | General Electric Company | Nested Turbine Bucket Closure Group |
US20080253887A1 (en) * | 2007-04-11 | 2008-10-16 | Ronald Ralph Cairo | Aeromechanical Blade |
US20090077795A1 (en) * | 2007-09-20 | 2009-03-26 | General Electric Company | Replaceable Staking Insert |
US20100162546A1 (en) * | 2008-12-31 | 2010-07-01 | General Electric Company | Apparatus and method for removing compressor blades |
EP2863016A1 (en) * | 2013-10-16 | 2015-04-22 | Doosan Heavy Industries & Construction Co., Ltd. | Turbine with bucket fixing means |
EP2868868A1 (en) * | 2013-11-05 | 2015-05-06 | Siemens Aktiengesellschaft | Mounting device and mounting method of a vane |
EP2944760A1 (en) * | 2014-05-14 | 2015-11-18 | General Electric Company | Turbomachine bucket displacement apparatus and method of use |
WO2016005687A1 (en) * | 2014-07-08 | 2016-01-14 | Snecma | Mounting of vanes in the periphery of a turbine engine disc |
US20160090841A1 (en) * | 2014-09-29 | 2016-03-31 | United Technologies Corporation | Gas turbine engine blade slot heat shield |
EP3318716A1 (en) * | 2016-11-04 | 2018-05-09 | General Electric Company | Installation or removal of turbine blade at turbine blade base |
EP3327250A1 (en) * | 2016-11-23 | 2018-05-30 | General Electric Company | Installation or removal of turbine blade at turbine blade base |
CN109339870A (en) * | 2018-10-26 | 2019-02-15 | 中国航发湖南动力机械研究所 | Turbine assembly, mortise structure and preparation method thereof |
Families Citing this family (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6755618B2 (en) | 2002-10-23 | 2004-06-29 | General Electric Company | Steam turbine closure bucket attachment |
US6893224B2 (en) | 2002-12-11 | 2005-05-17 | General Electric Company | Methods and apparatus for assembling turbine engines |
US6761537B1 (en) | 2002-12-19 | 2004-07-13 | General Electric Company | Methods and apparatus for assembling turbine engines |
US6827554B2 (en) * | 2003-02-25 | 2004-12-07 | General Electric Company | Axial entry turbine bucket dovetail with integral anti-rotation key |
FR2860740B1 (en) * | 2003-10-10 | 2007-03-02 | Snecma Moteurs | METHOD FOR BRAZING A TURBOMACHINE COMPRESSOR RECTIFIER |
ES2346874T3 (en) * | 2004-07-09 | 2010-10-21 | Siemens Aktiengesellschaft | DEVICE FOR DISASSEMBLY OF SHOVELS FROM A TURBINE OR A COMPRESSOR. |
KR100710574B1 (en) | 2005-06-27 | 2007-04-24 | 두산중공업 주식회사 | Fixture for cutting the tenon parts of the turbine bucket |
KR100642466B1 (en) * | 2005-10-07 | 2006-11-02 | 두산중공업 주식회사 | Jig for assembling integral type bucket of turbine rotor |
JP4673732B2 (en) | 2005-12-01 | 2011-04-20 | 株式会社東芝 | Turbine blades and steam turbines |
US8425194B2 (en) * | 2007-07-19 | 2013-04-23 | General Electric Company | Clamped plate seal |
KR101114534B1 (en) * | 2009-08-14 | 2012-02-27 | 두산중공업 주식회사 | Aseembly method of Finger type bucket |
US20110158819A1 (en) * | 2009-12-30 | 2011-06-30 | General Electric Company | Internal reaction steam turbine cooling arrangement |
US8727734B2 (en) * | 2010-05-17 | 2014-05-20 | Pratt & Whitney | Blade retainer clip |
US8657580B2 (en) * | 2010-06-17 | 2014-02-25 | Pratt & Whitney | Blade retainment system |
ITFI20130117A1 (en) | 2013-05-21 | 2014-11-22 | Nuovo Pignone Srl | "TURBOMACHINE ROTOR ASSEMBLY AND METHOD" |
US9689268B2 (en) | 2013-12-17 | 2017-06-27 | General Electric Company | Turbine bucket closure assembly and methods of assembling the same |
US9624780B2 (en) | 2013-12-17 | 2017-04-18 | General Electric Company | System and method for securing axially inserted buckets to a rotor assembly |
EP2896485A1 (en) * | 2014-01-15 | 2015-07-22 | Siemens Aktiengesellschaft | Handheld device for driving a guide vane into a vane groove |
US9494040B2 (en) | 2014-02-06 | 2016-11-15 | Siemens Energy, Inc. | Turbine engine blade removal apparatus and method |
US9429041B2 (en) * | 2014-05-14 | 2016-08-30 | General Electric Company | Turbomachine component displacement apparatus and method of use |
JP6641654B2 (en) * | 2016-01-08 | 2020-02-05 | 三菱日立パワーシステムズ株式会社 | Method for removing a moving blade, removal device for performing the method, and rotor set including the removal device |
EP3205451A1 (en) * | 2016-02-12 | 2017-08-16 | Siemens Aktiengesellschaft | Turbine blade torsional clamp |
KR102157899B1 (en) | 2019-04-25 | 2020-09-21 | 두산중공업 주식회사 | Bucket fixing apparatus for turbine and bucket assembling method using the same |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1953089A (en) * | 1931-05-14 | 1934-04-03 | Lisle F Small | Turbine blade lacing and method of making the same |
US2801074A (en) * | 1952-10-01 | 1957-07-30 | United Aircraft Corp | Blade retaining means |
US3198485A (en) * | 1963-09-26 | 1965-08-03 | Gen Motors Corp | Turbine blade lock |
US3627448A (en) * | 1969-12-31 | 1971-12-14 | Westinghouse Electric Corp | Locking arrangement for side-entry blades |
US4455730A (en) * | 1982-08-30 | 1984-06-26 | Westinghouse Electric Corp. | Turbine blade extractor |
DE3528640A1 (en) * | 1985-06-28 | 1987-01-08 | Bbc Brown Boveri & Cie | Blade lock for rim-straddling blades of turboengines |
US4778342A (en) * | 1985-07-24 | 1988-10-18 | Imo Delaval, Inc. | Turbine blade retainer |
GB2227191B (en) * | 1988-09-16 | 1993-03-03 | Refurbished Turbine Components | Turbine blade repair |
US5026032A (en) * | 1990-02-22 | 1991-06-25 | Southern California Edison | Blade assembly tool |
US5509784A (en) | 1994-07-27 | 1996-04-23 | General Electric Co. | Turbine bucket and wheel assembly with integral bucket shroud |
US6030178A (en) | 1998-09-14 | 2000-02-29 | General Electric Co. | Axial entry dovetail segment for securing a closure bucket to a turbine wheel and methods of installation |
US6158104A (en) * | 1999-08-11 | 2000-12-12 | General Electric Co. | Assembly jig for use with integrally covered bucket blades |
US6190131B1 (en) * | 1999-08-31 | 2001-02-20 | General Electric Co. | Non-integral balanced coverplate and coverplate centering slot for a turbine |
-
2000
- 2000-12-28 US US09/749,446 patent/US6416286B1/en not_active Expired - Fee Related
-
2001
- 2001-12-12 EP EP01985552A patent/EP1348066B1/en not_active Expired - Lifetime
- 2001-12-12 RU RU2002123045/06A patent/RU2002123045A/en not_active Application Discontinuation
- 2001-12-12 WO PCT/US2001/048133 patent/WO2002053875A1/en active IP Right Grant
- 2001-12-12 JP JP2002554360A patent/JP3814581B2/en not_active Expired - Fee Related
- 2001-12-12 KR KR1020027011254A patent/KR20020075457A/en not_active Application Discontinuation
Cited By (41)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2406144A (en) * | 2003-09-19 | 2005-03-23 | Rolls Royce Plc | Gas turbine engine blade retention system using a key |
US7415763B2 (en) | 2005-03-17 | 2008-08-26 | Siemens Aktiengesellschaft | Bending device and method for bending a plate |
EP1703078A1 (en) * | 2005-03-17 | 2006-09-20 | Siemens Aktiengesellschaft | Caulking device and method of caulking the locking tabs in a compressor or turbine |
US20060207309A1 (en) * | 2005-03-17 | 2006-09-21 | Siemens Aktiengesellschaft | Bending device and method for bending a plate |
CN100443209C (en) * | 2005-03-17 | 2008-12-17 | 西门子公司 | Caulking device and method of caulking the locking tabs in a compressor or turbine |
US20070084050A1 (en) * | 2005-10-13 | 2007-04-19 | Siemens Power Generation, Inc. | Turbine vane airfoil reconfiguration method |
US20070084048A1 (en) * | 2005-10-13 | 2007-04-19 | Siemens Westinghouse Power Corporation | Turbine vane airfoil reconfiguration system |
US7503113B2 (en) * | 2005-10-13 | 2009-03-17 | Siemens Energy, Inc. | Turbine vane airfoil reconfiguration system |
US7536783B2 (en) * | 2005-10-13 | 2009-05-26 | Siemens Energy, Inc. | Turbine vane airfoil reconfiguration method |
US20090260206A1 (en) * | 2005-10-13 | 2009-10-22 | Gosling Martin C | Turbine vane airfoil reconfiguration method |
US7730756B2 (en) | 2005-10-13 | 2010-06-08 | Siemens Energy, Inc. | Turbine vane airfoil reconfiguration method |
US20070248464A1 (en) * | 2006-04-25 | 2007-10-25 | General Electric Company | Nested Turbine Bucket Closure Group |
US7517195B2 (en) | 2006-04-25 | 2009-04-14 | General Electric Company | Nested turbine bucket closure group |
US20080253887A1 (en) * | 2007-04-11 | 2008-10-16 | Ronald Ralph Cairo | Aeromechanical Blade |
US7828526B2 (en) * | 2007-04-11 | 2010-11-09 | General Electric Company | Metallic blade having a composite inlay |
US8142161B2 (en) * | 2007-09-20 | 2012-03-27 | General Electric Company | Replaceable staking insert |
US20090077795A1 (en) * | 2007-09-20 | 2009-03-26 | General Electric Company | Replaceable Staking Insert |
EP2211027A1 (en) * | 2008-12-31 | 2010-07-28 | General Electric Company | Apparatus and method for removing compressor blades |
US20100162546A1 (en) * | 2008-12-31 | 2010-07-01 | General Electric Company | Apparatus and method for removing compressor blades |
CN101947727A (en) * | 2008-12-31 | 2011-01-19 | 通用电气公司 | Apparatus and method for removing compressor blades |
US7934302B2 (en) | 2008-12-31 | 2011-05-03 | General Electric Company | Apparatus and method for removing compressor blades |
EP2863016A1 (en) * | 2013-10-16 | 2015-04-22 | Doosan Heavy Industries & Construction Co., Ltd. | Turbine with bucket fixing means |
US10066494B2 (en) | 2013-10-16 | 2018-09-04 | Doosan Heavy Industries & Construction Co., Ltd. | Turbine with bucket fixing means |
EP2868868A1 (en) * | 2013-11-05 | 2015-05-06 | Siemens Aktiengesellschaft | Mounting device and mounting method of a vane |
WO2015067395A1 (en) * | 2013-11-05 | 2015-05-14 | Siemens Aktiengesellschaft | Mounting device and mounting method |
US9381602B2 (en) | 2014-05-14 | 2016-07-05 | General Electric Company | Turbomachine bucket displacement apparatus and method of use |
EP2944760A1 (en) * | 2014-05-14 | 2015-11-18 | General Electric Company | Turbomachine bucket displacement apparatus and method of use |
RU2701925C2 (en) * | 2014-07-08 | 2019-10-02 | Сафран Эйркрафт Энджинз | Method of installing blades on periphery of disc of turbine engine and tool for mounting blade |
US10787919B2 (en) * | 2014-07-08 | 2020-09-29 | Safran Aircraft Engines | Mounting of vanes at the periphery of a turbine engine disc |
CN106471217A (en) * | 2014-07-08 | 2017-03-01 | 赛峰航空器发动机 | Installation in turbine engine disk periphery blade |
US20170145841A1 (en) * | 2014-07-08 | 2017-05-25 | Safran Aircraft Engines | Mounting of vanes at the periphery of a turbine engine disc |
FR3023581A1 (en) * | 2014-07-08 | 2016-01-15 | Snecma | MOUNTING AUBES IN PERIPHERY OF A TURBOMACHINE DISK |
WO2016005687A1 (en) * | 2014-07-08 | 2016-01-14 | Snecma | Mounting of vanes in the periphery of a turbine engine disc |
US20160090841A1 (en) * | 2014-09-29 | 2016-03-31 | United Technologies Corporation | Gas turbine engine blade slot heat shield |
EP3318716A1 (en) * | 2016-11-04 | 2018-05-09 | General Electric Company | Installation or removal of turbine blade at turbine blade base |
EP3318716B2 (en) † | 2016-11-04 | 2023-01-11 | General Electric Company | Installation or removal of turbine blade at turbine blade base |
US11014205B2 (en) | 2016-11-04 | 2021-05-25 | General Electric Company | Installation or removal of turbine blade at turbine blade base |
EP3318716B1 (en) | 2016-11-04 | 2020-02-12 | General Electric Company | Installation or removal of turbine blade at turbine blade base |
US10724385B2 (en) | 2016-11-23 | 2020-07-28 | General Electric Company | Installation or removal of turbine blade at turbine blade base |
EP3327250A1 (en) * | 2016-11-23 | 2018-05-30 | General Electric Company | Installation or removal of turbine blade at turbine blade base |
CN109339870A (en) * | 2018-10-26 | 2019-02-15 | 中国航发湖南动力机械研究所 | Turbine assembly, mortise structure and preparation method thereof |
Also Published As
Publication number | Publication date |
---|---|
JP3814581B2 (en) | 2006-08-30 |
JP2004517245A (en) | 2004-06-10 |
US6416286B1 (en) | 2002-07-09 |
EP1348066B1 (en) | 2007-08-15 |
KR20020075457A (en) | 2002-10-04 |
EP1348066A1 (en) | 2003-10-01 |
WO2002053875A1 (en) | 2002-07-11 |
RU2002123045A (en) | 2004-02-27 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US6416286B1 (en) | System and method for securing a radially inserted integral closure bucket to a turbine rotor wheel assembly having axially inserted buckets | |
US5302086A (en) | Apparatus for retaining rotor blades | |
US3814539A (en) | Rotor sealing arrangement for an axial flow fluid turbine | |
US8128373B2 (en) | Turbine rotor with locking plates and corresponding assembly method | |
CA2388778C (en) | Turbomachine rotor assembly with two bladed-discs separated by a spacer | |
US4221542A (en) | Segmented blade retainer | |
EP1865153B1 (en) | Compressor and method of assembly thereof | |
US8573940B2 (en) | Interlocking knife edge seals | |
US7220099B2 (en) | Sealing arrangement for a rotor of a turbo machine | |
GB2226856A (en) | A boltless rotor blade retainer | |
EP1054137B1 (en) | Mounting an inner shell within an outer turbine casing | |
RU2669117C2 (en) | Turbomachine assembly and methods of assembly thereof | |
US4813850A (en) | Integral side entry control stage blade group | |
US4781534A (en) | Apparatus and method for reducing windage and leakage in steam turbine incorporating axial entry blade | |
US6499959B1 (en) | Steam turbine high strength tangential entry closure bucket and retrofitting methods therefor | |
US5001830A (en) | Method for assembling side entry control stage blades in a steam turbine | |
US6524061B1 (en) | Arrangement for sealing a steam-cooled gas turbine | |
CA1235071A (en) | Seal ring means for a bladed rotor assembly | |
US6572337B1 (en) | Turbine rotor torque transmission | |
US4477227A (en) | Keying for shrunk-on turbine wheels | |
US6786699B2 (en) | Methods of assembling airfoils to turbine components and assemblies thereof | |
US4208165A (en) | Composite stator type turbo-machine | |
US7537430B2 (en) | Stacked reaction steam turbine rotor assembly | |
US9422820B2 (en) | Method and system for self-locking a closure bucket in a rotary machine | |
EP4063617A1 (en) | Retaining assembly with anti-rotation feature |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:ROBERTS, DENNIS WILLIAM;CARUSO, DAVID ALAN;PELECH, JOSEPH MICHAEL;AND OTHERS;REEL/FRAME:011684/0889 Effective date: 20010315 |
|
REMI | Maintenance fee reminder mailed | ||
LAPS | Lapse for failure to pay maintenance fees | ||
STCH | Information on status: patent discontinuation |
Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362 |
|
FP | Lapsed due to failure to pay maintenance fee |
Effective date: 20060709 |