EP3519682B1 - Fixture for restraining a turbine wheel and corresponding method - Google Patents
Fixture for restraining a turbine wheel and corresponding method Download PDFInfo
- Publication number
- EP3519682B1 EP3519682B1 EP17764968.8A EP17764968A EP3519682B1 EP 3519682 B1 EP3519682 B1 EP 3519682B1 EP 17764968 A EP17764968 A EP 17764968A EP 3519682 B1 EP3519682 B1 EP 3519682B1
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- European Patent Office
- Prior art keywords
- fixture
- dovetail
- coupling
- wheel
- mounting section
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
- F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
Definitions
- the apparatus described herein relates generally to turbomachinery and, more specifically, to a fixture for restraining a turbine wheel during a blade removal or installation procedure.
- Turbomachines need regular maintenance to keep up with the cycle type, in which some cases are continuous (6,000 hours/year or more).
- the blades in the turbine section of the turbomachine may need to be replaced.
- the top half of the turbine case is removed, and technicians will restrain the rotor from rolling and begin to remove or replace the turbine blades.
- technicians have tied a strap around a blade and then attached it to somewhere in the turbine compartment. This known method could result in near miss or incidents which involve the rotor rolling due to a broken strap, as well as damage caused to the blade.
- the known method that uses a strap presents a risk of injury, safety concerns, as well as requiring possible replacement parts due to hardware damage.
- EP 2 921 657 A1 discloses a tool for installing or uninstalling a segment of an inner housing of a turbomachine.
- EP 2 752 382 A1 discloses a disc-hoisting tool that is capable of preventing deformation or collapse of the corners of engagement grooves, dropping of the disc, and damage of the surfaces forming the engagement grooves, and is capable of safe disc inversion.
- KR 2012 0092336 A discloses a heat shielding and fixing device for a rotor of a gas turbine comprising a platform unit, a handle unit, a shank unit, and a dovetail unit.
- a turbomachine such as a gas turbine
- the gas turbine 10 includes a compressor 12, a combustor assembly 14, a turbine 16, and a shaft 18. It is to be appreciated that one embodiment of the gas turbine 10 may include a plurality of compressors 12, combustor assemblies 14, turbines 16 and/or shafts 18. The compressor 12 and the turbine 16 are coupled by the shaft 18.
- the shaft 18 may be a single shaft or a plurality of shaft segments coupled together to form the shaft 18.
- the combustor assembly 14 uses a combustible liquid and/or gas fuel, such as a natural gas or a hydrogen rich synthetic gas, to run the gas turbine 10.
- the combustor assembly 14 includes a combustor chamber 20 that is in fluid communication with a fuel pre-mixer 22 that is in fluid communication with an airflow 24 and a fuel source 26.
- the fuel pre-mixer 22 creates an air-fuel mixture, and discharges the air-fuel mixture into the combustor chamber 20, thereby causing a combustion that creates a hot pressurized exhaust gas.
- the combustor chamber 20 directs the hot pressurized gas through a transition piece into the turbine 16, causing rotation of the turbine 16.
- the turbine section 16 has multiple rotatable wheels 17 on which a plurality of blades are mounted. In this example, three stages of turbine wheels 17 are shown, and each wheel would be paired with a stator vane stage (not shown).
- turbomachines include, compressors, gas turbines and steam turbines.
- FIG. 2 illustrates a perspective view of single turbine wheel 17.
- the wheel 17 includes a series of circumferentially arranged dovetail slots 201.
- a turbine blade (not shown) is inserted into each of these dovetail slots 201.
- the blades may need to be removed or installed. In a service example, the blades are removed and the used blades are either repaired and re-installed or just replaced with new blades.
- Turbomachines such as gas or steam turbines, have large and heavy components.
- the wheel 17 with blades attached is one example of a heavy component, and this wheel is balanced to reduce vibrations.
- a fixture 210 for restraining the wheel 17 is the focus of this disclosure, and will be described in greater detail hereinbelow.
- FIG. 3 illustrates a perspective view of the fixture 210 for restraining a wheel 17 of a turbomachine 10.
- the fixture 210 includes a dovetail section 320 adapted for insertion into the dovetail slot 201 of the wheel 17.
- the dovetail section 320 has a dovetail shaped profile or fir tree shaped profile, which include a plurality of ridges and valleys, adapted to interlock with corresponding notches or recesses in the dovetail slot 201 of wheel 17.
- the peak height of each ridge decreases in height as the peaks become nearer to the bottom (radially inner portion) of the dovetail section.
- a mounting section 330 is located on top of and adjacent to, or formed integrally with, the dovetail section 320.
- Fixture 210 also includes at least one coupling 340 attached to the mounting section 330.
- the coupling 340 may be a coupling ring, hoist ring, shackle or other suitable coupling device.
- a fastener 342, such as a shoulder head screw with washer, may be used to attach the coupling ring 340 to the mounting section 330.
- the coupling 340 may be attached so that it swivels about an axial axis, and so that it can be oriented as shown in FIG. 3 or FIG. 4 , or any position in between the illustrated positions.
- the coupling 340 is secured to a stationary anchoring point via a restraint.
- stops 350, 360, 450 are used on axial ends or axial faces thereof.
- the fixture 210 has a forward axial face (or end) 370 and an aft axial face (or end) 371.
- the stop 350 is configured as a T-shaped stop and the top of the "T" extends past the outline of the dovetail slot 201. In this manner, the stop 350 rests against a forward axial face of wheel 17 and prevents axial movement of the fixture.
- the stop 350 is attached to the dovetail section 320 by means of a fastener 352, such as a shoulder screw or bolt.
- the aft axial face 371 has a fastener 362 and washer 360 that function as a stop.
- the washer 360 is sized so that it overlaps the dovetail slot boundary, and in so doing prevent axial movement of the fixture.
- FIG. 4 illustrates a perspective view of the fixture 210 for restraining a wheel 17 of a turbomachine 10.
- Wheels 17 may have varying thicknesses. A thicker wheel may require a stop 350 as shown in FIG. 3 . However, for a thinner wheel a stop 450 may be used. Stop 450 is comprised of a plate having holes for one or more fasteners 452. The fasteners 452 may be configured to screw into an axial face of mounting section 330 (as shown) and/or into dovetail section 320. As an example only, the axial length of the dovetail section 320 and mounting section 330 may be sized to match the thinnest wheel of the target turbomachine.
- T-stops 350 may be used to adjust the fixture to thicker wheels, and the stop plate 450 may be used on the thinnest wheel.
- the various stops 350, 450, 360 may also be fabricated from 4140-HT (heat treated) high alloy tool steel, or any other suitable material.
- both the aft end and the forward end have one or more internally threaded holes 481, 482 adapted for securing fasteners.
- the mounting section 330 includes at least one internally threaded hole 483 adapted for attaching the coupling 340 to the mounting section 330, and fastener 342 and an optional washer secures the coupling ring 340 to the mounting section 330 via the threaded hole 483.
- the mounting section 330 includes at least one attachment point configured for securing the fixture 210, and this attachment point can be the coupling 340, the threaded hole 483, or any other suitable device/feature located on or in the mounting section.
- FIG. 5 illustrates an exploded, perspective view of the fixture 210 in a dovetail slot 201 of a wheel 17 of a turbomachine.
- the fixture 210 is inserted into the dovetail slot 201 and is restrained from moving radially or circumferentially. However, the fixture could slide out axially forward or aft. To prevent this, axial stops are installed.
- the forward axial stop 350 is attached/secured to the forward side of the fixture.
- the aft axial stop 360 is then installed on the aft side of the fixture. When both stops are installed the fixture is locked to the wheel.
- the coupling 340 may then be attached to the mounting section 330.
- one or more coupling rings may be used, for example, one coupling ring on each axial face/end of the fixture, or one or more coupling rings may be located on the top (or radially outer surface) of the mounting section 330, or any combination thereof.
- dovetail section 320 has a straight profile adapted for use with a straight dovetail slot 201.
- FIG. 6 illustrates a top, cross-sectional view of the fixture located in a dovetail slot.
- the dovetail section 620 has an angled profile adapted for use with an angled dovetail slot 601.
- the axial extending sides of slot 601 are not orthogonal to the axial faces thereof.
- FIG. 7 illustrates a top, cross-sectional view of the fixture located in a dovetail slot.
- the dovetail section 720 has a curved profile adapted for use with a curved dovetail slot 701. This curved, axial-entry type of configuration may be used in steam turbines, or any other turbomachine as desired.
- FIG. 8 illustrates a partial side view of the fixture installed in a wheel and connected to a stationary anchoring point on the turbomachine's casing.
- the stationary anchoring point 800 may include at least one counterbore assembly 810 having a coupling ring 812 attached thereto.
- the counterbore assembly 800 is adapted to be secured to a stationary structure 820, such as a turbomachine casing, shell or flange.
- the stationary structure 820 is the bottom half of a turbine case.
- the counterbore assembly 810 has a counterbore insert 814 that has a portion adapted to extend into a hole 822 of the turbine case 820. A head of the counterbore insert 814 is larger than the hole 822 diameter.
- the shaft portion of the counterbore insert (the portion that goes into the turbine casing hole 822) includes an internally threaded hole that is configured for use with fastener 813.
- the counterbore insert may be a cylindrical element having two opposing internally threaded holes, one for use with fastener 813 and another for a bolt (e.g., which would take the place of 814).
- the fastener 813 connects the coupling ring 812 to the counterbore insert 814, and therefore to the turbine case 820.
- a washer 815 may be interposed between the turbine case 820 and coupling ring 812.
- the coupling 340 is secured to the coupling ring 812 on stationary anchoring point 800 by restraint 830, which may be a chain, chain with come-along, cable or wire. Come-alongs may also be referred to as ratchet pullers, ratchet mechanisms or cable (or chain) pullers. Lever chain hoists or similarly functioning devices may be used as well for restraint 830.
- restraint 830 may be a chain, chain with come-along, cable or wire. Come-alongs may also be referred to as ratchet pullers, ratchet mechanisms or cable (or chain) pullers.
- Lever chain hoists or similarly functioning devices may be used as well for restraint 830.
- FIG. 9 illustrates a perspective view of the fixture 210 in a dovetail slot 201 of a wheel 17 of a turbomachine.
- the fixture 201 includes two couplings 340 and 940.
- Coupling ring 940 is attached to a forward end of the mounting section and is located on a forward axial side of the wheel 17, and coupling 340 is attached to an aft end of the mounting section and is located on the aft axial side of wheel 17.
- This type of configuration allows two restraints 830 to be attached to the fixture.
- the restraints may extend in the same direction, or extend in generally opposing directions.
- FIG. 10 illustrates a partial side view of the fixture 201 of FIG. 9 installed in a dovetail slot of wheel 17, and the fixture is connected to two stationary anchoring points on the turbomachine's casing.
- the first stationary anchoring point 800 is connected to the fixture 210 via restraint 830 (shown by a dotted line).
- the second stationary anchoring point 800' is connected to the fixture 210 via restraint 830' (shown by a dotted line).
- the two stationary anchoring points 800, 800' may be on opposing sides of the turbine case.
- the restraints 830, 830' may be tightened by the use of a come-along 1010 or 1010'.
- the restraints 830 do not need to be excessively tightened, as simply taking up the slack will be sufficient to prevent or restrain undesired wheel rotation. It is also to be understood that one or more coupling rings could be attached onto the top of the mounting section 330.
- FIG. 11 is a flowchart for a method 1100 for restraining a wheel 17 of a turbomachine.
- the fixture 210 is inserted into a dovetail slot 201 in the wheel 17.
- the fixture 210 includes a dovetail section 320 adapted for insertion into the dovetail slot 201, and a mounting section 330 located adjacent to, or formed integrally with, the dovetail section 320.
- the mounting section 330 is adapted to connect to at least one coupling 340.
- Step 1110 may also include placing a washer 360 over a fastener 362, and then inserting the fastener 362 into a threaded hole in the dovetail section 320.
- the washer is adapted to extend over or overlap an axial face of the dovetail slot 201.
- at least one coupling 340 may be attached to the mounting section 330 or the fixture 210 in general.
- step 1120 at least one counterbore assembly 810 is attached to a stationary structure 820.
- a restraint 830 is connected to the coupling 340 and the at least one counterbore assembly 810. Steps 1120 and 1130 may be repeated until the desired number of restraints are installed.
- Connecting step 1130 may also include attaching a come-along 1010 having a strap, chain 830 or cable to both the coupling 340 and the counterbore assembly 810 or other coupling ring 812 located on the stationary support.
- step 1140 the restraints are tightened to restrain or prevent the wheel 17 from rotating.
- FIG. 12 illustrates a perspective view of the fixture 1200.
- the fixture 1200 includes a dovetail section 1210 adapted for insertion into the dovetail slot 201 of the wheel 17.
- the dovetail section 1210 has a dovetail shaped profile or fir tree shaped profile, which includes a plurality of ridges and valleys, adapted to interlock with corresponding notches or recesses in the dovetail slot 201 of wheel 17.
- the peak height of each ridge decreases in height as the peaks become nearer to the bottom (radially inner portion) of the dovetail section.
- a mounting section 1220 is located on top of and adjacent to, or formed integrally with, the dovetail section 1210.
- the dovetail section 1210 and mounting section 1220 are cast as, or machined from, a single piece of material, and this material may be 4140-HT (heat treated) high alloy tool steel as it has good strength, toughness, and mechanical properties. Alternatively, any other suitable material may be used as desired in the specific application.
- Fixture 1200 also includes at least one coupling 1230 attached to the mounting section 1220.
- the coupling 1230 may be a coupling ring, hoist ring, shackle or other suitable coupling device.
- the coupling 1230 is attached to the top of the mounting section (as shown).
- a threaded fastener (not shown) that is attached to the coupling 1230 is screwed into an internally threaded hole (not shown) in the top 1221 of the mounting section 1220.
- a washer may be interposed between the bottom of the coupling 1230 and the top 1221 of the mounting section, if desired.
- the coupling 1230 may also be attached so that it swivels about a radial axis (with respect to the turbomachine).
- a back plate 1240 is attached to a first axial end of the mounting section, and is adapted to extend over an axial face of the dovetail slot to restrain axial movement of the fixture.
- the back plate 1240 may be a substantially rectangular and planar member, as shown.
- a plurality of fasteners 1242 (three are shown) may be used to attach the back plate 1240 to the mounting section 1220.
- the first axial end of the mounting section includes a plurality of internally threaded holes configured for use with fasteners 1242.
- the fasteners 1242 may be screws, bolts or any other suitable fastening device.
- a sliding block 1250 may be attached to the top of the mounting section 1220 near an opposing (or second) axial end of the mounting section.
- the sliding block 1250 is adapted to extend over an axial face of the dovetail slot 201 and restrain axial movement of the fixture 1200.
- the sliding block 1250 is adapted to slide up and down along a radial axis, with respect to the turbomachine, so that the fixture 1200 can be inserted into the dovetail slot 210 when the sliding block is at an upper position.
- the fixture 1200 is restrained from axial movement when the sliding block 1250 is in a lower position, as shown.
- Two pins 1252 are attached to the mounting section and act as guides for the radial (or up and down) movement of the sliding block.
- the pins 1252 can be screwed into the mounting section via corresponding threaded holes.
- a lock screw 1254 such as a shoulder screw, is used to lock the sliding block in place and prevent radial movement thereof.
- the lock screw 1254 also locks the sliding block in place to prevent axial movement of the fixture.
- the coupling 1230 is secured to a stationary anchoring point via a restraint.
- FIG. 13 illustrates a perspective view of the fixture 1300.
- the fixture 1300 includes two couplings 1331 and 1332. Couplings 1331 and 1332 are both attached to a top portion of the mounting section 1220. This type of configuration allows two restraints 830 to be attached to the fixture. The restraints may extend in the same direction, or extend in generally opposing directions.
Description
- The apparatus described herein relates generally to turbomachinery and, more specifically, to a fixture for restraining a turbine wheel during a blade removal or installation procedure.
- Turbomachines need regular maintenance to keep up with the cycle type, in which some cases are continuous (6,000 hours/year or more). During an inspection maintenance outage, the blades in the turbine section of the turbomachine may need to be replaced. The top half of the turbine case is removed, and technicians will restrain the rotor from rolling and begin to remove or replace the turbine blades. To restrain the rotor, technicians have tied a strap around a blade and then attached it to somewhere in the turbine compartment. This known method could result in near miss or incidents which involve the rotor rolling due to a broken strap, as well as damage caused to the blade. The known method that uses a strap presents a risk of injury, safety concerns, as well as requiring possible replacement parts due to hardware damage.
-
EP 2 921 657 A1 discloses a tool for installing or uninstalling a segment of an inner housing of a turbomachine.EP 2 752 382 A1 discloses a disc-hoisting tool that is capable of preventing deformation or collapse of the corners of engagement grooves, dropping of the disc, and damage of the surfaces forming the engagement grooves, and is capable of safe disc inversion.KR 2012 0092336 A - The invention is defined by the appended claims. In the following, any method and/or apparatus that do not fall within the scope of the claims are to be understood as examples helpful in understanding the invention.
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FIG. 1 is a schematic illustration of a gas turbine system. -
FIG. 2 illustrates a perspective view of single turbine wheel. -
FIG. 3 illustrates a perspective view of a fixture for restraining a wheel of a turbomachine, according to an aspect not forming part of the present invention. -
FIG. 4 illustrates a perspective view of the fixture for restraining a wheel of a turbomachine, according to an aspect not forming part of the present invention. -
FIG. 5 illustrates an exploded, perspective view of the fixture in a dovetail slot of a wheel, according to an aspect not forming part of the present invention. -
FIG. 6 illustrates a top, cross-sectional view of the fixture located in a dovetail slot. -
FIG. 7 illustrates a top, cross-sectional view of the fixture located in a curved, axial-entry type of dovetail slot. -
FIG. 8 illustrates a partial side view of the fixture installed in a wheel and connected to a stationary anchoring point on the turbomachine's casing. -
FIG. 9 illustrates a perspective view of a fixture located in a dovetail slot of a wheel of a turbomachine, according to an aspect of the invention. -
FIG. 10 illustrates a partial side view of the fixture ofFIG. 9 installed in a dovetail slot of wheel, and the fixture is connected to two stationary anchoring points on the turbomachine's casing. -
FIG. 11 is a flowchart for a method for restraining a wheel of a turbomachine. -
FIG. 12 illustrates a perspective view of a fixture, according to an aspect not forming part of the present invention. -
FIG. 13 illustrates a perspective view of a fixture having two coupling mounted thereon, according to an aspect not forming part of the invention. - One or more specific aspects/embodiments of the present invention will be described below. In an effort to provide a concise description of these aspects/embodiments, all features of an actual implementation may not be described in the specification. It should be appreciated that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions must be made to achieve the developers' specific goals, such as compliance with machine-related, system-related and business-related constraints, which may vary from one implementation to another. Moreover, it should be appreciated that such a development effort might be complex and time consuming, but would nevertheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill having the benefit of this disclosure.
- When introducing elements of various embodiments of the present invention, the articles "a," "an," and "the" are intended to mean that there are one or more of the elements. The terms "comprising," "including," and "having" are intended to be inclusive and mean that there may be additional elements other than the listed elements. Any examples of operating parameters and/or environmental conditions are not exclusive of other parameters/conditions of the disclosed embodiments. Additionally, it should be understood that references to "one embodiment", "one aspect" or "an embodiment" or "an aspect" of the present invention are not intended to be interpreted as excluding the existence of additional embodiments or aspects that also incorporate the recited features.
- Referring to
FIG. 1 , a turbomachine, such as a gas turbine, is schematically illustrated withreference numeral 10. Thegas turbine 10 includes acompressor 12, acombustor assembly 14, aturbine 16, and ashaft 18. It is to be appreciated that one embodiment of thegas turbine 10 may include a plurality ofcompressors 12,combustor assemblies 14,turbines 16 and/orshafts 18. Thecompressor 12 and theturbine 16 are coupled by theshaft 18. Theshaft 18 may be a single shaft or a plurality of shaft segments coupled together to form theshaft 18. - The
combustor assembly 14 uses a combustible liquid and/or gas fuel, such as a natural gas or a hydrogen rich synthetic gas, to run thegas turbine 10. Thecombustor assembly 14 includes acombustor chamber 20 that is in fluid communication with a fuel pre-mixer 22 that is in fluid communication with anairflow 24 and afuel source 26. The fuel pre-mixer 22 creates an air-fuel mixture, and discharges the air-fuel mixture into thecombustor chamber 20, thereby causing a combustion that creates a hot pressurized exhaust gas. Thecombustor chamber 20 directs the hot pressurized gas through a transition piece into theturbine 16, causing rotation of theturbine 16. Rotation of theturbine 16 causes theshaft 18 to rotate, thereby compressing air as it flows into thecompressor 12. Theturbine section 16 has multiplerotatable wheels 17 on which a plurality of blades are mounted. In this example, three stages ofturbine wheels 17 are shown, and each wheel would be paired with a stator vane stage (not shown). In general, turbomachines include, compressors, gas turbines and steam turbines. -
FIG. 2 illustrates a perspective view ofsingle turbine wheel 17. Thewheel 17 includes a series of circumferentially arrangeddovetail slots 201. A turbine blade (not shown) is inserted into each of thesedovetail slots 201. During service (or assembly) of theturbomachine 10, the blades may need to be removed or installed. In a service example, the blades are removed and the used blades are either repaired and re-installed or just replaced with new blades. Turbomachines, such as gas or steam turbines, have large and heavy components. Thewheel 17 with blades attached is one example of a heavy component, and this wheel is balanced to reduce vibrations. However, as the blades are removed fromwheel 17, the wheel's center of gravity changes, and the wheel will want to rotate in either a clockwise or counter-clockwise direction. This can present a serious safety hazard to people working on the turbine, as an unexpected wheel rotation can force a blade (or other wheel component) onto personnel. Therefore, it would be desirable to restrain the rotor from rotation during a blade removal or installation procedure. Afixture 210 for restraining thewheel 17 is the focus of this disclosure, and will be described in greater detail hereinbelow. -
FIG. 3 illustrates a perspective view of thefixture 210 for restraining awheel 17 of aturbomachine 10. Thefixture 210 includes adovetail section 320 adapted for insertion into thedovetail slot 201 of thewheel 17. Thedovetail section 320 has a dovetail shaped profile or fir tree shaped profile, which include a plurality of ridges and valleys, adapted to interlock with corresponding notches or recesses in thedovetail slot 201 ofwheel 17. Typically, the peak height of each ridge decreases in height as the peaks become nearer to the bottom (radially inner portion) of the dovetail section. A mountingsection 330 is located on top of and adjacent to, or formed integrally with, thedovetail section 320. In one example, thedovetail section 320 and mountingsection 330 are cast as, or machined from, a single piece of material, and this material may be 4140-HT (heat treated) high alloy tool steel as it has good strength, toughness, and mechanical properties. Alternatively, any other suitable material may be used as desired in the specific application.Fixture 210 also includes at least onecoupling 340 attached to the mountingsection 330. Thecoupling 340 may be a coupling ring, hoist ring, shackle or other suitable coupling device. Afastener 342, such as a shoulder head screw with washer, may be used to attach thecoupling ring 340 to the mountingsection 330. Thecoupling 340 may be attached so that it swivels about an axial axis, and so that it can be oriented as shown inFIG. 3 or FIG. 4 , or any position in between the illustrated positions. - In use, the
coupling 340 is secured to a stationary anchoring point via a restraint. To lock the fixture into thedovetail slot 201, stops 350, 360, 450 are used on axial ends or axial faces thereof. Thefixture 210 has a forward axial face (or end) 370 and an aft axial face (or end) 371. Thestop 350 is configured as a T-shaped stop and the top of the "T" extends past the outline of thedovetail slot 201. In this manner, thestop 350 rests against a forward axial face ofwheel 17 and prevents axial movement of the fixture. Thestop 350 is attached to thedovetail section 320 by means of afastener 352, such as a shoulder screw or bolt. The aftaxial face 371 has afastener 362 andwasher 360 that function as a stop. Thewasher 360 is sized so that it overlaps the dovetail slot boundary, and in so doing prevent axial movement of the fixture. When both stops 350, 360 are installed, thedovetail section 320 is locked in thedovetail slot 201, and the fixture will not slide out of theslot 201. -
FIG. 4 illustrates a perspective view of thefixture 210 for restraining awheel 17 of aturbomachine 10.Wheels 17 may have varying thicknesses. A thicker wheel may require astop 350 as shown inFIG. 3 . However, for a thinner wheel astop 450 may be used. Stop 450 is comprised of a plate having holes for one ormore fasteners 452. Thefasteners 452 may be configured to screw into an axial face of mounting section 330 (as shown) and/or intodovetail section 320. As an example only, the axial length of thedovetail section 320 and mountingsection 330 may be sized to match the thinnest wheel of the target turbomachine. In this manner, T-stops 350 may be used to adjust the fixture to thicker wheels, and thestop plate 450 may be used on the thinnest wheel. The various stops 350, 450, 360 may also be fabricated from 4140-HT (heat treated) high alloy tool steel, or any other suitable material. In addition, both the aft end and the forward end have one or more internally threadedholes section 330 includes at least one internally threadedhole 483 adapted for attaching thecoupling 340 to the mountingsection 330, andfastener 342 and an optional washer secures thecoupling ring 340 to the mountingsection 330 via the threadedhole 483. The mountingsection 330 includes at least one attachment point configured for securing thefixture 210, and this attachment point can be thecoupling 340, the threadedhole 483, or any other suitable device/feature located on or in the mounting section. -
FIG. 5 illustrates an exploded, perspective view of thefixture 210 in adovetail slot 201 of awheel 17 of a turbomachine. Thefixture 210 is inserted into thedovetail slot 201 and is restrained from moving radially or circumferentially. However, the fixture could slide out axially forward or aft. To prevent this, axial stops are installed. The forwardaxial stop 350 is attached/secured to the forward side of the fixture. The aftaxial stop 360 is then installed on the aft side of the fixture. When both stops are installed the fixture is locked to the wheel. Thecoupling 340 may then be attached to the mountingsection 330. It is to be understood that one or more coupling rings may be used, for example, one coupling ring on each axial face/end of the fixture, or one or more coupling rings may be located on the top (or radially outer surface) of the mountingsection 330, or any combination thereof. As shown inFIG. 5 dovetail section 320 has a straight profile adapted for use with astraight dovetail slot 201. -
FIG. 6 illustrates a top, cross-sectional view of the fixture located in a dovetail slot. Thedovetail section 620 has an angled profile adapted for use with anangled dovetail slot 601. The axial extending sides ofslot 601 are not orthogonal to the axial faces thereof.FIG. 7 illustrates a top, cross-sectional view of the fixture located in a dovetail slot. Thedovetail section 720 has a curved profile adapted for use with acurved dovetail slot 701. This curved, axial-entry type of configuration may be used in steam turbines, or any other turbomachine as desired. -
FIG. 8 illustrates a partial side view of the fixture installed in a wheel and connected to a stationary anchoring point on the turbomachine's casing. Thestationary anchoring point 800 may include at least onecounterbore assembly 810 having acoupling ring 812 attached thereto. Thecounterbore assembly 800 is adapted to be secured to astationary structure 820, such as a turbomachine casing, shell or flange. In the example shown, thestationary structure 820 is the bottom half of a turbine case. Thecounterbore assembly 810 has acounterbore insert 814 that has a portion adapted to extend into ahole 822 of theturbine case 820. A head of thecounterbore insert 814 is larger than thehole 822 diameter. The shaft portion of the counterbore insert (the portion that goes into the turbine casing hole 822) includes an internally threaded hole that is configured for use withfastener 813. Alternatively, the counterbore insert may be a cylindrical element having two opposing internally threaded holes, one for use withfastener 813 and another for a bolt (e.g., which would take the place of 814). Thefastener 813 connects thecoupling ring 812 to thecounterbore insert 814, and therefore to theturbine case 820. If desired awasher 815 may be interposed between theturbine case 820 andcoupling ring 812. Thecoupling 340 is secured to thecoupling ring 812 onstationary anchoring point 800 byrestraint 830, which may be a chain, chain with come-along, cable or wire. Come-alongs may also be referred to as ratchet pullers, ratchet mechanisms or cable (or chain) pullers. Lever chain hoists or similarly functioning devices may be used as well forrestraint 830. -
FIG. 9 illustrates a perspective view of thefixture 210 in adovetail slot 201 of awheel 17 of a turbomachine. Thefixture 201 includes twocouplings Coupling ring 940 is attached to a forward end of the mounting section and is located on a forward axial side of thewheel 17, andcoupling 340 is attached to an aft end of the mounting section and is located on the aft axial side ofwheel 17. This type of configuration allows tworestraints 830 to be attached to the fixture. The restraints may extend in the same direction, or extend in generally opposing directions. -
FIG. 10 illustrates a partial side view of thefixture 201 ofFIG. 9 installed in a dovetail slot ofwheel 17, and the fixture is connected to two stationary anchoring points on the turbomachine's casing. The firststationary anchoring point 800 is connected to thefixture 210 via restraint 830 (shown by a dotted line). The second stationary anchoring point 800' is connected to thefixture 210 via restraint 830' (shown by a dotted line). The two stationary anchoring points 800, 800' may be on opposing sides of the turbine case. Therestraints 830, 830' may be tightened by the use of a come-along 1010 or 1010'. However, therestraints 830 do not need to be excessively tightened, as simply taking up the slack will be sufficient to prevent or restrain undesired wheel rotation. It is also to be understood that one or more coupling rings could be attached onto the top of the mountingsection 330. -
FIG. 11 is a flowchart for amethod 1100 for restraining awheel 17 of a turbomachine. Instep 1110 thefixture 210 is inserted into adovetail slot 201 in thewheel 17. Thefixture 210 includes adovetail section 320 adapted for insertion into thedovetail slot 201, and a mountingsection 330 located adjacent to, or formed integrally with, thedovetail section 320. The mountingsection 330 is adapted to connect to at least onecoupling 340.Step 1110 may also include placing awasher 360 over afastener 362, and then inserting thefastener 362 into a threaded hole in thedovetail section 320. The washer is adapted to extend over or overlap an axial face of thedovetail slot 201. In addition, at least onecoupling 340 may be attached to the mountingsection 330 or thefixture 210 in general. - In
step 1120, at least onecounterbore assembly 810 is attached to astationary structure 820. In step 1130 arestraint 830 is connected to thecoupling 340 and the at least onecounterbore assembly 810.Steps step 1130 may also include attaching a come-along 1010 having a strap,chain 830 or cable to both thecoupling 340 and thecounterbore assembly 810 orother coupling ring 812 located on the stationary support. Instep 1140, the restraints are tightened to restrain or prevent thewheel 17 from rotating. -
FIG. 12 illustrates a perspective view of thefixture 1200. Thefixture 1200 includes adovetail section 1210 adapted for insertion into thedovetail slot 201 of thewheel 17. Thedovetail section 1210 has a dovetail shaped profile or fir tree shaped profile, which includes a plurality of ridges and valleys, adapted to interlock with corresponding notches or recesses in thedovetail slot 201 ofwheel 17. Typically, the peak height of each ridge decreases in height as the peaks become nearer to the bottom (radially inner portion) of the dovetail section. A mountingsection 1220 is located on top of and adjacent to, or formed integrally with, thedovetail section 1210. In one example, thedovetail section 1210 and mountingsection 1220 are cast as, or machined from, a single piece of material, and this material may be 4140-HT (heat treated) high alloy tool steel as it has good strength, toughness, and mechanical properties. Alternatively, any other suitable material may be used as desired in the specific application.Fixture 1200 also includes at least onecoupling 1230 attached to themounting section 1220. Thecoupling 1230 may be a coupling ring, hoist ring, shackle or other suitable coupling device. Thecoupling 1230 is attached to the top of the mounting section (as shown). In this example, a threaded fastener (not shown) that is attached to thecoupling 1230 is screwed into an internally threaded hole (not shown) in the top 1221 of the mountingsection 1220. A washer may be interposed between the bottom of thecoupling 1230 and the top 1221 of the mounting section, if desired. Thecoupling 1230 may also be attached so that it swivels about a radial axis (with respect to the turbomachine). - A
back plate 1240 is attached to a first axial end of the mounting section, and is adapted to extend over an axial face of the dovetail slot to restrain axial movement of the fixture. Theback plate 1240 may be a substantially rectangular and planar member, as shown. A plurality of fasteners 1242 (three are shown) may be used to attach theback plate 1240 to themounting section 1220. The first axial end of the mounting section includes a plurality of internally threaded holes configured for use withfasteners 1242. Thefasteners 1242 may be screws, bolts or any other suitable fastening device. - A sliding
block 1250 may be attached to the top of the mountingsection 1220 near an opposing (or second) axial end of the mounting section. The slidingblock 1250 is adapted to extend over an axial face of thedovetail slot 201 and restrain axial movement of thefixture 1200. In addition, the slidingblock 1250 is adapted to slide up and down along a radial axis, with respect to the turbomachine, so that thefixture 1200 can be inserted into thedovetail slot 210 when the sliding block is at an upper position. Thefixture 1200 is restrained from axial movement when the slidingblock 1250 is in a lower position, as shown. Twopins 1252 are attached to the mounting section and act as guides for the radial (or up and down) movement of the sliding block. Thepins 1252 can be screwed into the mounting section via corresponding threaded holes. Alock screw 1254, such as a shoulder screw, is used to lock the sliding block in place and prevent radial movement thereof. Thelock screw 1254 also locks the sliding block in place to prevent axial movement of the fixture. In use, thecoupling 1230 is secured to a stationary anchoring point via a restraint. When both theback plate 1240 and slidingblock 1250 are installed and locked in place, thedovetail section 1210 is locked in thedovetail slot 201, and thefixture 1200 will not slide out of theslot 201. -
FIG. 13 illustrates a perspective view of thefixture 1300. Thefixture 1300 includes twocouplings Couplings section 1220. This type of configuration allows tworestraints 830 to be attached to the fixture. The restraints may extend in the same direction, or extend in generally opposing directions. - This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.
Claims (15)
- A fixture (210) for restraining a wheel (17) of a turbomachine (10) with restraints (830, 830'), the turbomachine comprising two stationary anchoring points (800) and the wheel comprising a dovetail slot (201), the fixture comprising:a dovetail section (320) adapted for insertion into the dovetail slot of the wheel;a mounting section (330) located adjacent to, or formed integrally with, the dovetail section;a first coupling (340) attached to an aft end of the mounting section; anda second coupling (940) attached to a forward end of the mounting section;wherein the first and the second couplings are each configured for securing the fixture to one of the stationary anchoring points via the restraints.
- The fixture of claim 1, the dovetail section having a dovetail shaped or fir tree shaped profile adapted to interlock with corresponding notches or recesses in the dovetail slot of the wheel.
- The fixture of claim 2, the fixture further comprising an aft end and a forward end, at least one of the aft end and the forward end having a threaded hole (483) adapted for securing a fastener (342).
- The fixture of claim 3, further comprising the fastener and a washer secured by the threaded hole, and a stop (350) located on an end opposing the threaded hole, the washer and the stop adapted to lock the dovetail section to the dovetail slot.
- The fixture of claim 3, at least one of the aft end or the forward end having:
a T-shaped stop or a rectangular shaped stop. - The fixture of claim 1, the dovetail section having one of:a straight profile adapted for use with a straight dovetail slot, oran angled profile adapted for use with an angled dovetail slot, ora curved profile adapted for use with a curved dovetail slot.
- The fixture of claim 1, the mounting section further comprising:
at least one threaded hole (481, 482) adapted for attaching the coupling to the mounting section, and wherein a fastener secures the one of the first and second couplings to the mounting section via the at least one threaded hole. - The fixture of claim 1, further comprising:
a coupling (1230) attached to the top of the mounting section. - A turbomachine comprising:a wheel;a stationary anchoring point;the wheel comprising a dovetail slot; andthe fixture of any one of the preceding claims.
- The turbomachine of claim 9, the stationary anchoring point further comprising:
at least one counterbore assembly (810) having a coupling (812) attached thereto, the at least one counterbore assembly adapted to be secured to a stationary structure (820). - The turbomachine of claim 10, wherein the stationary structure is at least one of:
a shell, a flange or a casing of the turbomachine. - A method for restraining a wheel (17) of a turbomachine (10), the method comprising:inserting a fixture (210) into a dovetail slot (201) in the wheel, the fixture comprising:a dovetail section (320) adapted for insertion into the dovetail slot;a mounting section (330) located adjacent to, or formed integrally with, the dovetail section, the mounting section adapted to connect to at least one coupling;attaching a first coupling (340) to an aft end of the mounting section; andattaching a second coupling (940) to a forward end of the mounting section;attaching at least one counterbore assembly (810) to a stationary structure (820);connecting a restraint to the at least one of the first and second coupling and the at least one counterbore assembly; andsecuring the fixture to a stationary anchoring point (800) via the restraint.
- The method of claim 12, the stationary structure comprising at least one of:
a shell, a flange or a casing of the turbomachine. - The method of claim 13, the inserting a fixture step further comprising:placing a washer or a stop over a fastener (342);inserting the fastener into a threaded hole (483) in the dovetail section, wherein the washer or the stop is adapted to extend over an axial face of the dovetail slot; andattaching the at least one coupling to the mounting section.
- The method of claim 12, the connecting step further comprising:
attaching a come-along having a strap, chain (830) or cable to both the at least one coupling and the at least one counterbore assembly, and tightening the come-along to restrain the wheel.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US15/277,354 US10100677B2 (en) | 2016-09-27 | 2016-09-27 | Fixture for restraining a turbine wheel |
US15/277,327 US10024164B2 (en) | 2016-09-27 | 2016-09-27 | Fixture for restraining a turbine wheel |
PCT/US2017/049106 WO2018063667A1 (en) | 2016-09-27 | 2017-08-29 | Fixture for restraining a turbine wheel and corresponding method |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3519682A1 EP3519682A1 (en) | 2019-08-07 |
EP3519682B1 true EP3519682B1 (en) | 2020-12-23 |
Family
ID=59846667
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP17764968.8A Active EP3519682B1 (en) | 2016-09-27 | 2017-08-29 | Fixture for restraining a turbine wheel and corresponding method |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP3519682B1 (en) |
JP (1) | JP6740466B2 (en) |
WO (1) | WO2018063667A1 (en) |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR101184327B1 (en) * | 2011-02-11 | 2012-09-19 | 한국중부발전(주) | Dummy Blade for Gas Turbine Heat Shield Positioning and Gas Turbine Apparatus using Dummy Blade for Gas Turbine Heat Shield Positioning |
JP5791430B2 (en) * | 2011-08-29 | 2015-10-07 | 三菱日立パワーシステムズ株式会社 | Disc lifting jig |
EP2921657A1 (en) * | 2014-03-20 | 2015-09-23 | Alstom Technology Ltd | Tool for removing an inner casing from a turbomachine |
-
2017
- 2017-08-29 WO PCT/US2017/049106 patent/WO2018063667A1/en unknown
- 2017-08-29 EP EP17764968.8A patent/EP3519682B1/en active Active
- 2017-08-29 JP JP2019513851A patent/JP6740466B2/en active Active
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
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WO2018063667A1 (en) | 2018-04-05 |
JP2019533110A (en) | 2019-11-14 |
JP6740466B2 (en) | 2020-08-12 |
EP3519682A1 (en) | 2019-08-07 |
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