US20150078892A1 - Eccentric coupling device and method for coupling mating casings in a turbomachine - Google Patents
Eccentric coupling device and method for coupling mating casings in a turbomachine Download PDFInfo
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- US20150078892A1 US20150078892A1 US14/488,661 US201414488661A US2015078892A1 US 20150078892 A1 US20150078892 A1 US 20150078892A1 US 201414488661 A US201414488661 A US 201414488661A US 2015078892 A1 US2015078892 A1 US 2015078892A1
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- United States
- Prior art keywords
- bore hole
- casing
- flange
- bushing
- pin
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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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
- B25B27/14—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for assembling objects other than by press fit or detaching same
- B25B27/16—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for assembling objects other than by press fit or detaching same abutted flanges
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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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
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- 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
- Y10T29/49826—Assembling or joining
- Y10T29/49895—Associating parts by use of aligning means [e.g., use of a drift pin or a "fixture"]
- Y10T29/49899—Associating parts by use of aligning means [e.g., use of a drift pin or a "fixture"] by multiple cooperating aligning means
Definitions
- the present disclosure relates generally to turbomachines, such as gas turbine systems, and more particularly to methods and apparatus for coupling mating casings, such as turbine casings and exhaust casings, of turbomachines together.
- a conventional gas turbine system includes a compressor section, a combustor section, and at least one turbine section.
- the compressor section is configured to compress air as the air flows through the compressor section.
- the air is then flowed from the compressor section to the combustor section, where it is mixed with fuel and combusted, generating a hot gas flow.
- the hot gas flow is provided to the turbine section, which utilizes the hot gas flow by extracting energy from it to power the compressor, an electrical generator, and other various loads.
- a turbine casing may surround at least a portion of the turbine section of a gas turbine system
- an exhaust casing may surround at least a portion of the exhaust section of a gas turbine system.
- the present disclosure is directed to a coupling device for coupling a first casing and a second casing together.
- the first casing and second casing include mating bore holes defined in mating flanges thereof, which may be misaligned.
- the coupling device may include a bushing insertable and positionable within one of the mating bore holes, and a pin insertable and positionable within the bushing and the other of the mating bore holes.
- the bushing and pin may each include eccentric features which may facilitate insertion into the mating bore holes when the bore holes are misaligned, thus coupling the first casing and second casing together.
- the present disclosure is directed to a turbomachine.
- the turbomachine may include a first casing and an second casing, and may further include one or more coupling devices as disclosed herein for coupling the first casing and second casing together.
- the present disclosure is directed to a method for coupling a first casing and a second casing together.
- the method may include inserting a bushing into a bore hole defined in a flange of the first casing or the second casing, rotating the bushing to align with a mating bore hole defined in a flange of the other of the first casing or the second casing, inserting a pin into the bushing, rotating the pin to align with the mating bore hole defined in a flange of the other of the first casing or the second casing, and inserting the pin into the mating bore hole.
- the bushing and pin may each include eccentric features which may facilitate insertion into the mating bore holes when the bore holes are misaligned, thus coupling the first casing and second casing together.
- FIG. 1 is a schematic view of a gas turbine system according to one embodiment of the present disclosure
- FIG. 2 is a side view of a gas turbine system according to one embodiment of the present disclosure
- FIG. 3 is a cross-sectional view of a coupling device coupling a first casing flange and an second casing flange together according to one embodiment of the present disclosure
- FIG. 4 is a bottom view of a bearing of a coupling device according to one embodiment of the present disclosure.
- FIG. 5 is a side cross-sectional view of a bearing of a coupling device according to one embodiment of the present disclosure
- FIG. 6 is a bottom view of a pin of a coupling device according to one embodiment of the present disclosure.
- FIG. 7 is a side view of a pin of a coupling device according to one embodiment of the present disclosure.
- FIG. 1 is a schematic diagram of a turbomachine, which in the embodiment shown is a gas turbine system 10 .
- the system 10 as shown may include a compressor section 12 , a combustor section 14 which may include a plurality of combustors 15 as discussed below, and a turbine section 16 .
- the compressor section 12 and turbine section 16 may be coupled by a shaft 18 .
- the shaft 18 may be a single shaft or a plurality of shaft segments coupled together to form shaft 18 .
- the shaft 18 may further be coupled to a generator or other suitable energy storage device, or may be connected directly to, for example, an electrical grid.
- An inlet section 19 may provide an air flow to the compressor section 12 , and exhaust gases may be exhausted from the turbine section 16 through an exhaust section 20 and exhausted and/or utilized in the system 10 or other suitable system. Exhaust gases from the system 10 may for example be exhausted into the atmosphere, flowed to a steam turbine or other suitable system, or recycled through a heat recovery steam generator.
- gas turbine 10 includes various casings.
- a turbine casing 32 is illustrated, which surrounds at least a portion of the turbine section 16 .
- Turbine casing 32 is generally cylindrical, and may be formed from one or more sections.
- a turbine casing 32 may include an upper casing portion and a lower casing portion. The upper casing portion may typically be uncoupled from the lower casing portion for access to the turbine section 16 , etc.
- the turbine casing 32 may be formed from one, three, four or more components.
- Turbine casing 32 may further include a flange 38 disposed at a generally downstream end (with respect to a general direction of flow through the gas turbine system 10 ).
- the flange 38 may be generally cylindrical, and may include a plurality of bore holes 40 defined therein and spaced annularly around the flange 38 .
- Each bore hole 40 may extend generally along a longitudinal axis or centerline 42 that is generally parallel to a longitudinal axis 45 of the gas turbine system 10 .
- Exhaust casing 52 is illustrated, which surrounds at least a portion of the exhaust section 20 .
- Exhaust casing 52 is generally cylindrical, and may be formed from one or more sections.
- an exhaust casing 52 may include an upper casing portion and a lower casing portion. The upper casing portion may typically be uncoupled from the lower casing portion for access to the exhaust section 20 , etc.
- the exhaust casing 52 may be formed from one, three, four or more components.
- Exhaust casing 52 may further include a flange 58 disposed at a generally upstream end (with respect to a general direction of flow through the gas turbine system 10 ).
- the flange 58 may be generally cylindrical, and may include a plurality of bore holes 60 defined therein and spaced annularly around the flange 58 .
- Each bore hole 60 may extend generally along a longitudinal axis or centerline 62 that is generally parallel to a longitudinal axis 45 of the gas turbine system 10 .
- FIG. 2 Other various casings are illustrated in FIG. 2 .
- an inlet casing 80 , compressor casing 82 , and compressor discharge casing 84 are illustrated.
- such casings may be generally cylindrical and formed from one or more sections.
- each casing 80 , 82 , 84 may include upstream and/or downstream flanges, which may abut with flanges of other casings to couple to casings together.
- a downstream flange of inlet casing 80 may abut with an upstream flange of compressor casing 82
- a downstream flange of compressor casing 82 may abut with an upstream flange of compressor discharge casing 84
- a downstream flange of compressor discharge casing 84 may abut with an upstream flange of turbine casing 32 .
- respective bore holes 40 , 60 of the turbine casing 32 and the exhaust casing 52 may mate together to couple the turbine casing 32 and exhaust casing 52 together.
- the respective flanges 38 , 58 may abutted together, with the desire that the bore holes 40 , 60 are generally aligned.
- bore holes 40 , 60 may be slightly offset, such that the bore holes 40 are not aligned.
- bore holes 40 , 60 may be misaligned such that the respective longitudinal axes 42 , 62 of the bore holes 40 , 60 are not co-axial. In these events, it may still be desirable, however, to couple the turbine casing 32 and exhaust casing 52 together.
- the present disclosure is further directed to coupling devices 100 for coupling first casings 32 and second casings 52 of turbomachines together.
- the present disclosure illustrates and describes embodiments wherein the turbine casing and exhaust casing are the first and second casings 32 , 52
- any suitable turbomachine casings which include generally vertically extending flanges and axially extending bore holes are within the scope and spirit of the present disclosure.
- a coupling device 100 extends through the mating bore holes 40 , 60 of the flanges 38 , 58 of the first casing 32 and second casing 52 when the flanges 38 , 58 are abutted together.
- a coupling device 100 may include eccentric features that facilitate extending the coupling device 100 through both mating bore holes 40 , 60 to couple the first casing 32 and second casing 52 together, even when misaligned.
- the bore holes 40 , 60 have different widths (or diameters) 70 , 72 and cross-sectional areas.
- the width 70 of bore hole 40 is larger than the width 72 of bore hole 60 .
- the width 72 of bore hole 60 may be larger than the width 70 of bore hole 40 .
- Such relative widths may, in conjunction with the eccentric features as discussed herein, facilitate coupling the flanges 38 , 58 together when misaligned.
- coupling device 100 may include a bushing 102 and a pin 104 .
- the bushing 102 may generally fit within one of the mating bore holes 40 , 60 , such as the first casing bore hole 40 as illustrated.
- Bushing 102 may thus include an outer surface 110 which, when engaged in a bore hole 40 , 60 , is proximate or in contact with an inner surface 112 of the bore hole.
- Bushing 102 may further include a bore hole 114 extending therethrough along a longitudinal axis or centerline 116 .
- the bore hole 114 may be eccentrically positioned within the bushing 102 .
- the longitudinal axis 116 of the bore hole 114 may be purposefully misaligned, and thus not co-axial with, a longitudinal axis or centerline 118 of the bushing 102 .
- the axes 116 , 118 may be generally parallel but spaced apart and not-coaxial.
- the bushing 102 can be rotated, such as about the longitudinal axis 118 , until the other mating bore hole 40 , 60 , is roughly aligned with bore hole 114 .
- the generally entire periphery of the other mating bore hole 40 , 60 is longitudinally contained in alignment within the bore hole 114 , such that pin 104 can be extended through bushing 102 and into bore hole 114 .
- Pin 104 may generally fit within bushing 102 , such as the bore hole 114 thereof, as well the other mating bore hole 40 , 60 , such as the second casing bore hole 60 as illustrated.
- pin 104 may include a first portion 130 and a second portion 132 .
- the first portion 130 may generally fit within the bushing 102 , such as within the bore hole 114 thereof, while the second portion 130 may generally extend through the bushing 102 and generally fit within the other mating bore hole 40 , 60 .
- the first portion 130 may thus include an outer surface 134 which, when engaged in the bore hole 114 of the bushing 102 , is proximate or in contact with an inner surface 136 of the bore hole 114 .
- the second portion 132 may include an outer surface 138 which, when engaged in the other mating bore hole 40 , 60 , such as the second casing bore hole 60 as illustrated, is proximate or in contact with an inner surface 140 of the other mating bore hole 40 , 60 .
- the second portion 132 may have a width and cross-sectional area that is less than a width and cross-sectional area of the first portion 130 . Further and advantageously, the second portion 132 may be eccentrically positioned relative to the first portion 130 .
- a longitudinal axis or centerline 142 of the first portion 130 may be purposefully misaligned, and thus not co-axial with, a longitudinal axis or centerline 144 of the second portion 132 .
- the axes 142 , 144 may be generally parallel but spaced apart and not-coaxial.
- the pin 104 when the pin 104 is initially being positioned within and/or relative to the bore hole 114 of the bushing 102 , the pin 104 can be rotated, such as generally about the longitudinal axis 142 , until the second portion 132 is aligned with the other mating bore hole 40 , 60 . Once aligned, the second portion 132 can be extended into the other mating bore hole 40 , 60 , with the first portion 130 thus positioned within the bore hole 114 of the bushing 102 .
- Positioning and engagement of the pin 104 within the bushing 102 may thus couple the first casing 32 and second casing 52 together.
- the pin 104 and bushing 102 may be fixedly connected to the first casing 32 and/or second casing 52 , such as to the flanges 38 , 58 thereof, once engaged in the bore holes 40 , 60 .
- the bushing 102 may be welded, brazed, bonded, affixed with an adhesive, or otherwise fixidly connected to the one of the bore holes 40 , 60 that the bushing 102 is disposed within.
- the pin 104 may be welded, brazed, bonded, affixed with an adhesive, or otherwise fixidly connected to the bushing 102 .
- Such fixed connection may further facilitate coupling of the first casing 32 and second casing 52 by the coupling device 100 .
- a method may include, for example, abutting mating flanges 38 , 58 of the first casing 32 and second casing 52 together.
- the method may further include inserting an eccentric bushing 102 into a bore hole 40 , 60 defined in one of the mating flanges 38 , 58 , and rotating the bushing 102 about a longitudinal axis 118 to align a bore hole 114 of the bushing 102 with a bore hole 40 , 60 defined in the other of the mating flanges 38 , 58 .
- the method may further include inserting an eccentric pin 104 into the bushing 102 , and rotating the pin 104 to align a portion thereof with the bore hole 40 , 60 defined in the other of the mating flanges 38 , 58 .
- the method may further include inserting the portion of the pin 104 into the other bore hole 40 , 60 .
- the pin 104 may be inserted and rotated after rotation of the bushing 102 , while in other embodiments, the pin 104 and bushing 102 may be rotated generally simultaneously.
- both the bushing 102 and pin 104 may be initially inserted. Both the bushing 102 and pin 104 may then be rotated into proper alignment. The portion of the pin 104 may then be inserted.
- a method according to the present disclosure may further include fixidly connecting the bushing 102 and the pin 104 , such as to the flange 38 and/or 58 .
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Abstract
Turbomachines, coupling devices and methods for coupling a first casing and an second casing together are provided. The first casing and second casing include mating bore holes defined in mating flanges thereof, which may be misaligned. The coupling device may include a bushing insertable and positionable within one of the mating bore holes, and a pin insertable and positionable within the bushing and the other of the mating bore holes. The bushing and pin may each include eccentric features which may facilitate insertion into the mating bore holes when the bore holes are misaligned, thus coupling the first casing and second casing together.
Description
- The present application claims filing benefit of U.S. Provisional Patent Application Ser. No. 61/878,770 having a filing date of Sep. 17, 2013, which is incorporated by reference herein in its entirety.
- The present disclosure relates generally to turbomachines, such as gas turbine systems, and more particularly to methods and apparatus for coupling mating casings, such as turbine casings and exhaust casings, of turbomachines together.
- Turbomachines are widely utilized in fields such as power generation. For example, a conventional gas turbine system includes a compressor section, a combustor section, and at least one turbine section. The compressor section is configured to compress air as the air flows through the compressor section. The air is then flowed from the compressor section to the combustor section, where it is mixed with fuel and combusted, generating a hot gas flow. The hot gas flow is provided to the turbine section, which utilizes the hot gas flow by extracting energy from it to power the compressor, an electrical generator, and other various loads.
- Various casings are typically utilized to encase and protect the various components of a turbomachine such as a gas turbine system. For example, a turbine casing may surround at least a portion of the turbine section of a gas turbine system, and an exhaust casing may surround at least a portion of the exhaust section of a gas turbine system. These casings are typically coupled together through the use of bolts which are extended through mating flanges of the casings.
- However, the use of typically known coupling apparatus can present various disadvantages when coupling such sections together. For example, in some cases, it can be discovered during initial assembly of the turbine casing and exhaust casing, or other mating casings, that the respective alignment bore holes (which could be original bolt holes or additional aligment holes) defined in the respective flanges do not align. Such misalignment may also occur after initial assembly during reassembly after, for example, routine maintenance, repair or replacement activities.
- Currently, when such misalignment occurs, new aligning bore holes must be drilled into the flanges for the bolts to be extended through. Such practice, however, is time-consuming and can weaken the respective flanges.
- Accordingly, improved methods and apparatus for coupling mating casings of a turbomachine are desired in the art. In particular, methods and apparatus that can compensate for misalignments between the respective casings would be advantageous.
- Aspects and advantages of the invention will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the invention.
- In one embodiment, the present disclosure is directed to a coupling device for coupling a first casing and a second casing together. The first casing and second casing include mating bore holes defined in mating flanges thereof, which may be misaligned. The coupling device may include a bushing insertable and positionable within one of the mating bore holes, and a pin insertable and positionable within the bushing and the other of the mating bore holes. The bushing and pin may each include eccentric features which may facilitate insertion into the mating bore holes when the bore holes are misaligned, thus coupling the first casing and second casing together.
- In another embodiment, the present disclosure is directed to a turbomachine. The turbomachine may include a first casing and an second casing, and may further include one or more coupling devices as disclosed herein for coupling the first casing and second casing together.
- In another embodiment, the present disclosure is directed to a method for coupling a first casing and a second casing together. The method may include inserting a bushing into a bore hole defined in a flange of the first casing or the second casing, rotating the bushing to align with a mating bore hole defined in a flange of the other of the first casing or the second casing, inserting a pin into the bushing, rotating the pin to align with the mating bore hole defined in a flange of the other of the first casing or the second casing, and inserting the pin into the mating bore hole. The bushing and pin may each include eccentric features which may facilitate insertion into the mating bore holes when the bore holes are misaligned, thus coupling the first casing and second casing together.
- These and other features, aspects and advantages of the present invention will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention.
- A full and enabling disclosure of the present invention, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which:
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FIG. 1 is a schematic view of a gas turbine system according to one embodiment of the present disclosure; -
FIG. 2 is a side view of a gas turbine system according to one embodiment of the present disclosure; -
FIG. 3 is a cross-sectional view of a coupling device coupling a first casing flange and an second casing flange together according to one embodiment of the present disclosure; -
FIG. 4 is a bottom view of a bearing of a coupling device according to one embodiment of the present disclosure; and -
FIG. 5 is a side cross-sectional view of a bearing of a coupling device according to one embodiment of the present disclosure; -
FIG. 6 is a bottom view of a pin of a coupling device according to one embodiment of the present disclosure; and -
FIG. 7 is a side view of a pin of a coupling device according to one embodiment of the present disclosure. - Reference now will be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For instance, features illustrated or described as part of one embodiment can be used with another embodiment to yield a still further embodiment. Thus, it is intended that the present invention covers such modifications and variations as come within the scope of the appended claims and their equivalents.
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FIG. 1 is a schematic diagram of a turbomachine, which in the embodiment shown is agas turbine system 10. It should be understood that the turbomachine of the present disclosure need not be agas turbine system 10, but rather may be any suitable turbine system or other turbomachine, such as a steam turbine system or other suitable system. Thesystem 10 as shown may include acompressor section 12, acombustor section 14 which may include a plurality of combustors 15 as discussed below, and aturbine section 16. Thecompressor section 12 andturbine section 16 may be coupled by ashaft 18. Theshaft 18 may be a single shaft or a plurality of shaft segments coupled together to formshaft 18. Theshaft 18 may further be coupled to a generator or other suitable energy storage device, or may be connected directly to, for example, an electrical grid. Aninlet section 19 may provide an air flow to thecompressor section 12, and exhaust gases may be exhausted from theturbine section 16 through anexhaust section 20 and exhausted and/or utilized in thesystem 10 or other suitable system. Exhaust gases from thesystem 10 may for example be exhausted into the atmosphere, flowed to a steam turbine or other suitable system, or recycled through a heat recovery steam generator. - Referring now to
FIG. 2 , a side view of agas turbine system 10 is illustrated. Thegas turbine 10 system as shown is mounted to a base. As illustrated,gas turbine 10 includes various casings. For example, a turbine casing 32 is illustrated, which surrounds at least a portion of theturbine section 16. Turbine casing 32 is generally cylindrical, and may be formed from one or more sections. For example, in exemplary embodiments, a turbine casing 32 may include an upper casing portion and a lower casing portion. The upper casing portion may typically be uncoupled from the lower casing portion for access to theturbine section 16, etc. Alternatively, the turbine casing 32 may be formed from one, three, four or more components. Turbine casing 32 may further include aflange 38 disposed at a generally downstream end (with respect to a general direction of flow through the gas turbine system 10). Theflange 38 may be generally cylindrical, and may include a plurality of bore holes 40 defined therein and spaced annularly around theflange 38. Eachbore hole 40 may extend generally along a longitudinal axis orcenterline 42 that is generally parallel to alongitudinal axis 45 of thegas turbine system 10. - Further, an exhaust casing 52 is illustrated, which surrounds at least a portion of the
exhaust section 20. Exhaust casing 52 is generally cylindrical, and may be formed from one or more sections. For example, in exemplary embodiments, an exhaust casing 52 may include an upper casing portion and a lower casing portion. The upper casing portion may typically be uncoupled from the lower casing portion for access to theexhaust section 20, etc. Alternatively, the exhaust casing 52 may be formed from one, three, four or more components. Exhaust casing 52 may further include aflange 58 disposed at a generally upstream end (with respect to a general direction of flow through the gas turbine system 10). Theflange 58 may be generally cylindrical, and may include a plurality of bore holes 60 defined therein and spaced annularly around theflange 58. Eachbore hole 60 may extend generally along a longitudinal axis orcenterline 62 that is generally parallel to alongitudinal axis 45 of thegas turbine system 10. - Other various casings are illustrated in
FIG. 2 . For example, aninlet casing 80,compressor casing 82, andcompressor discharge casing 84 are illustrated. Similarly to the turbine casing 32 and exhaust casing 52, such casings may be generally cylindrical and formed from one or more sections. Further, eachcasing inlet casing 80 may abut with an upstream flange ofcompressor casing 82, a downstream flange ofcompressor casing 82 may abut with an upstream flange ofcompressor discharge casing 84, and a downstream flange ofcompressor discharge casing 84 may abut with an upstream flange of turbine casing 32. - As further illustrated in
FIGS. 2 and 3 , respective bore holes 40, 60 of the turbine casing 32 and the exhaust casing 52 may mate together to couple the turbine casing 32 and exhaust casing 52 together. For example, therespective flanges flanges holes FIG. 3 , bore holes 40, 60 may be misaligned such that the respectivelongitudinal axes - Accordingly, and referring now to
FIGS. 3-7 , the present disclosure is further directed tocoupling devices 100 for coupling first casings 32 and second casings 52 of turbomachines together. It should be understood that, while the present disclosure illustrates and describes embodiments wherein the turbine casing and exhaust casing are the first and second casings 32, 52, any suitable turbomachine casings which include generally vertically extending flanges and axially extending bore holes are within the scope and spirit of the present disclosure. As shown inFIG. 3 , acoupling device 100 extends through the mating bore holes 40, 60 of theflanges flanges longitudinal axes coupling device 100 according to the present disclosure may include eccentric features that facilitate extending thecoupling device 100 through both mating bore holes 40, 60 to couple the first casing 32 and second casing 52 together, even when misaligned. - It should be noted that in exemplary embodiments, the bore holes 40, 60 have different widths (or diameters) 70, 72 and cross-sectional areas. For example, as shown, the
width 70 ofbore hole 40 is larger than thewidth 72 ofbore hole 60. Alternatively, thewidth 72 ofbore hole 60 may be larger than thewidth 70 ofbore hole 40. Such relative widths may, in conjunction with the eccentric features as discussed herein, facilitate coupling theflanges - As shown in
FIGS. 3-7 ,coupling device 100 may include abushing 102 and apin 104. Thebushing 102 may generally fit within one of the mating bore holes 40, 60, such as the first casing borehole 40 as illustrated. Bushing 102 may thus include anouter surface 110 which, when engaged in abore hole inner surface 112 of the bore hole. Bushing 102 may further include abore hole 114 extending therethrough along a longitudinal axis orcenterline 116. Advantageously, thebore hole 114 may be eccentrically positioned within thebushing 102. For example, as shown, thelongitudinal axis 116 of thebore hole 114 may be purposefully misaligned, and thus not co-axial with, a longitudinal axis orcenterline 118 of thebushing 102. As shown, theaxes bushing 102 is initially positioned within thebore hole bushing 102 can be rotated, such as about thelongitudinal axis 118, until the other mating borehole bore hole 114. In this rough alignment, as illustrated inFIG. 3 , the generally entire periphery of the other mating borehole bore hole 114, such thatpin 104 can be extended throughbushing 102 and intobore hole 114. -
Pin 104 may generally fit withinbushing 102, such as thebore hole 114 thereof, as well the other mating borehole hole 60 as illustrated. For example, pin 104 may include afirst portion 130 and asecond portion 132. Thefirst portion 130 may generally fit within thebushing 102, such as within thebore hole 114 thereof, while thesecond portion 130 may generally extend through thebushing 102 and generally fit within the other mating borehole first portion 130 may thus include anouter surface 134 which, when engaged in thebore hole 114 of thebushing 102, is proximate or in contact with aninner surface 136 of thebore hole 114. Thesecond portion 132 may include anouter surface 138 which, when engaged in the other mating borehole hole 60 as illustrated, is proximate or in contact with aninner surface 140 of the other mating borehole - Accordingly, in exemplary embodiments as illustrated, the
second portion 132 may have a width and cross-sectional area that is less than a width and cross-sectional area of thefirst portion 130. Further and advantageously, thesecond portion 132 may be eccentrically positioned relative to thefirst portion 130. For example, as shown, a longitudinal axis orcenterline 142 of thefirst portion 130 may be purposefully misaligned, and thus not co-axial with, a longitudinal axis orcenterline 144 of thesecond portion 132. As shown, theaxes pin 104 is initially being positioned within and/or relative to thebore hole 114 of thebushing 102, thepin 104 can be rotated, such as generally about thelongitudinal axis 142, until thesecond portion 132 is aligned with the other mating borehole second portion 132 can be extended into the other mating borehole first portion 130 thus positioned within thebore hole 114 of thebushing 102. - Positioning and engagement of the
pin 104 within thebushing 102 may thus couple the first casing 32 and second casing 52 together. Further, in some exemplary embodiments, thepin 104 andbushing 102 may be fixedly connected to the first casing 32 and/or second casing 52, such as to theflanges bushing 102 may be welded, brazed, bonded, affixed with an adhesive, or otherwise fixidly connected to the one of the bore holes 40, 60 that thebushing 102 is disposed within. Thepin 104 may be welded, brazed, bonded, affixed with an adhesive, or otherwise fixidly connected to thebushing 102. Such fixed connection may further facilitate coupling of the first casing 32 and second casing 52 by thecoupling device 100. - The present disclosure is further directed to method for coupling first casings 32 and second casings 52 together. A method may include, for example, abutting
mating flanges eccentric bushing 102 into abore hole mating flanges bushing 102 about alongitudinal axis 118 to align abore hole 114 of thebushing 102 with abore hole mating flanges eccentric pin 104 into thebushing 102, and rotating thepin 104 to align a portion thereof with thebore hole mating flanges pin 104 into theother bore hole pin 104 may be inserted and rotated after rotation of thebushing 102, while in other embodiments, thepin 104 andbushing 102 may be rotated generally simultaneously. For example, in some embodiments, both thebushing 102 and pin 104 may be initially inserted. Both thebushing 102 and pin 104 may then be rotated into proper alignment. The portion of thepin 104 may then be inserted. - In some embodiments, a method according to the present disclosure may further include fixidly connecting the
bushing 102 and thepin 104, such as to theflange 38 and/or 58. - 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 include 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 (20)
1. A coupling device for coupling a first casing and a second casing of a gas turbine system together, the first casing comprising a first flange that defines a first flange bore hole and the second casing comprising a second flange that defines a second flange bore hole, the first flange and the second flange abutted together, the coupling device comprising:
a bushing insertable and positionable within one of the first flange bore hole and the second flange bore hole; and
a pin insertable and positionable within the bushing and the other of the first flange bore hole and the second flange bore hole,
wherein the bushing and the pin each comprise an eccentric feature.
2. The coupling device of claim 1 , wherein the bushing comprises an outer surface sized to contact an inner surface of the one of the first flange bore hole and the second flange bore hole when the bushing is inserted in the one of the first flange bore hole and the second flange bore hole.
3. The coupling device of claim 1 , wherein the bushing defines a bushing bore hole.
4. The coupling device of claim 3 , wherein a longitudinal axis of the bushing bore hole is offset from a longitudinal axis of the bushing.
5. The coupling device of claim 3 , wherein the pin comprises a first portion and a second portion, the second portion having a width that is less than a width of the first portion.
6. The coupling device of claim 5 , wherein the first portion comprises an outer surface sized to contact an inner surface of the bushing bore hole when the first portion is inserted in the bushing bore hole, and wherein the second portion comprises an outer surface sized to contact an inner surface of the other of the first flange bore hole and the second flange bore hole when the second portion is inserted in the other of the first flange bore hole and the second flange bore hole.
7. The coupling device of claim 5 , wherein a longitudinal axis of the second portion is offset from a longitudinal axis of the first portion.
8. A turbomachine, the turbomachine comprising:
a first casing, the first casing comprising a first flange that defines a first flange bore hole;
a second casing, the second casing comprising a second flange that defines a second flange bore hole, wherein the first flange and the second flange are abutted together; and
a coupling device coupling the first casing and the second casing together, the coupling device comprising:
a bushing positioned within one of the first flange bore hole and the second flange bore hole; and
a pin positioned within the bushing and the other of the first flange bore hole and the second flange bore hole,
wherein the bushing and the pin each comprise an eccentric feature.
9. The turbomachine of claim 8 , wherein the bushing comprises an outer surface contacting an inner surface of the one of the first flange bore hole and the second flange bore hole.
10. The turbomachine of claim 8 , wherein the bushing defines a bushing bore hole.
11. The turbomachine of claim 10 , wherein a longitudinal axis of the bushing bore hole is offset from a longitudinal axis of the bushing.
12. The turbomachine of claim 10 , wherein the pin comprises a first portion and a second portion, the second portion having a width that is less than a width of the first portion.
13. The turbomachine of claim 12 , wherein the first portion is positioned within the bushing and the second portion is positioned within the other of the first flange bore hole and the second flange bore hole.
14. The turbomachine of claim 13 , wherein the first portion comprises an outer surface contacting an inner surface of the bushing bore hole, and wherein the second portion comprises an outer surface contacting an inner surface of the other of the first flange bore hole and the second flange bore hole.
15. The turbomachine of claim 12 , wherein a longitudinal axis of the second portion is offset from a longitudinal axis of the first portion.
16. The turbomachine of claim 8 , wherein the bushing is fixedly connected to the one of the first flange bore hole and the second flange bore hole, and wherein the pin is fixedly connected to the bushing and the other of the first flange bore hole and the second flange bore hole.
17. The turbomachine of claim 8 , wherein the first casing is a turbine casing and the second casing is an exhaust casing.
18. The turbomachine of claim 8 , wherein a longitudinal axis of the first flange bore hole is offset from the longitudinal axis of the second flange bore hole.
19. A method for coupling a first casing and a second casing of a gas turbine system together, the method comprising:
inserting a bushing into a bore hole defined in a flange of the first casing or the second casing;
rotating the bushing to align with a mating bore hole defined in a flange of the other of the first casing or the second casing;
inserting a pin into the bushing;
rotating the pin to align with the mating bore hole defined in the flange of the other of the first casing or the second casing; and
inserting the pin into the mating bore hole,
wherein the bushing and the pin each comprise an eccentric feature.
20. The method of claim 19 , wherein a longitudinal axis of the bore hole defined in the flange of the first casing is offset from a longitudinal axis of the bore hole defined in the flange of the second casing.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/488,661 US20150078892A1 (en) | 2013-09-17 | 2014-09-17 | Eccentric coupling device and method for coupling mating casings in a turbomachine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201361878770P | 2013-09-17 | 2013-09-17 | |
US14/488,661 US20150078892A1 (en) | 2013-09-17 | 2014-09-17 | Eccentric coupling device and method for coupling mating casings in a turbomachine |
Publications (1)
Publication Number | Publication Date |
---|---|
US20150078892A1 true US20150078892A1 (en) | 2015-03-19 |
Family
ID=51656099
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/488,661 Abandoned US20150078892A1 (en) | 2013-09-17 | 2014-09-17 | Eccentric coupling device and method for coupling mating casings in a turbomachine |
Country Status (6)
Country | Link |
---|---|
US (1) | US20150078892A1 (en) |
EP (1) | EP3047120A1 (en) |
JP (1) | JP2016531243A (en) |
KR (1) | KR20160055260A (en) |
CN (1) | CN105765175A (en) |
WO (1) | WO2015042095A1 (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102015114401A1 (en) * | 2015-08-28 | 2017-03-02 | Wittenstein Se | Mounting system for a machine element |
FR3042724A1 (en) * | 2015-10-27 | 2017-04-28 | Snecma | MEANS OF CONNECTION BETWEEN TWO MECHANICAL PARTS |
FR3094745A1 (en) * | 2019-04-02 | 2020-10-09 | Safran Aircraft Engines | Method of centering annular flange holes |
US10934892B2 (en) * | 2016-08-16 | 2021-03-02 | General Electric Technology Gmbh | Axial flow turbine having a diaphragm split in two halves at a horizontal joint plane |
US11440172B2 (en) | 2017-01-25 | 2022-09-13 | Vestas Wind Systems A/S | Alignment tool for aligning bores in structural members |
US11635002B2 (en) * | 2017-02-24 | 2023-04-25 | Mitsubishi Heavy Industries Compressor Corporation | Steam turbine, center guide pin, and method for manufacturing steam turbine |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR20180078080A (en) * | 2016-12-29 | 2018-07-09 | 한국항공우주연구원 | Fixed body position correcting apparatus considering eccentricity of rotor |
DE102022122109A1 (en) | 2022-09-01 | 2024-03-07 | Bayerische Motoren Werke Aktiengesellschaft | Housing for aligning a first component feature to a second component feature for a motor vehicle, component arrangement, motor vehicle |
Citations (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1097185A (en) * | 1913-04-22 | 1914-05-19 | Henry C Oehrle | Coupling-bolt. |
US3062497A (en) * | 1958-11-24 | 1962-11-06 | Ford Motor Co | Gas turbine engine |
US3072423A (en) * | 1961-11-06 | 1963-01-08 | Northrop Corp | Adjustable support pin |
US3493249A (en) * | 1968-01-18 | 1970-02-03 | Westinghouse Electric Corp | Eccentric bushings for housings |
US4320984A (en) * | 1979-08-25 | 1982-03-23 | Robert Bosch Gmbh | Arrangement for connecting two structural parts |
US4650396A (en) * | 1984-01-09 | 1987-03-17 | Bbc Brown, Boveri & Company, Limited | Externally adjustable axial location for a vane carrier in a turbine |
US4789287A (en) * | 1985-07-18 | 1988-12-06 | Nixdorf Computer Ag | Through bolt connection for unilaterally accessible locations |
US5104286A (en) * | 1991-02-08 | 1992-04-14 | Westinghouse Electric Corp. | Recirculation seal for a gas turbine exhaust diffuser |
US5438756A (en) * | 1993-12-17 | 1995-08-08 | General Electric Company | Method for assembling a turbine frame assembly |
US5513547A (en) * | 1995-01-06 | 1996-05-07 | Westinghouse Electric Corporation | Combustion turbine alignment method and apparatus |
DE10236097A1 (en) * | 2002-08-02 | 2004-02-19 | Becher, Reinhard | Dowel for inserting into bores in two components to join them together is made up of two sections which are offset from each other to compensate for misalignment of bores |
US20100126013A1 (en) * | 2007-04-02 | 2010-05-27 | Ansaldo Energia S.P.A. | Maintenance method of a gas turbine unit and gas turbine unit |
WO2014010287A1 (en) * | 2012-07-11 | 2014-01-16 | 三菱重工業株式会社 | Axial flow exhaust turbine |
US8870533B2 (en) * | 2011-07-13 | 2014-10-28 | General Electric Company | Assembly for aligning an inner shell of a turbine casing |
EP2960530A1 (en) * | 2014-06-27 | 2015-12-30 | Siemens Aktiengesellschaft | Assembly method for an electric machine comprising at least two machine segments |
US20160341069A1 (en) * | 2014-01-27 | 2016-11-24 | Mitsubishi Hitachi Power Systems, Ltd. | Position adjustment device, rotating machine provided with same, and position adjustment method |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1120216B (en) * | 1958-11-24 | 1961-12-21 | Ford Werke Ag | Gas turbine |
US5848874A (en) * | 1997-05-13 | 1998-12-15 | United Technologies Corporation | Gas turbine stator vane assembly |
-
2014
- 2014-09-17 US US14/488,661 patent/US20150078892A1/en not_active Abandoned
- 2014-09-17 WO PCT/US2014/055991 patent/WO2015042095A1/en active Application Filing
- 2014-09-17 EP EP14778004.3A patent/EP3047120A1/en not_active Withdrawn
- 2014-09-17 JP JP2016542882A patent/JP2016531243A/en active Pending
- 2014-09-17 KR KR1020167009676A patent/KR20160055260A/en not_active Application Discontinuation
- 2014-09-17 CN CN201480051293.4A patent/CN105765175A/en active Pending
Patent Citations (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1097185A (en) * | 1913-04-22 | 1914-05-19 | Henry C Oehrle | Coupling-bolt. |
US3062497A (en) * | 1958-11-24 | 1962-11-06 | Ford Motor Co | Gas turbine engine |
US3072423A (en) * | 1961-11-06 | 1963-01-08 | Northrop Corp | Adjustable support pin |
US3493249A (en) * | 1968-01-18 | 1970-02-03 | Westinghouse Electric Corp | Eccentric bushings for housings |
US4320984A (en) * | 1979-08-25 | 1982-03-23 | Robert Bosch Gmbh | Arrangement for connecting two structural parts |
US4650396A (en) * | 1984-01-09 | 1987-03-17 | Bbc Brown, Boveri & Company, Limited | Externally adjustable axial location for a vane carrier in a turbine |
US4789287A (en) * | 1985-07-18 | 1988-12-06 | Nixdorf Computer Ag | Through bolt connection for unilaterally accessible locations |
US5104286A (en) * | 1991-02-08 | 1992-04-14 | Westinghouse Electric Corp. | Recirculation seal for a gas turbine exhaust diffuser |
US5438756A (en) * | 1993-12-17 | 1995-08-08 | General Electric Company | Method for assembling a turbine frame assembly |
US5513547A (en) * | 1995-01-06 | 1996-05-07 | Westinghouse Electric Corporation | Combustion turbine alignment method and apparatus |
DE10236097A1 (en) * | 2002-08-02 | 2004-02-19 | Becher, Reinhard | Dowel for inserting into bores in two components to join them together is made up of two sections which are offset from each other to compensate for misalignment of bores |
US20100126013A1 (en) * | 2007-04-02 | 2010-05-27 | Ansaldo Energia S.P.A. | Maintenance method of a gas turbine unit and gas turbine unit |
US8443514B2 (en) * | 2007-04-02 | 2013-05-21 | Ansaldo Energia S.P.A. | Maintenance method of a gas turbine unit and gas turbine unit |
US8870533B2 (en) * | 2011-07-13 | 2014-10-28 | General Electric Company | Assembly for aligning an inner shell of a turbine casing |
WO2014010287A1 (en) * | 2012-07-11 | 2014-01-16 | 三菱重工業株式会社 | Axial flow exhaust turbine |
US20160341069A1 (en) * | 2014-01-27 | 2016-11-24 | Mitsubishi Hitachi Power Systems, Ltd. | Position adjustment device, rotating machine provided with same, and position adjustment method |
EP2960530A1 (en) * | 2014-06-27 | 2015-12-30 | Siemens Aktiengesellschaft | Assembly method for an electric machine comprising at least two machine segments |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102015114401A1 (en) * | 2015-08-28 | 2017-03-02 | Wittenstein Se | Mounting system for a machine element |
US10428854B2 (en) | 2015-08-28 | 2019-10-01 | Wittenstein Se | Fastening system for a machine element |
FR3042724A1 (en) * | 2015-10-27 | 2017-04-28 | Snecma | MEANS OF CONNECTION BETWEEN TWO MECHANICAL PARTS |
US10934892B2 (en) * | 2016-08-16 | 2021-03-02 | General Electric Technology Gmbh | Axial flow turbine having a diaphragm split in two halves at a horizontal joint plane |
US11440172B2 (en) | 2017-01-25 | 2022-09-13 | Vestas Wind Systems A/S | Alignment tool for aligning bores in structural members |
US11635002B2 (en) * | 2017-02-24 | 2023-04-25 | Mitsubishi Heavy Industries Compressor Corporation | Steam turbine, center guide pin, and method for manufacturing steam turbine |
FR3094745A1 (en) * | 2019-04-02 | 2020-10-09 | Safran Aircraft Engines | Method of centering annular flange holes |
Also Published As
Publication number | Publication date |
---|---|
EP3047120A1 (en) | 2016-07-27 |
WO2015042095A1 (en) | 2015-03-26 |
KR20160055260A (en) | 2016-05-17 |
JP2016531243A (en) | 2016-10-06 |
CN105765175A (en) | 2016-07-13 |
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