US20120186260A1 - Transition piece impingement sleeve for a gas turbine - Google Patents
Transition piece impingement sleeve for a gas turbine Download PDFInfo
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- US20120186260A1 US20120186260A1 US13/012,838 US201113012838A US2012186260A1 US 20120186260 A1 US20120186260 A1 US 20120186260A1 US 201113012838 A US201113012838 A US 201113012838A US 2012186260 A1 US2012186260 A1 US 2012186260A1
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- Prior art keywords
- casing
- impingement sleeve
- flange
- shoulder
- joint
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
Definitions
- the present subject matter relates generally to gas turbines and, more particularly, to an impingement sleeve for a transition piece of a gas turbine combustor.
- Gas turbines typically include a compressor section, a combustion section, and a turbine section.
- the compressor section pressurizes air flowing into the turbine.
- the pressurized air discharged from the compressor section flows into the combustion section, which may be characterized by a plurality of combustors disposed around an annular array about the axis of the engine.
- Each of the plurality of combustors includes a combustion liner, which defines the combustion chamber of the combustor.
- air entering each combustor is mixed with fuel and combusted within the combustion liner. Hot gases of combustion flow from the combustion liner through a transition piece to the turbine section of the gas turbine to drive the turbine and generate power.
- the transition piece of a gas turbine may be configured as a double walled component.
- the transition piece may include an impingement sleeve and an inner duct disposed radially inwardly from the impingement sleeve.
- the inner duct is generally configured to transport the flow of hot gases from the combustion chamber to a first stage nozzle of the turbine section.
- the impingement sleeve is generally configured to provide impingement cooling for the inner duct.
- the impingement sleeve may define a plurality cooling holes configured to receive the pressurized air discharged from the compressor section.
- the impingement sleeve be formed from two or more sections configured to be assembled around the inner duct.
- the sections of the impingement sleeve are welded to one another.
- the process of welding the impingement sleeve sections together is often a difficult task.
- the disassembly of the impingement sleeve in the field in order to perform inspections and/or repairs can be quite challenging and very time consuming.
- the present subject matter discloses an impingement sleeve for a transition piece of a gas turbine.
- the impingement sleeve generally includes a first casing configured to surround a portion of an inner duct of the transition piece and a second casing configured to surround a portion of the inner duct.
- the impingement sleeve may include a substantially flat joint defined between the first and second casings.
- the substantially flat joint may include a plurality of fasteners configured to attach the first casing to the second casing.
- the present subject matter discloses an impingement sleeve for a transition piece of a gas turbine.
- the impingement sleeve generally includes a first casing configured to surround a portion of an inner duct of the transition piece and a second casing configured to surround a portion of the inner duct.
- the impingement sleeve may include a joint defined between the first and second casings.
- the joint may include a plurality of fasteners configured to attach the first casing to the second casing.
- at least one channel may be mounted to an inner surface of at least one of the first casing and the second casing.
- the channel may generally include a plurality of threaded nuts secured thereto.
- FIG. 1 illustrates a schematic depiction of a gas turbine
- FIG. 2 illustrates a cross-sectional, side view of a combustor of a gas turbine
- FIG. 3 illustrates a perspective view of one embodiment of an impingement sleeve in accordance with aspects of the present subject matter
- FIG. 4 illustrates an exploded view of one embodiment of a double walled transition piece in accordance with aspects of the present subject matter
- FIG. 5 illustrates a cross-sectional, side view of the double walled transition piece shown in FIG. 4 ;
- FIG. 6 illustrates a partial, cross-sectional view of one embodiment of an attachment joint for attaching components of an impingement sleeve together in accordance with aspects of the present subject matter.
- FIG. 1 illustrates a schematic depiction of a gas turbine 10 .
- the gas turbine 10 includes a compressor section 12 , a combustion section 14 , and a turbine section 16 .
- the combustion section 14 may include a plurality of combustors 20 (one of which is illustrated in FIG. 2 ) disposed around an annular array about the axis of the gas turbine 10 .
- 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 the shaft 18 .
- the compressor section 12 supplies compressed air to the combustion section 14 .
- the compressed air is mixed with fuel and burned within each combustor 20 ( FIG. 2 ) and hot gases of combustion flow from the combustion section 14 to the turbine section 16 , wherein energy is extracted from the hot gases to produce work.
- the combustor 20 may generally include a substantially cylindrical combustion casing 22 secured to a portion of a gas turbine casing 24 , such as a compressor discharge casing or a combustion wrapper casing.
- a flange 26 may generally extend outwardly from an upstream end of the combustion casing 22 .
- the flange 26 may be configured such that an end cover assembly (not illustrated) may be secured to the combustion casing 22 .
- the end cover assembly may include a plurality of fuel nozzles (not shown).
- the combustor 20 may also include an internal flow sleeve 28 and a combustion liner 30 substantially concentrically arranged within the flow sleeve 28 .
- the combustion liner 30 may generally define a substantially cylindrical combustion chamber 32 , wherein fuel and air are injected and combusted to produce hot gases of combustion. Additionally, both the flow sleeve 28 and the combustion liner 30 may extend, at their downstream ends, to a double walled transition piece 34 , including an impingement sleeve 36 and an inner duct 38 disposed radially inwardly from the impingement sleeve 36 .
- the combustion liner 30 may be coupled at its downstream end to the inner duct 38 such that the combustion liner 30 and the inner duct 38 generally define a flowpath for the hot gases of combustion flowing from each combustor 20 to the turbine section 16 of the gas turbine 10 ( FIG. 1 ).
- the flow sleeve 28 may be coupled at its downstream end to the impingement sleeve 36 such that the flow sleeve 28 and the impingement sleeve 36 generally define a flowpath for the pressurized air discharged from the compressor section 12 of the gas turbine 10 ( FIG. 1 ).
- the impingement sleeve 36 may define a plurality of cooling holes 40 configured to permit the pressurized air to enter the radial space defined between the inner duct 38 and the impingement sleeve 36 .
- one or both of the downstream ends of impingement sleeve 36 and the inner duct 38 may be coupled to a transition piece aft frame 42 .
- the aft frame 42 may be configured to attach the transition piece 34 to a first stage nozzle (not shown) of the turbine section 16 ( FIG. 1 ) such that the hot gases of combustion flowing through the inner duct 38 may be directed into the turbine section 16 .
- FIGS. 3-6 one embodiment of a double walled transition piece 100 and, particularly, one embodiment of an impingement sleeve 102 suitable for use with the transition piece 100 is illustrated in accordance with aspects of the present subject matter.
- FIG. 3 illustrates a perspective view of the impingement sleeve 102 .
- FIGS. 4 and 5 illustrate exploded and cross-sectional views, respectively, of the transition piece 100 , particularly illustrating various components and/or features of the impingement sleeve 102 .
- FIG. 6 illustrates a partial, cross-sectional view of the attachment features of the casing components 106 , 108 of the disclosed impingement sleeve 102 .
- the disclosed impingement sleeve 102 may generally be configured to be positioned radially outwardly from the inner duct 104 of the transition piece 100 .
- the impingement sleeve 102 may be disposed relative to the inner duct 104 such that a radial space or gap 110 is defined between the impingement sleeve 102 and the inner duct 104 .
- the pressurized air discharged from the compressor section 12 of the gas turbine 10 ( FIG. 1 ) may be directed through the radial gap 110 to provide cooling for the inner duct 104 .
- a plurality of cooling holes 112 may be defined through the impingement sleeve 102 such that the pressurized air flowing along its outer perimeter may be directed through the impingement sleeve 102 and may impinge onto the outer surface 114 of the inner duct 104 .
- the downstream ends 116 of the impingement sleeve 102 and/or the inner duct 104 may be configured to be coupled to a downstream component of the gas turbine 10 , such an aft frame 42 of the combustor 20 ( FIG. 2 ).
- the impingement sleeve 102 includes a first casing component 106 and a second casing component 108 .
- the first and second casing components 106 , 108 may generally define a shape or profile corresponding to the shape or profile of the portion of the inner duct 104 around which the casing components 106 , 108 are configured to be disposed (e.g., the first and second side portions 118 , 120 of the inner duct 104 ).
- the shape or profile of the first and second casing components 106 , 108 may also be varied from the shape or profile of the inner duct 104 to take into account effective cooling configurations and the available packaging within the gas turbine 10 .
- first and second casing components 106 , 108 may be configured to be attached to another such that, once assembled, the casing components 106 , 108 generally encase the inner duct 104 .
- an attachment joint 140 may generally be formed at the interfaces of the first and second casing components 106 , 108 , such as between the top ends 126 of the casing components 106 , 108 and between the bottom ends 128 of the casing components 126 , 128 .
- the casing components 106 , 108 may generally have any suitable configuration designed to form any suitable joint known in the art.
- the casing components 106 , 108 may be configured to overlap one another such that the attachment joints 140 defined between the casing components 106 , 108 are configured as lap joints.
- the first casing component 106 may include a first mounting flange 122 disposed at a top end 126 of the casing component 106 and a second mounting flange 124 disposed at a bottom end 128 of the casing component 106 .
- the second casing component 108 may include a first mounting shoulder 130 disposed at a top end 126 of the casing component 108 and a second mounting shoulder 132 disposed at a bottom end 128 of the casing component 108 .
- the flanges 122 , 124 and shoulders 130 , 132 of the casing components 106 , 108 may generally be configured such that, when the first and second casing components 106 , 108 are assembled around the inner duct 104 , the first shoulder 130 is aligned with and overlaps the first flange 122 and the second shoulder 132 is aligned with and overlaps the second flange 124 so as to define the attachment joints 140 .
- the flanges 122 , 124 and shoulders 130 , 132 may then be attached to one another such that the first and second casing components 106 , 108 generally form an encasing configuration about the inner duct 104 .
- the second casing component 108 may include a slight bend at the attachment joints 140 having a height generally equal to the width 143 ( FIG. 6 ) of the flanges 122 , 124 to permit the shoulders 130 , 132 to be aligned with and overlap the flanges 122 , 124 .
- the second casing component 108 may include a radially outwardly extending bend 142 at the base of each shoulder 130 , 132 such that the flanges 122 , 124 may be disposed radially inwardly from the shoulders 130 , 132 .
- the second casing component 108 may include a radially inwardly extending bend 142 at the base of each shoulder 130 , 132 such that the flanges 122 , 124 may be disposed radially outwardly from the shoulders 130 , 132 .
- the second casing component 108 need not define a bend 142 .
- the second casing component 108 may simply define a radius of curvature or may otherwise have a radial dimension which is slightly larger or slight smaller than the radius of curvature or radial dimension of the first casing component 106 such that the flanges 122 , 124 and shoulders 130 , 132 overlap one another when the casing components 106 , 108 are positioned together.
- the attachment joints 140 may generally be configured as substantially flat joints.
- substantially flat it is meant that the shape or profile of the portions of the casing components 106 , 108 forming the attachment joints 140 may generally correspond to the overall shape or profile of the impingement sleeve 102 in an area generally adjacent to the joints 140 .
- the flanges 122 , 124 and the shoulders 130 , 132 may generally be configured to form an extension of the shape or profile of the first and second casing components 106 , 108 , respectively, at each attachment joint 140 .
- the first and second flanges 122 , 124 may generally define a straight or curved profile extending substantially tangentially and/or parallel to the profile of the first casing component 106 in an area adjacent to the attachment joint 140 (e.g., the profile defined at the top and bottom ends 126 , 128 of the first casing component 106 ).
- the first and second shoulders 130 , 132 may generally define a straight or curved profile extending substantially tangentially and/or parallel to the profile of the second casing component 108 in an area adjacent to the attachment joints 140 (e.g., the profile defined at the top and bottom ends 126 , 128 of the second casing component 108 ).
- the flanges 122 , 124 and shoulders 130 , 132 when attached, may be configured to extend substantially parallel to one another.
- the attachment joints 140 when the first and second casing components 106 , 108 are positioned in an encasing configuration around the inner duct 104 , the attachment joints 140 may generally have a substantially flat configuration with respect to the overall shape or profile of the impingement sleeve 102 .
- the corresponding profiles of the flanges 122 , 124 and shoulders 130 , 132 may generally vary depending on the location at which the attachment joints 140 are defined along the outer perimeter of the impingement sleeve 102 .
- the first and second casing components 106 , 108 may be configured such that the attachment joints 140 are defined along the sides 141 of the impingement sleeve 102 .
- the flanges 122 , 124 and shoulders 130 , 132 may generally define a straight or curved profile extending substantially tangentially and/or parallel to the profile of the sides 141 of the first and second casing component 106 , 108 .
- the casing components 106 , 108 may generally be configured to be secured to one another at the attachment joints 140 using any suitable means. However, in several embodiments of the present subject matter, the casing components 106 , 108 may be configured to be weldlessly attached to one another.
- the first and second flanges 122 , 124 may define a plurality of flange openings 134 forming a bolt hole pattern which generally corresponds to the bolt hole pattern formed by a plurality of shoulder openings 136 defined in first and second shoulders 130 , 132 .
- each of the flange openings 134 defined in the first mounting flange 122 may be configured to be aligned with one of the shoulder openings 136 defined in the first mounting shoulder 130 when the first and second casing components 106 , 108 are positioned around the inner duct 104 .
- each of the flange openings 134 defined in the second mounting flange 124 may be configured to be aligned with one of the shoulder openings 136 defined in the second mounting shoulder 132 .
- the flange openings 134 and the shoulder openings 136 may generally be configured such that a fastener 138 may be disposed through the aligned openings 134 , 136 in order to permit the first casing component 106 to be attached to the second casing component 108 .
- the disclosed fasteners 138 may comprise any suitable fasteners known in the art.
- the fasteners 138 may comprise a plurality of threaded fasteners, such as threaded bolts, screws and the like.
- the fasteners 138 may comprise rivets, pins, clips, bolts, brackets, rods and any other suitable mechanical fasteners and/or attachment mechanisms.
- the fasteners 138 may be configured to be secured within the openings 134 , 136 using any suitable means.
- the fasteners 138 may be secured within the openings 134 , 136 using nuts, retaining pins, retaining rods, adhesives, and the like.
- each of the fasteners 138 may be secured within the openings 134 , 136 using a floating nut 144 .
- a floating nut 144 may comprise a threaded nut 146 which is movably disposed within a cage, frame or other retainer 148 .
- the threaded nut 146 may be disposed within the retainer 148 such that a gap is defined between the threaded nut 146 and the base 152 of the retainer 148 .
- the threaded nut 146 may move or otherwise float relative to the retainer base 152 within such gap.
- the threaded nut 146 may also be configured to move or otherwise float perpendicularly to retainer base 152 .
- each floating nut 144 may generally provide built-in flexibility in attaching the fasteners 138 to the threaded nuts 146 , thereby simplifying the blind attachment of the flanges 122 , 124 to the shoulders, 130 , 132 . It should be appreciated that the floating nuts 144 described herein may generally have any suitable floating nut configuration known in the art and, thus, need not have the exact configuration illustrated herein and described above.
- a plurality of floating nuts 144 may be mounted within the impingement sleeve 102 such that, when the first and second casing components 106 , 108 are positioned around the inner duct 104 , one floating nut 144 is generally aligned with each pair of aligned flange and shoulder openings 134 , 136 .
- the floating nuts 140 may be disposed along the inner surfaces 154 of the first and second flanges 122 , 124 .
- the floating nuts 144 may be disposed along the inner surfaces 156 ( FIG. 6 ) of the first and second shoulders 130 , 132 .
- each of the floating nuts 144 may be separately mounted onto an inner surface of the impingement sleeve 102 , such as the inner surfaces 154 of the flanges 122 , 124 .
- the retainer 148 of each floating nut 144 may be directly attached to the inner surfaces 154 of the flanges 122 , 124 (e.g., by welding or otherwise fastening the retainer 148 to the inner surfaces 154 ).
- the floating nuts 144 may be grouped or ganged into a common carriage or channel 158 , 160 for attachment to the inner surfaces 154 of the mounting flanges 122 , 124 .
- first and second elongated channels 158 , 160 may generally be secured to the inner surfaces 154 of the first and second flanges 122 , 124 , respectively, such as by welding or otherwise fastening the elongated channels 158 , 160 onto the inner surfaces 154 .
- each elongated channel 158 , 160 may generally be configured to define a shape or profile corresponding to the shape or profile of the portion of the impingement sleeve 102 to which it is attached.
- the first elongated channel 158 may generally extend lengthwise between the upstream and downstream ends 162 , 164 ( FIG. 5 ) of the first flange 122 and may include a base 180 defining a curved profile generally corresponding to the curved profile of the first flange 122 .
- the second elongated channel 160 may generally extend lengthwise between the upstream and downstream ends 166 , 168 ( FIG.
- the second flange 124 may include a base 180 defining a curved profile generally corresponding to the curved profile of the second flange 124 .
- the elongated channels 158 , 160 may generally be secured substantially flush against the inner surfaces of the impingement sleeve 102 .
- the elongated channels 158 , 160 need not be configured to extend fully between the upstream and downstream ends 162 , 164 , 166 , 168 of the first and second flanges 122 , 124 .
- the elongated channels 158 , 160 may only extend partially between the upstream and downstream ends 162 , 164 , 166 , 168 .
- two or more elongated channels 158 , 160 may be secured between the upstream and downstream ends 162 , 164 , 166 , 168 of each flange 122 , 124 .
- each elongated channel 158 , 160 may generally include a plurality of floating nuts 144 mounted to the base 180 of each channel 158 , 160 .
- the retainers 148 of the floating nuts 144 may be welded or otherwise fastened to each base 180 .
- the spacing of the floating nuts 144 along each channel 158 , 160 may generally correspond to the spacing of the flange and shoulder openings 134 , 136 defined in the flanges 122 , 124 and the shoulders 130 , 132 , respectively.
- one floating nut 144 may generally be disposed in alignment with each pair of aligned flange and shoulder openings 134 , 136 .
- a plurality of threaded members such as threaded nuts 146 may be secured to the elongated channels 158 , 160 as an alternative to the floating nuts 144 .
- the elongated channels 158 , 160 may be configured to include sidewalls 161 extending substantially perpendicularly from the base 180 of each channel 158 , 160 .
- the elongated channels 158 , 160 may be configured simply as mounting plates and, thus, need not include the illustrated sidewalls 161 .
- first and second flanges 122 , 124 may be crimped together or attached together using an adhesive or other suitable bonding material.
- the first and second casing components 106 , 108 may also include corresponding pairs of lips 170 , 172 extending radially outwardly from the casing components 106 , 108 at their upstream ends 162 , 166 .
- the radially extending lips 170 , 172 may be configured such that, when the lips 170 of the first casing component 106 are secured to the lips 172 of the second casing component 108 , a seal 174 ( FIG. 5 ) disposed between an upstream component 176 of the combustor 20 ( FIG.
- the orientation of the radially extending lips 170 of the first casing component 106 may be configured to match or correspond to the orientation of the radially extending lips 172 of the second casing component 108 , such as by configuring the lips 170 , 172 to extend substantially parallel to one another when the first and second casing components 106 , 108 are positioned together.
- each of the radially extending lips 170 , 172 may be configured to extend substantially perpendicularly from the top and bottom ends 126 , 128 of the casing components 106 , 108 .
- the lips 170 , 172 may generally extend outwardly from the top and bottom ends 126 , 128 of the casing components 106 , 108 at any suitable angle.
- the lips 170 of the first casing component 106 may generally be configured to be attached to the lips 172 of the second casing component 108 using any suitable means.
- the lips 170 , 172 may define openings 178 configured to receive suitable fasteners 179 (e.g., bolts, screws, rivets, pins, other mechanical fasteners and the like) for attaching the lips 170 , 172 to one another.
- suitable fasteners 179 e.g., bolts, screws, rivets, pins, other mechanical fasteners and the like
- various other suitable attachment methods may be utilized to attach to the lips 170 , 172 to one another, such as by crimping the lips 170 , 172 together or by attaching the lips 170 , 172 together using an adhesive or other bonding material.
- the one or more shoulders 130 , 132 may be disposed on the first casing component 106 while one or more flanges 122 , 124 may be disposed on the second casing component 108 .
- the flanges 122 , 124 need not be disposed radially inwardly of the shoulders 130 , 132 .
- the shoulders 130 , 132 may be disposed radially inwardly of the flanges 122 , 124 .
- the first shoulder 130 may be configured to be disposed radially inwardly of the first flange 122 while the second shoulder 132 may be configured to be disposed radially outwardly of the second flange 124 .
- first and second casing components 106 , 108 need not be configured such that the attachment joints 140 defined at the flanges 122 , 124 and the shoulders 130 , 132 are formed at the top and bottom ends 26 , 128 of the impingement sleeve 102 . Rather, the casing components 106 , 108 may be configured such that the attachment joints 140 are formed at any location along the outer perimeter of the impingement sleeve 102 , such as on the sides 141 or corners of the impingement sleeve 102 . Further, in another embodiment, the impingement sleeve 102 may include more than two casing components. For instance, the impingement sleeve 102 may include three or more casing components, with the casing components being configured to be attached to one another so as to encase the inner duct 104 .
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Abstract
An impingement sleeve for a transition piece of a gas turbine is disclosed. The impingement sleeve generally includes a first casing configured to surround a portion of an inner duct of the transition piece and a second casing configured to surround a portion of the inner duct. Additionally, the impingement sleeve may include a joint defined between the first and second casings. The joint may include a plurality of fasteners configured to attach the first casing to the second casing.
Description
- The present subject matter relates generally to gas turbines and, more particularly, to an impingement sleeve for a transition piece of a gas turbine combustor.
- Gas turbines typically include a compressor section, a combustion section, and a turbine section. The compressor section pressurizes air flowing into the turbine. The pressurized air discharged from the compressor section flows into the combustion section, which may be characterized by a plurality of combustors disposed around an annular array about the axis of the engine. Each of the plurality of combustors includes a combustion liner, which defines the combustion chamber of the combustor. As such, air entering each combustor is mixed with fuel and combusted within the combustion liner. Hot gases of combustion flow from the combustion liner through a transition piece to the turbine section of the gas turbine to drive the turbine and generate power.
- The transition piece of a gas turbine may be configured as a double walled component. In particular, the transition piece may include an impingement sleeve and an inner duct disposed radially inwardly from the impingement sleeve. The inner duct is generally configured to transport the flow of hot gases from the combustion chamber to a first stage nozzle of the turbine section. The impingement sleeve is generally configured to provide impingement cooling for the inner duct. For example, the impingement sleeve may define a plurality cooling holes configured to receive the pressurized air discharged from the compressor section.
- It is often the case that the geometry or shape of the inner duct necessitates that the impingement sleeve be formed from two or more sections configured to be assembled around the inner duct. Typically, the sections of the impingement sleeve are welded to one another. However, the process of welding the impingement sleeve sections together is often a difficult task. Moreover, by welding the sections to one another, the disassembly of the impingement sleeve in the field in order to perform inspections and/or repairs can be quite challenging and very time consuming.
- Accordingly, an impingement sleeve that can be easily assembled and disassembled would be welcomed in the art.
- 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 aspect, the present subject matter discloses an impingement sleeve for a transition piece of a gas turbine. The impingement sleeve generally includes a first casing configured to surround a portion of an inner duct of the transition piece and a second casing configured to surround a portion of the inner duct. Additionally, the impingement sleeve may include a substantially flat joint defined between the first and second casings. The substantially flat joint may include a plurality of fasteners configured to attach the first casing to the second casing.
- In another aspect, the present subject matter discloses an impingement sleeve for a transition piece of a gas turbine. The impingement sleeve generally includes a first casing configured to surround a portion of an inner duct of the transition piece and a second casing configured to surround a portion of the inner duct. Additionally, the impingement sleeve may include a joint defined between the first and second casings. The joint may include a plurality of fasteners configured to attach the first casing to the second casing. Further, at least one channel may be mounted to an inner surface of at least one of the first casing and the second casing. The channel may generally include a plurality of threaded nuts secured thereto.
- 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:
-
FIG. 1 illustrates a schematic depiction of a gas turbine; -
FIG. 2 illustrates a cross-sectional, side view of a combustor of a gas turbine; -
FIG. 3 illustrates a perspective view of one embodiment of an impingement sleeve in accordance with aspects of the present subject matter; -
FIG. 4 illustrates an exploded view of one embodiment of a double walled transition piece in accordance with aspects of the present subject matter; -
FIG. 5 illustrates a cross-sectional, side view of the double walled transition piece shown inFIG. 4 ; and -
FIG. 6 illustrates a partial, cross-sectional view of one embodiment of an attachment joint for attaching components of an impingement sleeve together in accordance with aspects of the present subject matter. - 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.
- Referring to the drawings,
FIG. 1 illustrates a schematic depiction of agas turbine 10. Thegas turbine 10 includes acompressor section 12, acombustion section 14, and aturbine section 16. Thecombustion section 14 may include a plurality of combustors 20 (one of which is illustrated inFIG. 2 ) disposed around an annular array about the axis of thegas turbine 10. 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 form theshaft 18. During operation of thegas turbine 10, thecompressor section 12 supplies compressed air to thecombustion section 14. The compressed air is mixed with fuel and burned within each combustor 20 (FIG. 2 ) and hot gases of combustion flow from thecombustion section 14 to theturbine section 16, wherein energy is extracted from the hot gases to produce work. - Referring to
FIG. 2 , a cross-sectional side view of an embodiment of acombustor 20 of thecombustion section 14 of agas turbine 10 is illustrated. Thecombustor 20 may generally include a substantiallycylindrical combustion casing 22 secured to a portion of agas turbine casing 24, such as a compressor discharge casing or a combustion wrapper casing. Aflange 26 may generally extend outwardly from an upstream end of thecombustion casing 22. Theflange 26 may be configured such that an end cover assembly (not illustrated) may be secured to thecombustion casing 22. As is generally known, the end cover assembly may include a plurality of fuel nozzles (not shown). - The
combustor 20 may also include aninternal flow sleeve 28 and acombustion liner 30 substantially concentrically arranged within theflow sleeve 28. Thecombustion liner 30 may generally define a substantiallycylindrical combustion chamber 32, wherein fuel and air are injected and combusted to produce hot gases of combustion. Additionally, both the flow sleeve 28 and thecombustion liner 30 may extend, at their downstream ends, to a double walledtransition piece 34, including animpingement sleeve 36 and aninner duct 38 disposed radially inwardly from theimpingement sleeve 36. In particular, thecombustion liner 30 may be coupled at its downstream end to theinner duct 38 such that thecombustion liner 30 and theinner duct 38 generally define a flowpath for the hot gases of combustion flowing from eachcombustor 20 to theturbine section 16 of the gas turbine 10 (FIG. 1 ). Moreover, theflow sleeve 28 may be coupled at its downstream end to theimpingement sleeve 36 such that theflow sleeve 28 and theimpingement sleeve 36 generally define a flowpath for the pressurized air discharged from thecompressor section 12 of the gas turbine 10 (FIG. 1 ). For example, theimpingement sleeve 36 may define a plurality ofcooling holes 40 configured to permit the pressurized air to enter the radial space defined between theinner duct 38 and theimpingement sleeve 36. - Further, as shown in
FIG. 2 , one or both of the downstream ends ofimpingement sleeve 36 and theinner duct 38 may be coupled to a transition pieceaft frame 42. As is generally understood, theaft frame 42 may be configured to attach thetransition piece 34 to a first stage nozzle (not shown) of the turbine section 16 (FIG. 1 ) such that the hot gases of combustion flowing through theinner duct 38 may be directed into theturbine section 16. - Referring now to
FIGS. 3-6 , one embodiment of a doublewalled transition piece 100 and, particularly, one embodiment of animpingement sleeve 102 suitable for use with thetransition piece 100 is illustrated in accordance with aspects of the present subject matter. In particular,FIG. 3 illustrates a perspective view of theimpingement sleeve 102.FIGS. 4 and 5 illustrate exploded and cross-sectional views, respectively, of thetransition piece 100, particularly illustrating various components and/or features of theimpingement sleeve 102. Additionally,FIG. 6 illustrates a partial, cross-sectional view of the attachment features of thecasing components impingement sleeve 102. - The disclosed
impingement sleeve 102 may generally be configured to be positioned radially outwardly from theinner duct 104 of thetransition piece 100. For example, theimpingement sleeve 102 may be disposed relative to theinner duct 104 such that a radial space orgap 110 is defined between theimpingement sleeve 102 and theinner duct 104. As such, the pressurized air discharged from thecompressor section 12 of the gas turbine 10 (FIG. 1 ) may be directed through theradial gap 110 to provide cooling for theinner duct 104. For instance, a plurality ofcooling holes 112 may be defined through theimpingement sleeve 102 such that the pressurized air flowing along its outer perimeter may be directed through theimpingement sleeve 102 and may impinge onto theouter surface 114 of theinner duct 104. Additionally, as is generally understood, the downstream ends 116 of theimpingement sleeve 102 and/or theinner duct 104 may be configured to be coupled to a downstream component of thegas turbine 10, such anaft frame 42 of the combustor 20 (FIG. 2 ). - As shown in the illustrated embodiment, the
impingement sleeve 102 includes afirst casing component 106 and asecond casing component 108. The first andsecond casing components inner duct 104 around which thecasing components second side portions second casing components inner duct 104 to take into account effective cooling configurations and the available packaging within thegas turbine 10. - In general, the first and
second casing components casing components inner duct 104. Thus, as shown, an attachment joint 140 may generally be formed at the interfaces of the first andsecond casing components casing components casing components casing components casing components casing components - For example, in the illustrated embodiment, the
first casing component 106 may include a first mountingflange 122 disposed at atop end 126 of thecasing component 106 and asecond mounting flange 124 disposed at abottom end 128 of thecasing component 106. Similarly, thesecond casing component 108 may include a first mountingshoulder 130 disposed at atop end 126 of thecasing component 108 and a second mountingshoulder 132 disposed at abottom end 128 of thecasing component 108. Theflanges shoulders casing components second casing components inner duct 104, thefirst shoulder 130 is aligned with and overlaps thefirst flange 122 and thesecond shoulder 132 is aligned with and overlaps thesecond flange 124 so as to define the attachment joints 140. Theflanges shoulders second casing components inner duct 104. - In several embodiments, to facilitate the overlapping configuration of the
casing components second casing component 108 may include a slight bend at the attachment joints 140 having a height generally equal to the width 143 (FIG. 6 ) of theflanges shoulders flanges FIG. 6 , thesecond casing component 108 may include a radially outwardly extendingbend 142 at the base of eachshoulder flanges shoulders second casing component 108 may include a radially inwardly extendingbend 142 at the base of eachshoulder flanges shoulders second casing component 108 need not define abend 142. For example, in one embodiment, thesecond casing component 108 may simply define a radius of curvature or may otherwise have a radial dimension which is slightly larger or slight smaller than the radius of curvature or radial dimension of thefirst casing component 106 such that theflanges shoulders casing components - Additionally, in several embodiments of the present subject matter, the attachment joints 140 may generally be configured as substantially flat joints. By “substantially flat”, it is meant that the shape or profile of the portions of the
casing components impingement sleeve 102 in an area generally adjacent to thejoints 140. For example, theflanges shoulders second casing components FIGS. 3-4 and 6, the first andsecond flanges first casing component 106 in an area adjacent to the attachment joint 140 (e.g., the profile defined at the top and bottom ends 126, 128 of the first casing component 106). Similarly, the first andsecond shoulders second casing component 108 in an area adjacent to the attachment joints 140 (e.g., the profile defined at the top and bottom ends 126, 128 of the second casing component 108). Additionally, as shown, theflanges shoulders second casing components inner duct 104, the attachment joints 140 may generally have a substantially flat configuration with respect to the overall shape or profile of theimpingement sleeve 102. - It should be appreciated that, in embodiments in which the attachment joints 140 are configured as substantially flat joints, the corresponding profiles of the
flanges shoulders impingement sleeve 102. For example, in an alternative embodiment, the first andsecond casing components sides 141 of theimpingement sleeve 102. In such an embodiment, theflanges shoulders sides 141 of the first andsecond casing component - Referring still to
FIGS. 3-6 , thecasing components casing components second flanges flange openings 134 forming a bolt hole pattern which generally corresponds to the bolt hole pattern formed by a plurality ofshoulder openings 136 defined in first andsecond shoulders flange openings 134 defined in the first mountingflange 122 may be configured to be aligned with one of theshoulder openings 136 defined in the first mountingshoulder 130 when the first andsecond casing components inner duct 104. Similarly, each of theflange openings 134 defined in the second mountingflange 124 may be configured to be aligned with one of theshoulder openings 136 defined in the second mountingshoulder 132. Accordingly, theflange openings 134 and theshoulder openings 136 may generally be configured such that afastener 138 may be disposed through the alignedopenings first casing component 106 to be attached to thesecond casing component 108. - In general, the disclosed
fasteners 138 may comprise any suitable fasteners known in the art. For instance, in several embodiments, thefasteners 138 may comprise a plurality of threaded fasteners, such as threaded bolts, screws and the like. In alternative embodiments, thefasteners 138 may comprise rivets, pins, clips, bolts, brackets, rods and any other suitable mechanical fasteners and/or attachment mechanisms. Additionally, thefasteners 138 may be configured to be secured within theopenings fasteners 138 may be secured within theopenings fasteners 138 may be secured within theopenings nut 144. - As is generally understood, a floating
nut 144 may comprise a threadednut 146 which is movably disposed within a cage, frame orother retainer 148. For example, as shown inFIG. 6 , the threadednut 146 may be disposed within theretainer 148 such that a gap is defined between the threadednut 146 and thebase 152 of theretainer 148. As such, the threadednut 146 may move or otherwise float relative to theretainer base 152 within such gap. Moreover, in addition to being capable of moving towards and away from theretainer base 152, the threadednut 146 may also be configured to move or otherwise float perpendicularly toretainer base 152. As such, the threadednut 146 may be displaced or may otherwise be moved into alignment with thefastener 138 as it is inserted through theopenings nut 144 may generally provide built-in flexibility in attaching thefasteners 138 to the threadednuts 146, thereby simplifying the blind attachment of theflanges nuts 144 described herein may generally have any suitable floating nut configuration known in the art and, thus, need not have the exact configuration illustrated herein and described above. - In several embodiments, a plurality of floating
nuts 144 may be mounted within theimpingement sleeve 102 such that, when the first andsecond casing components inner duct 104, one floatingnut 144 is generally aligned with each pair of aligned flange andshoulder openings FIGS. 5 and 6 , the floatingnuts 140 may be disposed along theinner surfaces 154 of the first andsecond flanges shoulders flanges nuts 144 may be disposed along the inner surfaces 156 (FIG. 6 ) of the first andsecond shoulders - Additionally, in one embodiment, each of the floating
nuts 144 may be separately mounted onto an inner surface of theimpingement sleeve 102, such as theinner surfaces 154 of theflanges retainer 148 of each floatingnut 144 may be directly attached to theinner surfaces 154 of theflanges 122, 124 (e.g., by welding or otherwise fastening theretainer 148 to the inner surfaces 154). Alternatively, the floatingnuts 144 may be grouped or ganged into a common carriage orchannel inner surfaces 154 of the mountingflanges elongated channels inner surfaces 154 of the first andsecond flanges elongated channels inner surfaces 154. - In several embodiments, each
elongated channel impingement sleeve 102 to which it is attached. Thus, in the illustrated embodiment, the firstelongated channel 158 may generally extend lengthwise between the upstream and downstream ends 162, 164 (FIG. 5 ) of thefirst flange 122 and may include a base 180 defining a curved profile generally corresponding to the curved profile of thefirst flange 122. Similarly, the secondelongated channel 160 may generally extend lengthwise between the upstream and downstream ends 166, 168 (FIG. 5 ) of thesecond flange 124 and may include a base 180 defining a curved profile generally corresponding to the curved profile of thesecond flange 124. As such, theelongated channels impingement sleeve 102. - It should be appreciated that, in alternative embodiments, the
elongated channels second flanges elongated channels elongated channels flange - Moreover, as shown in FIGS. 3 and 5-6, each
elongated channel nuts 144 mounted to thebase 180 of eachchannel retainers 148 of the floatingnuts 144 may be welded or otherwise fastened to each base 180. Additionally, it should be appreciated that the spacing of the floatingnuts 144 along eachchannel shoulder openings flanges shoulders elongated channels inner surfaces casing components casing components inner duct 104, one floatingnut 144 may generally be disposed in alignment with each pair of aligned flange andshoulder openings - It should be appreciated that, in further embodiments, a plurality of threaded members, such as threaded
nuts 146, may be secured to theelongated channels FIGS. 3 and 6 , in one embodiment, theelongated channels sidewalls 161 extending substantially perpendicularly from thebase 180 of eachchannel elongated channels sidewalls 161. - It should also be appreciated that, as an alternative to using
fasteners 138 and floating nuts 144 (or threaded nuts 146), various other suitable attachment methods may be utilized to weldlessly attach to the first andsecond flanges second shoulders flanges shoulders - The first and
second casing components lips casing components radially extending lips lips 170 of thefirst casing component 106 are secured to thelips 172 of thesecond casing component 108, a seal 174 (FIG. 5 ) disposed between anupstream component 176 of the combustor 20 (FIG. 1 ) and the upstream ends 162, 166 of thecasing components radially extending lips 170 of thefirst casing component 106 may be configured to match or correspond to the orientation of theradially extending lips 172 of thesecond casing component 108, such as by configuring thelips second casing components radially extending lips casing components lips casing components - It should also be appreciated that the
lips 170 of thefirst casing component 106 may generally be configured to be attached to thelips 172 of thesecond casing component 108 using any suitable means. For instance, in the illustrated embodiment, thelips openings 178 configured to receive suitable fasteners 179 (e.g., bolts, screws, rivets, pins, other mechanical fasteners and the like) for attaching thelips lips lips lips - It should be readily appreciated by those of ordinary skill in the art that, in addition to the configurations described herein, various other impingement sleeve configurations may be utilized within the scope of the present subject matter. For example, the one or
more shoulders first casing component 106 while one ormore flanges second casing component 108. Additionally, as noted above, theflanges shoulders shoulders flanges first shoulder 130 may be configured to be disposed radially inwardly of thefirst flange 122 while thesecond shoulder 132 may be configured to be disposed radially outwardly of thesecond flange 124. - Moreover, it should be appreciated that the first and
second casing components flanges shoulders impingement sleeve 102. Rather, thecasing components impingement sleeve 102, such as on thesides 141 or corners of theimpingement sleeve 102. Further, in another embodiment, theimpingement sleeve 102 may include more than two casing components. For instance, theimpingement sleeve 102 may include three or more casing components, with the casing components being configured to be attached to one another so as to encase theinner duct 104. - 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. An impingement sleeve for a transition piece of a gas turbine, the impingement sleeve comprising:
a first casing configured to surround a portion of an inner duct of the transition piece;
a second casing configured to surround a portion of the inner duct; and
a substantially flat joint defined between said first and second casings, said substantially flat joint including a plurality of fasteners configured to attach said first casing to said second casing.
2. The impingement sleeve of claim 1 , wherein said substantially flat joint is configured as a lap joint.
3. The impingement sleeve of claim 1 , wherein said first casing includes at least one flange and said second casing includes at least one shoulder, said at least one flange being attached to said at least one shoulder at said substantially flat joint.
4. The impingement sleeve of claim 3 , wherein said at least one flange and said at least one shoulder each define a plurality of openings, said plurality of openings being configured to receive said plurality of fasteners.
5. The impingement sleeve of claim 3 , wherein said at least one flange is disposed substantially parallel to said at least one shoulder at said substantially flat joint.
6. The impingement sleeve of claim 3 , wherein at least one of said at least one flange and said at least one shoulder is configured to extend substantially tangent to a profile of the impingement sleeve at said substantially flat joint.
7. The impingement sleeve of claim 1 , further comprising a plurality of threaded nuts mounted to an inner surface of at least one of said first casing and said second casing, said plurality of fasteners comprising a plurality of threaded fasteners being configured to be secured within said plurality of threaded nuts.
8. The impingement sleeve of claim 7 , wherein each of said plurality of threaded nuts is configured as a floating nut.
9. The impingement sleeve of claim 7 , wherein said plurality of threaded nuts is grouped within at least one channel mounted to said inner surface.
10. The impingement sleeve of claim 9 , wherein a profile of said at least one channel is configured to generally correspond to a profile of said inner surface such that said at least one channel is positioned substantially flush against said inner surface.
11. The impingement sleeve of claim 1 , wherein said first casing includes at least one lip extending substantially perpendicularly from an end of said first casing and said second casing includes at least one lip extending substantially perpendicularly from an end of said second casing, said at least one lip of said first casing being configured to be attached to said at least one lip of said second casing.
12. An impingement sleeve for a transition piece of a gas turbine, the impingement sleeve comprising:
a first casing configured to surround a portion of an inner duct of the transition piece;
a second casing configured to surround a portion of the inner duct;
a joint defined between said first and second casings, said joint including a plurality of threaded fasteners configured to attach said first casing to said second casing; and
at least one channel mounted to an inner surface of at least one of said first casing and said second casing, said at least one channel including a plurality of threaded nuts attached thereto.
13. The impingement sleeve of claim 12 , wherein said joint is configured to be substantially flat.
14. The impingement sleeve of claim 12 , wherein said first casing includes at least one flange and said second casing includes at least one shoulder, said at least one flange being attached to said at least one shoulder at said joint.
15. The impingement sleeve of claim 14 , wherein said at least one flange and said at least one shoulder each define a plurality of openings, said plurality of openings being configured to receive said plurality of fasteners.
16. The impingement sleeve of claim 14 , wherein said at least one flange is disposed substantially parallel to said at least one shoulder at said joint.
17. The impingement sleeve of claim 14 , wherein at least one of said at least one flange and said at least one shoulder is configured to extend substantially tangent to a profile of the impingement sleeve at said joint.
18. The impingement sleeve of claim 12 , wherein each of said plurality of threaded nuts is configured as a floating nut.
19. The impingement sleeve of claim 12 , wherein a profile of said at least one channel is configured to generally correspond to a profile of said inner surface such that said at least one channel is positioned substantially flush against said inner surface.
20. The impingement sleeve of claim 12 , wherein said first casing includes at least one lip extending substantially perpendicularly from an end of said first casing and said second casing includes at least one lip extending substantially perpendicularly from an end of said second casing, said at least one lip of said first casing being configured to be attached to said at least one lip of said second casing.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/012,838 US20120186260A1 (en) | 2011-01-25 | 2011-01-25 | Transition piece impingement sleeve for a gas turbine |
JP2012008544A JP2012154614A (en) | 2011-01-25 | 2012-01-19 | Transition piece impingement sleeve for gas turbine |
DE102012100517A DE102012100517A1 (en) | 2011-01-25 | 2012-01-23 | Impact sleeve of a transition piece for a gas turbine |
FR1250724A FR2970736A1 (en) | 2011-01-25 | 2012-01-25 | TRANSITION PIECE IMPACT SLEEVE FOR GAS TURBINE |
CN2012100277585A CN102620294A (en) | 2011-01-25 | 2012-01-30 | Transition piece impingement sleeve for a gas turbine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/012,838 US20120186260A1 (en) | 2011-01-25 | 2011-01-25 | Transition piece impingement sleeve for a gas turbine |
Publications (1)
Publication Number | Publication Date |
---|---|
US20120186260A1 true US20120186260A1 (en) | 2012-07-26 |
Family
ID=46467246
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/012,838 Abandoned US20120186260A1 (en) | 2011-01-25 | 2011-01-25 | Transition piece impingement sleeve for a gas turbine |
Country Status (5)
Country | Link |
---|---|
US (1) | US20120186260A1 (en) |
JP (1) | JP2012154614A (en) |
CN (1) | CN102620294A (en) |
DE (1) | DE102012100517A1 (en) |
FR (1) | FR2970736A1 (en) |
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US8759770B1 (en) | 2013-04-08 | 2014-06-24 | General Electric Company | System and method for qualifying usability risk associated with subsurface defects in a multilayer coating |
US20140260277A1 (en) * | 2013-03-18 | 2014-09-18 | General Electric Company | Flow sleeve for a combustion module of a gas turbine |
JP2014181701A (en) * | 2013-03-18 | 2014-09-29 | General Electric Co <Ge> | Flow sleeve assembly for combustion module of gas turbine combustor |
US20150361809A1 (en) * | 2014-06-11 | 2015-12-17 | General Electric Co. | Cooling passages for inner casing of a turbine exhaust |
US9316155B2 (en) | 2013-03-18 | 2016-04-19 | General Electric Company | System for providing fuel to a combustor |
US9316396B2 (en) | 2013-03-18 | 2016-04-19 | General Electric Company | Hot gas path duct for a combustor of a gas turbine |
US9383104B2 (en) | 2013-03-18 | 2016-07-05 | General Electric Company | Continuous combustion liner for a combustor of a gas turbine |
US9400114B2 (en) | 2013-03-18 | 2016-07-26 | General Electric Company | Combustor support assembly for mounting a combustion module of a gas turbine |
US20160238252A1 (en) * | 2015-02-17 | 2016-08-18 | Siemens Energy, Inc. | Thermally expandable transition piece |
US9574498B2 (en) | 2013-09-25 | 2017-02-21 | General Electric Company | Internally cooled transition duct aft frame with serpentine cooling passage and conduit |
US9631812B2 (en) | 2013-03-18 | 2017-04-25 | General Electric Company | Support frame and method for assembly of a combustion module of a gas turbine |
US20180031245A1 (en) * | 2016-07-27 | 2018-02-01 | Honda Motor Co., Ltd. | Structure for supporting nozzle guide of gas turbine engine |
US10066837B2 (en) | 2015-02-20 | 2018-09-04 | General Electric Company | Combustor aft mount assembly |
GB2571591A (en) * | 2018-03-03 | 2019-09-04 | Rolls Royce Plc | Rear outer discharge nozzle |
US10436445B2 (en) | 2013-03-18 | 2019-10-08 | General Electric Company | Assembly for controlling clearance between a liner and stationary nozzle within a gas turbine |
CN110494632A (en) * | 2017-03-30 | 2019-11-22 | 通用电气公司 | The machanical fastener of increasing material manufacturing with cooling channels |
US10816507B2 (en) | 2019-03-20 | 2020-10-27 | Raytheon Technologies Corporation | Apparatus and method and system for inspecting a component of a gas turbine engine |
US11371709B2 (en) | 2020-06-30 | 2022-06-28 | General Electric Company | Combustor air flow path |
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JP6644489B2 (en) * | 2015-07-16 | 2020-02-12 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor |
WO2017058155A1 (en) * | 2015-09-29 | 2017-04-06 | Siemens Aktiengesellschaft | Impingement cooling arrangement for gas turbine transition ducts |
JP6619307B2 (en) * | 2016-09-05 | 2019-12-11 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor |
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- 2012-01-23 DE DE102012100517A patent/DE102012100517A1/en not_active Withdrawn
- 2012-01-25 FR FR1250724A patent/FR2970736A1/en not_active Withdrawn
- 2012-01-30 CN CN2012100277585A patent/CN102620294A/en active Pending
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US20140260277A1 (en) * | 2013-03-18 | 2014-09-18 | General Electric Company | Flow sleeve for a combustion module of a gas turbine |
JP2014181701A (en) * | 2013-03-18 | 2014-09-29 | General Electric Co <Ge> | Flow sleeve assembly for combustion module of gas turbine combustor |
US10436445B2 (en) | 2013-03-18 | 2019-10-08 | General Electric Company | Assembly for controlling clearance between a liner and stationary nozzle within a gas turbine |
US9631812B2 (en) | 2013-03-18 | 2017-04-25 | General Electric Company | Support frame and method for assembly of a combustion module of a gas turbine |
US9316155B2 (en) | 2013-03-18 | 2016-04-19 | General Electric Company | System for providing fuel to a combustor |
US9316396B2 (en) | 2013-03-18 | 2016-04-19 | General Electric Company | Hot gas path duct for a combustor of a gas turbine |
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US9360217B2 (en) * | 2013-03-18 | 2016-06-07 | General Electric Company | Flow sleeve for a combustion module of a gas turbine |
US9383104B2 (en) | 2013-03-18 | 2016-07-05 | General Electric Company | Continuous combustion liner for a combustor of a gas turbine |
US9400114B2 (en) | 2013-03-18 | 2016-07-26 | General Electric Company | Combustor support assembly for mounting a combustion module of a gas turbine |
US8759770B1 (en) | 2013-04-08 | 2014-06-24 | General Electric Company | System and method for qualifying usability risk associated with subsurface defects in a multilayer coating |
US9574498B2 (en) | 2013-09-25 | 2017-02-21 | General Electric Company | Internally cooled transition duct aft frame with serpentine cooling passage and conduit |
US20150361809A1 (en) * | 2014-06-11 | 2015-12-17 | General Electric Co. | Cooling passages for inner casing of a turbine exhaust |
CN105221192A (en) * | 2014-06-11 | 2016-01-06 | 通用电气公司 | For the cooling channel of gas turbine exhaust inner shell |
US9903215B2 (en) * | 2014-06-11 | 2018-02-27 | General Electric Company | Cooling passages for inner casing of a turbine exhaust |
CN105221192B (en) * | 2014-06-11 | 2019-01-08 | 通用电气公司 | Cooling duct for gas turbine exhaust inner shell |
US20160238252A1 (en) * | 2015-02-17 | 2016-08-18 | Siemens Energy, Inc. | Thermally expandable transition piece |
US10066837B2 (en) | 2015-02-20 | 2018-09-04 | General Electric Company | Combustor aft mount assembly |
US10539328B2 (en) * | 2016-07-27 | 2020-01-21 | Honda Motor Co., Ltd. | Structure for supporting nozzle guide of gas turbine engine |
US20180031245A1 (en) * | 2016-07-27 | 2018-02-01 | Honda Motor Co., Ltd. | Structure for supporting nozzle guide of gas turbine engine |
CN110494632A (en) * | 2017-03-30 | 2019-11-22 | 通用电气公司 | The machanical fastener of increasing material manufacturing with cooling channels |
GB2571591A (en) * | 2018-03-03 | 2019-09-04 | Rolls Royce Plc | Rear outer discharge nozzle |
GB2571591B (en) * | 2018-03-03 | 2020-08-05 | Rolls Royce Plc | Rear outer discharge nozzle |
US10816507B2 (en) | 2019-03-20 | 2020-10-27 | Raytheon Technologies Corporation | Apparatus and method and system for inspecting a component of a gas turbine engine |
US11371709B2 (en) | 2020-06-30 | 2022-06-28 | General Electric Company | Combustor air flow path |
Also Published As
Publication number | Publication date |
---|---|
FR2970736A1 (en) | 2012-07-27 |
CN102620294A (en) | 2012-08-01 |
JP2012154614A (en) | 2012-08-16 |
DE102012100517A1 (en) | 2012-07-26 |
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Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:DICINTIO, RICHARD MARTIN;BELSOM, KEITH CLETUS;PENTECOST, RONNIE RAY;SIGNING DATES FROM 20101210 TO 20101214;REEL/FRAME:025688/0645 |
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