Interface arrangement for a combustion chamber

Abstract

Combustion chamber which has: a flow sleeve (38) having a rear flange (44), the rear flange (44) comprising a first segment (46) extending radially with respect to a central axis of the combustion chamber and a cylindrical second segment (48) extending perpendicularly from the first segment (46); a transition piece (28) arranged adjacent to the rear flange (44) of the flow sleeve (38); an interface assembly (40) disposed axially between the flow sleeve (38) and the transition piece (28), the interface assembly (40) being a pre-assembled unit configured to be connected to the rear flange (44) of the flow sleeve (38), and comprising: an interface housing (54) having a cylindrical base wall (62) adapted to be coaxially received within the cylindrical second segment (48) of the rear flange (44), at least one rear wall segment (68), and a channel (70) defined by the base wall (62) and the at least one rear wall segment (68), the rear wall segment (68) being engageable and operatively connected to the rear flange (44) of the flow sleeve (38); and a piston ring (72) which is arranged in the channel (70).

Description

BACKGROUND OF THE INVENTION

[0001] The subject matter disclosed herein relates generally to gas turbines and, more particularly, to an interface assembly for a combustor assembly.

[0002] Gas turbines include a combustor assembly having a combustor liner for defining a combustion chamber, the combustor liner being disposed adjacent a downstream transition piece that directs hot gas to a turbine section of the gas turbine. Often, a flow sleeve surrounds the combustor liner, with the flow sleeve engaging the transition piece at an aft end of the flow sleeve. At the interface between the flow sleeve and the transition piece, a structure, such as a piston ring, is present that is used to control pressure drop across the combustor assembly. The piston rings experience progressively significant wear during a typical combustion cycle. When worn, replacing the interface between the flow sleeve and the transition piece is cumbersome, time-consuming, and labor-intensive.Undesirably, the entire flow sleeve must be removed from the combustion chamber assembly and sent to a manufacturer for replacement.

[0003] US 2011 / 0 252 805 A1 describes a combustion chamber assembly having a combustion chamber liner, a flow sleeve disposed radially outward from the combustion chamber liner and having a radially outwardly extending rear flange, a transition piece disposed adjacent to the rear flange of the flow sleeve, and an interface assembly disposed between the flow sleeve and the transition piece. The interface assembly is integrally formed with the rear flange of the flow sleeve and includes an interface housing having a cylindrical base wall projecting axially away from the rear flange of the flow sleeve and a circumferential annular rear wall defining, with the base wall, a channel in which a piston ring is matingly disposed.

[0004] JP 2003-193 866 A describes a transition piece connecting a combustion chamber section to a turbine section of a gas turbine, comprising a frame part at the downstream end of the transition piece comprising a seal sealing the transition piece against the turbine section, the seal being provided with a wear coating on its surfaces. BRIEF DESCRIPTION OF THE INVENTION

[0005] According to one aspect of the invention, a combustor comprises: a flow sleeve having an aft flange, the aft flange including a first segment extending radially with respect to a central axis of the combustion chamber and a cylindrical second segment extending perpendicularly from the first segment; a transition piece disposed adjacent the aft flange of the flow sleeve; and an interface assembly disposed axially between the flow sleeve and the transition piece, the interface assembly being a pre-assembled unit configured to be coupled to the aft flange of the flow sleeve.The interface assembly includes an interface housing having a cylindrical base wall configured to be coaxially received within the cylindrical second segment of the aft flange, at least one aft wall segment, and a channel defined by the base wall and the at least one aft wall segment, the aft wall segment being engageable and operatively connected to the aft flange of the flow sleeve. Further included is a piston ring matingly disposed within the channel.

[0006] The at least one rear wall segment can have a plurality of retaining tabs.

[0007] The rear flange of the flow sleeve of the interface assembly of any of the above-mentioned combustors may be substantially L-shaped.

[0008] The back wall segment of the interface housing of the interface assembly of any of the above-mentioned combustors may be welded to the flow sleeve.

[0009] The channel of the interface assembly of any combustion chamber interface assembly mentioned above may be substantially U-shaped.

[0010] The interface assembly of any combustion chamber mentioned above may further include a wear layer on at least one surface of the interface assembly, wherein the at least one surface may include a piston ring leading surface, a piston ring trailing surface, a piston ring inner surface, the inside of a leading wall of the interface assembly, and the rear of the rear flange.

[0011] The wear layer of the interface assembly of any of the above-mentioned combustion chambers may comprise a wear-resistant coating.

[0012] The wear-resistant coating of the interface assembly of any of the above-mentioned combustion chambers may be a cobalt-chromium alloy.

[0013] The interface assembly of any of the above-mentioned combustors may further include a resilient member disposed between an interface housing surface and an inner surface of the aft flange of the flow sleeve.

[0014] The resilient element of the interface assembly of any combustion chamber mentioned above may comprise a spring leaf seal.

[0015] The elastic element of the interface assembly of any combustion chamber mentioned above may be operatively connected to the interface housing.

[0016] The elastic element of the interface assembly of any of the above-mentioned combustion chambers may be formed integrally with the interface housing.

[0017] The interface assembly of any combustion chamber mentioned above may further include an anti-rotation component configured to maintain a circumferential position of the piston ring.

[0018] The interface assembly of any of the above-mentioned combustion chambers may be removable and replaceable with the flow sleeve.

[0019] According to another aspect of the invention, a combustor assembly includes a combustor liner and a flow sleeve disposed radially outward from the combustor liner, the flow sleeve having an aft flange, the aft flange including a first segment extending radially relative to a central axis of the combustor assembly and a cylindrical second segment extending perpendicularly from the first segment. Also included is a transition piece disposed adjacent an aft flange of the flow sleeve. Further included is an interface assembly disposed between the flow sleeve and the transition piece. The interface assembly is a preassembled subassembly configured to connect to the aft flange of the flow sleeve. The interface assembly includes a front wall having an outer surface and an inner surface.The interface assembly further includes a plurality of circumferentially spaced aft wall segments connected to the forward wall by a base wall, the base wall, the forward wall, and the plurality of circumferentially spaced aft wall segments being integrally formed and defining a channel, the interface assembly being operatively connected to the aft flange of the flow sleeve proximate a junction between the plurality of circumferentially spaced aft wall segments and the base wall. The interface assembly further includes a piston ring matingly disposed within the channel. The interface assembly still further includes a resilient member disposed between an outer surface of the base wall and an inner surface of the aft side of the flow sleeve.

[0020] The interface assembly of the above-mentioned combustion chamber assembly may be welded to the rear flange of the flow sleeve.

[0021] The combustion chamber assembly of any type mentioned above may further comprise a wear layer arranged on the inside of the front wall.

[0022] The combustion chamber assembly of any type mentioned above may further include a wear layer on at least one surface of the piston ring, wherein the at least one surface may include a piston ring leading surface, a piston ring trailing surface, and a piston ring inner surface.

[0023] The resilient member of any combustion chamber assembly mentioned above may comprise a leaf spring seal.

[0024] According to yet another aspect of the invention, a gas turbine includes a compressor, a turbine, and a combustor configured as described above.

[0025] These and other advantages and features will become more apparent from the following detailed description taken in conjunction with the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The subject matter regarded as the invention is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features and advantages of the invention will become apparent from the following detailed description taken in conjunction with the accompanying drawings, in which: Fig. 1 shows a schematic representation of a gas turbine; Fig. 2 shows a partial, schematic representation of a combustion chamber arrangement of the gas turbine; Fig. Figure 3 shows an enlarged perspective view of section III of the Fig. 2, showing an interface assembly operatively connected to a rear end of a flow sleeve of the combustor assembly; Fig. Figure 4 is a side elevational view of the interface assembly operatively connected to the rear end of the flow sleeve; Fig. Figure 5 shows a side elevation view of an interface assembly prior to connection to the flow sleeve; Fig. Figure 6 shows a perspective view of a portion of the interface assembly; and Fig. 7 shows a schematic representation of a portion of the interface arrangement according to another embodiment.

[0027] The detailed description explains, by way of example and with reference to drawings, embodiments of the invention together with their advantages and features. DETAILED DESCRIPTION OF THE INVENTION

[0028] With reference to Fig. 1, a turbine system, such as a gas turbine, is schematically illustrated by reference numeral 10. The gas turbine 10 includes a compressor section 12, a combustor section 14, a turbine section 16, a rotor 18, and a fuel nozzle 20. Note that one embodiment of the gas turbine 10 may include multiple compressors 12, combustors 14, turbines 16, rotors 18, and fuel nozzles 20. The compressor section 12 and the turbine section 16 are coupled by the rotor 18.

[0029] The combustor section 14 uses combustible liquid fuel and / or gaseous fuel, such as natural gas or hydrogen-rich syngas, to operate the gas turbine 10. For example, the fuel nozzles 20 are in fluid communication with an air supply and a fuel supply 22. The fuel nozzles 20 generate an air / fuel mixture and discharge the air / fuel mixture into the combustor section 14, causing combustion that produces a hot, pressurized exhaust gas. The combustor section 14 directs the hot, pressurized gas through a transition piece into a turbine nozzle (or "first-stage nozzle") and other stages of blades and vanes, causing rotation of the turbine blades within an outer casing 24 of the turbine section 16.

[0030] With reference to Fig. 2 illustrates a partial schematic view of the combustor section 14 of the gas turbine 10 in greater detail. The combustor section 14 includes a transition section 28 at least partially surrounded by an impingement sleeve 30 disposed radially outward of the transition section 28. Upstream therefrom, near a forward end 32 of the impingement sleeve 30, is a combustor liner 34 defining a combustion chamber 36. The combustor liner 34 is at least partially surrounded by a flow sleeve 38 disposed radially outward of the combustor liner 34. An interface assembly 40, described in detail below, is disposed at the junction between the forward end 32 of the impingement sleeve 30 and an aft end 42 of the flow sleeve 38.It is contemplated that certain embodiments of the combustor section 14 may not include the above-described impingement sleeve 30, such that a single liner of the transition piece 28 may be included and connected to the aft end 42 of the flow sleeve 38 and / or the combustor liner 34. Regardless of the precise embodiment, the interface assembly 40 is disposed at the junction between the entire transition piece assembly and the aft end 42 of the flow sleeve 38.

[0031] With reference to the Fig. 3-6, the aft end 42 of the flow sleeve 38 and the interface assembly 40 are illustrated in greater detail. As shown, the aft end 42 of the flow sleeve 38 includes an aft flange 44 having a first segment 46 and a second segment 48. The first segment 46 extends substantially radially with respect to a central axis of rotation of the gas turbine 10, and the second segment 48 is oriented substantially perpendicular to the first segment 46 such that the aft flange 44 is substantially L-shaped. The first segment 46 includes an aft side 50, and the second segment 48 includes an inner surface 52, each configured to couple to the interface assembly 40.

[0032] The interface assembly 40 is configured to seal an area between the flow sleeve 38 and the impingement sleeve 30 and / or the transition piece 28. Additionally, the interface assembly 40 controls pressure loss within the combustion chamber 36. The interface assembly 40 includes an interface housing 54 that extends circumferentially to form an annulus. The formed annulus may be a single, continuous structure or multiple segments joined to form an annulus. A front wall 56 extends from a first end 58 to a second end 60 and is integrally formed with a base wall 62 that extends from the second end 60 of the front wall 56 to a third end 64.Extending radially inward from the base wall 62, and in particular from the third end 64, are at least one, but typically a plurality of, rear wall segments 68, which form a channel 70 with the base wall 62 and the front wall 56. The interface housing 54 has a substantially U-shaped configuration in regions where the plurality of rear wall segments 68 are disposed, while the remainder of the interface housing 54 has a substantially L-shaped configuration defined by the front wall 56 and the base wall 62.

[0033] The interface housing 54 is configured to receive and snugly retain a piston ring 72 within the channel 70 defined by the front wall 56, the base wall 62, and a plurality of rear wall segments 68. The piston ring 72 is sized to be inserted into and disposed in close engagement with the channel 70. In particular, the piston ring 72 is in direct contact with an inner surface 74 of the front wall 56. Additionally, the piston ring inner surface 86 is in direct contact with the front end 32 of the impact sleeve 30 or with the front end of the transition piece 28 for embodiments lacking an impact sleeve. Retention of the piston ring 72 within the channel 70 is achieved at least in part by the plurality of rear wall segments 68 in contact with the piston ring 72. Additionally, an anti-rotation component, such asa pin-slot arrangement, to retain the piston ring 72 within the channel 70 and reduce or eliminate circumferential movement of the piston ring 72 therein.

[0034] A resilient member 80, such as a leaf spring seal, is operatively connected to an outer surface 78 of the base wall 62. In one embodiment, the resilient member 80 may be integrally formed with the base wall 62. The resilient member 80 is disposed between the outer surface 78 of the base wall 62 and an inner surface 52 of the second segment 48 of the rear flange 44 and is configured to radially bias the interface housing 54 and, consequently, the piston ring 72 in a radially inward direction.

[0035] To extend the life of the interface assembly 40, a wear layer is disposed on at least one surface of the piston ring 72 and the interface housing 54. Any suitable wear coating may be used. In one embodiment, the wear coating comprises a wear-resistant material, such as a cobalt-chromium alloy. One such material includes Stellite® 6. The wear coating may be disposed on a piston ring leading surface 82, a piston ring trailing surface 84, a piston ring inner surface 86, the inner side 74 of the leading wall 56, and / or the trailing surface 50.

[0036] The interface assembly 40 comprises a pre-assembled subassembly capable of replacing interface assemblies that have worn due to combustion operation. Advantageously, the user is not required to disassemble bulkier components, such as the flow sleeve 38, for shipping to the manufacturer during the course of the replacement effort. The interface assembly 40 is operatively connected to the flow sleeve 38 and can be easily disassembled therefrom. Operative connection of the interface assembly 40 to the flow sleeve 38 can be achieved in several contemplated ways. In one embodiment, the interface assembly 40 is welded at a location proximate the aft end of the second segment 48 of the aft flange 44. In another embodiment, the interface assembly 40 is coupled to the aft flange 44 by mechanical fasteners.

[0037] With reference to Fig. 7, an alternative embodiment of the interface assembly 40 is partially illustrated. In the illustrated embodiment, the interface housing 54 is a substantially L-shaped structure including the base wall 62 and the plurality of rear wall segments 68, with only a single rear wall segment shown. As with the previously described embodiments, the interface housing 54 is operatively connected, for example, by welding, to a location near the rear end of the second segment 48 of the rear flange 44. In such an embodiment, a wear coating consistent with the materials described above may be applied to the rear surface 50 of the rear flange 44.

[0038] While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention may be modified to include any variety of changes, modifications, substitutions, or equivalent arrangements not described hereinabove, which nevertheless remain within the spirit and scope of the invention. Furthermore, it is to be understood that while various embodiments of the invention have been described, aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be considered limited by the foregoing description, but is limited only by the scope of the appended claims.

[0039] An interface assembly for a combustor includes an interface housing having a channel defined by a front wall and at least one rear wall segment, the rear wall segment being operatively connected to a rear flange of a flow sleeve.

[0040] It also includes a piston ring that is positioned to fit within the channel. Parts list: 10 gas turbine 12 Compressor section 14 Combustion chamber section 16 Turbine section 18 Rotor 20 nozzle 22 Fuel supply 24 outer casings 28 Transition piece 30 impact sleeve 32 front end 34 Combustion chamber lining 36 combustion chamber 38 Flow sleeve 40 Interface arrangement 42 rear end 44 rear flange 46 first segment 48 second segment 50 back page 52 inner surface 54 interface housings 56 front wall 58 first end 60 second end 62 Base wall 64 third end 68 posterior wall segments 70 channel 72 piston ring 74 inner surface 78 outer surface 80 elastic element 82 Front 84 back 86 Inside

Claims

[1] Combustion chamber which has: a flow sleeve (38) having a rear flange (44), the rear flange (44) comprising a first segment (46) extending radially with respect to a central axis of the combustion chamber and a cylindrical second segment (48) extending perpendicularly from the first segment (46); a transition piece (28) arranged adjacent to the rear flange (44) of the flow sleeve (38); an interface assembly (40) disposed axially between the flow sleeve (38) and the transition piece (28), the interface assembly (40) being a pre-assembled unit configured to be connected to the rear flange (44) of the flow sleeve (38), and comprising: an interface housing (54) having a cylindrical base wall (62) adapted to be coaxially received within the cylindrical second segment (48) of the rear flange (44), at least one rear wall segment (68), and a channel (70) defined by the base wall (62) and the at least one rear wall segment (68), the rear wall segment (68) being engageable and operatively connected to the rear flange (44) of the flow sleeve (38); and a piston ring (72) which is arranged in the channel (70). [2] Combustion chamber according to claim 1, wherein the at least one rear wall segment (68) has a plurality of retaining tabs; and / or wherein the at least one rear wall segment (68) of the interface housing (54) is welded to the flow sleeve (38). [3] Combustion chamber according to claim 1, wherein the rear flange (44) of the flow sleeve (38) is substantially L-shaped. [4] Combustion chamber according to claim 1, wherein the channel (70) is substantially U-shaped. [5] The combustion chamber of claim 1, further comprising a wear coating on at least one surface of the interface assembly (40), the at least one surface comprising a piston ring front surface (82), a piston ring rear surface (84), a piston ring inner surface (86), the inner surface (74) of a front wall (56) of the interface assembly (40) and / or the rear surface (50) of the rear flange (44). [6] Combustion chamber according to claim 1, further comprising a resilient member (80) disposed between an interface housing surface and an inner surface (52) of the rear flange (44) of the flow sleeve (38). [7] Combustion chamber according to claim 6, wherein the elastic element (80) comprises a spring leaf; and / or wherein the elastic element (80) is operatively connected to the interface housing (54); and / or wherein the elastic element (80) is integrally formed with the interface housing (54). [8] The combustion chamber of claim 1, further comprising an anti-rotation component configured to maintain a circumferential position of the piston ring (72). [9] Combustion chamber arrangement comprising: a combustion chamber lining (34); a flow sleeve (38) disposed radially outwardly of the combustor liner (34), the flow sleeve (38) having a rear flange (44), the rear flange (44) including a first segment (46) extending radially relative to a central axis of the combustor assembly and a cylindrical second segment (48) extending perpendicularly from the first segment (46); a transition piece (28) arranged adjacent to the rear flange (44) of the flow sleeve (38); and an interface assembly (40) disposed axially between the flow sleeve (38) and the transition piece (28), the interface assembly (40) being a pre-assembled unit configured to be connected to the rear flange (44) of the flow sleeve (38), and comprising: a front wall (56) having an outer side and an inner side (74); a plurality of circumferentially spaced rear wall segments (68) connected to the front wall (56) by a base wall (62), the base wall (62), the front wall (56) and the plurality of circumferentially spaced rear wall segments (68) being integrally formed and defining a channel (70), the interface assembly (40) being engageable and operatively connected to the rear flange (44) of the flow sleeve (38) proximate a junction between the plurality of circumferentially spaced rear wall segments (68) and the base wall (62); a piston ring (72) which is suitably arranged in the channel (70); and an elastic element (80) arranged between an outer surface (78) of the base wall (62) and an inner surface (52) of the second segment (48) of the flow sleeve (38). [10] Gas turbine (10) comprising: a compressor (12); a turbine (16); and a combustion chamber according to any one of claims 1-8.

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