JP2014102067A - Adjustable telescoping cross-fire tube and method of assembling combustor structure - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a cross-fire tube and a method of assembling a combustor structure.SOLUTION: A adjustable telescoping cross-fire tube includes a cross-fire tube including a first portion and a second portion in mating engagement, the cross-fire tube extending from a first end region to a second end region for fluidly connecting a combustor chamber and an adjacent combustor chamber. The adjustable telescoping cross-fire tube also includes an outer shield spaced radially outwardly and surrounding at least a portion of the cross-fire tube. The adjustable telescoping cross-fire tube further includes a spring extending from proximity of the first end region to the second end region and disposed between the cross-fire tube and the outer shield, where the cross-fire tube is telescopingly moveable between a first position and a second position.

Description

  The subject matter disclosed herein relates to gas turbine systems and, more particularly, to methods for assembling crossfire tubes and combustor structures.

  In a gas turbine engine, generally, adjacent combustors are connected to each other by a crossfire tube, so that ignition is performed almost simultaneously in all the combustion chambers to equalize pressure. Crossfire tubes are typically coupled to adjacent combustors by various holding devices including, for example, clips. Such holding devices may become unusable due to geometric constraints or spatial limitations. In addition, adjacent combustors may be assembled as a module and collectively inserted into the combustor structure. Usually, at least a portion of the crossfire tube is placed in a space for receiving the module, such assembly results in a retention method normally required for a crossfire tube having a relatively rigid structure, i.e. the module. One of the limited flexibility that allows it to be inserted into the combustor structure may be limited. Furthermore, when installing a crossfire tube, it is necessary to appropriately arrange the crossfire tube with respect to other components, but the arrangement is left to the judgment or operation of the operator who performs the installation. It often causes human error.

U.S. Pat. No. 6,222,015

  According to one aspect of the present invention, a freely nested telescopic crossfire tube has a crossfire tube that includes a first portion and a second portion in mating engagement. The crossfire tube extends from the first end region to the second end region and fluidly couples the combustion chamber and the adjacent combustion chamber. The freely telescopic telescopic crossfire tube further includes an outer shield disposed at a distance on the radially outer side of the crossfire tube and surrounding at least a portion thereof. The freely telescopic telescopic crossfire tube further includes a spring extending from near the first end region to the second end region and disposed between the crossfire tube and the outer shield. The crossfire tube is movable telescopically between the first position and the second position.

  According to another aspect of the invention, a combustor structure for a gas turbine engine includes a combustor assembly and an adjacent combustor assembly. The combustor assembly has a combustion chamber and the adjacent combustor assembly has an adjacent combustion chamber. The combustor structure further has a first collar operably coupled to the combustor assembly. The combustor structure further includes a crossfire tube extending from a first end region disposed adjacent to the first collar to a second end region disposed proximate to the adjacent combustor assembly. The combustor structure further extends from near the first end region to the second end region and is disposed between the crossfire tube and an outer shield surrounding at least a portion of the crossfire tube. Has a spring.

  According to yet another aspect of the invention, a method for assembling a combustor structure is provided. The method includes inserting a first portion of a crossfire tube into a portion of a combustor assembly. The method further rotates the first portion of the crossfire tube to align the anti-rotation surface of the first portion with the corresponding anti-rotation feature of the first collar operably coupled to the combustor assembly. Including. The method further includes engaging the second portion of the crossfire tube to mate with the first portion and positioning the spring from the first portion to the second portion. The method further includes compressing the crossfire tube from a first position to a second position to provide clearance for inserting an adjacent combustor assembly into the combustor structure.

  These and other advantages and features will become more apparent from the following detailed description when taken in conjunction with the drawings.

  The subject matter regarded as the invention is particularly pointed out and distinctly claimed in the claims at the end of this specification. These and other features and advantages of the present invention will become apparent upon reading the following detailed description in conjunction with the accompanying drawings.

1 is a schematic view of a gas turbine system. It is a perspective fragmentary sectional view of a combustor structure. It is a perspective view of the cross fire pipe of a combustor structure. It is a perspective view of the color of a crossfire pipe. It is sectional drawing of the edge part area | region of a crossfire pipe | tube. It is a fragmentary sectional view in which a part of crossfire pipe is engaging with a collar. It is a perspective view of a crossfire pipe by other modes of the present invention. It is a perspective view of the mechanical fastener which fixes a crossfire pipe | tube. It is a fragmentary sectional view of the cross fire pipe in a compression state. It is a flowchart of the assembly method of a combustor structure.

  The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.

  Referring to FIG. 1, a diagram schematically illustrates a gas turbine engine 10 constructed in accordance with an exemplary embodiment of the present invention. The gas turbine engine 10 includes a compressor 12 and a plurality of combustor assemblies, one of which is arranged in a can annular array, one of which is indicated at 14. As shown, the combustor assembly 14 includes an end cover assembly 16 that seals the combustion chamber 18 and at least partially defines it. The plurality of nozzles 20-22 are supported by the end cover assembly 16 and extend into the combustion chamber 18. Fuel enters the nozzles 20 to 22 through a common fuel inlet (not shown), and further compressed air enters from the compressor 12. The fuel and compressed air enter the combustion chamber 18 and are ignited to produce a high temperature and high pressure combustion product or air stream that is used to drive the turbine 24. Turbine 24 includes a plurality of stages 26-28 that are operatively coupled to compressor 12 via a compressor / turbine shaft 30 (also referred to as a rotor).

  During operation, air enters the compressor 12 and is compressed into high pressure gas. The high pressure gas is supplied to the combustor assembly 14 and mixed in the combustion chamber 18 with fuel, for example natural gas, fuel oil, process gas and / or synthesis gas (syngas). The fuel / air or combustible mixture is ignited to produce a high temperature and high pressure combustion gas stream. In any case, combustor assembly 14 delivers a combustion gas stream to turbine 24, which converts thermal energy into mechanical rotational energy.

  Referring now to FIG. 2, as described above, the can annular array of combustor assemblies are circumferentially spaced about the axial centerline of the gas turbine engine 10. For purposes of clarity, a portion of the can annular array including the combustor assembly 14 and the adjacent combustor assembly 32 is shown. Combustion chamber 18 of combustor assembly 14 and adjacent combustion chamber 34 of adjacent combustor assembly 32 are fluidly coupled to crossfire tube 40 of crossfire tube configuration 42. A first end region 44 of the crossfire tube 40 is secured near a component of the combustor assembly 14. The components of the combustor assembly 14 to which the first end region 44 is secured include various configurations including a combustor liner 46, a sleeve 48 surrounding the combustor liner 46, and / or an air shield 49. May be an element. Each of the sleeve 48 and the air shield 49 are spaced apart radially outward of the combustor liner 46. The second end region 50 of the crossfire tube 40 is secured near the components of the adjacent combustor assembly 32. Similar to the components described above, the components of the adjacent combustor assembly 32 to which the second end region 50 is secured are spaced apart from each other on the adjacent combustor liner 52 and radially outward of the adjacent combustor liner 52. Adjacent sleeve 54 and / or adjacent air shield 56. The crossfire tube 40 typically includes a first portion 58 and a second portion 60 that are operably coupled to each other. In one embodiment, the first portion 58 is referred to as the male portion and is matingly engaged with a second portion 60 that receives the first portion 58, referred to as the female portion. This configuration forms a telescoping engagement between the first portion 58 and the second portion 60.

  The crossfire tube 40 includes an outer surface 62 and an inner surface 64. The inner surface 64 defines an internal region 68 that fluidly couples the combustion chamber 18 and the adjacent combustion chamber 34, thereby allowing a flame to travel from the combustion chamber 18 to the adjacent combustion chamber 34 or vice versa. This flame propagation is preferably done when ignition occurs in the combustor assembly of the gas turbine engine 10 so that the combustor assembly can be ignited or re-ignited at substantially the same time.

  The spring 70 is disposed along the outer surface 62 and extends from near the first end region 44 of the crossfire tube 40 to near the second end region 50. The spring 70 is at least partially retained by an outer shield 72 that surrounds the outer surface 62 of the crossfire tube 40. The outer shield 72 may be spaced radially outward from the outer surface 62, and a spring 70 may be disposed between the crossfire tube 40 and the outer shield 72. In the illustrated embodiment, the outer shield 72 is divided so as to surround only portions of the crossfire tube 40 and the spring 70. Specifically, the outer shield 72 surrounds a part of the first part 58 and a part of the second part 60 of the crossfire tube 40. However, it should be understood that the outer shield 72 may extend along the entire length, or substantially the entire length of the crossfire tube 40. Regardless of the extent to which the crossfire tube 40 is surrounded by the outer shield 72, an elastic spring biasing force by the spring 70 is applied to the first portion 58 and the second portion 60 of the crossfire tube 40. The crossfire tube 40 can be telescopically moved between a first extended position as shown in the drawing and a second compressed position when the spring 70 is compressed. As described in more detail below, it may be advantageous to be able to compress the crossfire tube 40 and the spring 70 at some stage in assembling the compressor assembly 14 and the adjacent compressor assembly 32.

  Referring now to FIGS. 3-5 in conjunction with FIG. 2, the crossfire tube configuration 42 may include a combustor liner 46, a sleeve 48 surrounding the combustor liner 46 and / or an air shield 49, such as an air shield 49. A first collar 80 is fixedly attached to the component. Similarly, the second collar 82 is fixedly attached to a component of the adjacent combustor assembly 32. The first collar 80 and the second collar 82 may be welded to their components and are configured to engage the first end region 44 and the second end region 50 of the crossfire tube 40, respectively. Is done. Since the first collar 80 and the second collar 82 perform similar functions with similar configurations, the same reference numerals will be used in their description.

  Both the first collar 80 and the second collar 82 include a central opening 84 that receives the first end region 44 and the second end region 50 of the crossfire tube 40, respectively. The first end region 44 and the second end region 50 include an anti-rotation surface 86 corresponding to at least one anti-rotation element 88 of the first collar 80 and the second collar 82. In one exemplary embodiment, the at least one anti-rotation element 88 and the anti-rotation surface 86 include coplanar non-planar surfaces each having a conical region. It should be understood that many other geometries can be used, and further, it is contemplated to use protrusions and depressions that coincide with each other to form the anti-rotation surface 86 and the at least one anti-rotation element 88. You can also. Regardless of the structural precision of the anti-rotation surface 86 and the at least one anti-rotation element 88, the matching features allow the cross-fire tube configuration 42 to self-align. Specifically, when the crossfire tube 40 is disposed so as to contact the first collar 80 and the second collar 82, the crossfire tube 40 reaches a fixed rotational position. Judgments will be reduced.

  During operation of the combustor assembly 14 and the adjacent combustor assembly 32, the first end region 44 and the second end region 50 are exposed to the combustion chamber 18 and the adjacent combustion chamber 34, so that particularly high temperature effects are present. It is easy to receive. In order to cool them, a plurality of cooling holes 90 are formed in regions adjacent to the first end region 44 and the second end region 50 of the first collar 80 and the second collar 82. It will be noted that the first end region 44 and the second end region 50 are of a smooth outer diameter such as a circle or an oval. These smooth outer diameters reduce the turbulence of the airflow that flows through the annulus between the combustor liner 46 and the sleeve 48 and / or the air shield 49.

  Referring now to FIGS. 6-9, there are shown several installation procedures for the crossfire tube configuration 42. FIG. As described above, the first end region 44 of the first portion 58 of the crossfire tube 40 or the second end region 50 of the second portion 60 may be the first collar 80 or the second collar 82. Can be respectively inserted into the central opening 84 (FIG. 6). When the anti-rotation surface 86 and at least one anti-rotation element 88 are in contact, the crossfire tube 40 is self-aligned in a fixed rotational position. In the illustrated embodiment, a second portion 60 that is engaged with the second collar 82 is shown. Engage the first portion 58 and the second portion 60 with the spring 70 sandwiched between the first end region 44 and the second end region 50 and between the crossfire tube 40 and the outer shield 72. Let Engagement between the first portion 58 and the second portion 60 can occur before or after placing the second portion 60 in the second collar 82. Similarly, it should be understood that the first portion 58 may be engaged with the first collar 80 prior to being engaged with the second portion 60. As shown in FIG. 7, a threaded rod 98 can be engaged with either or both of the first portion 58 and the second portion 60. The threaded rod 98 extends through an opening in the combustor assembly 14 or adjacent combustor assembly 32 and can receive a mechanical fastener 92 such as a washer and nut configuration (FIG. 8). Such a configuration helps to fix the crossfire tube 40 in a fixed position.

  Since the crossfire tube 40 can move between a first position 94 and a second position 96 (FIG. 9) as shown in FIG. 2, combustion such as a module inserted into the combustor assembly 14 Clearances for portions of vessel 14 can be formed. In the second position 96, the spring 70 and the crossfire tube 40 are in compression so that components of the combustor assembly 14 can be inserted into the entire combustor structure. When the component is fully inserted into the combustor assembly 14, the elasticity of the spring 70 causes the crossfire tube 40 to expand. Establishing the clearance necessary to ensure insertion of the combustor assembly 14 components generally requires the crossfire tube 40 to be compressed a long distance. Placing the spring 70 along substantially the entire length of the crossfire tube 40 allows the crossfire tube 40 to be compressed to a significant degree.

  As shown in the flow diagram of FIG. 10, with reference to FIGS. 1-9, a method 100 for assembling a combustor structure is further provided. Since the gas turbine engine 10 and the crossfire tube configuration 42 have already been described, the specific structural elements need not be described in greater detail. Combustor structure assembly method 100 includes inserting 102 a first portion of a crossfire tube into a portion of a combustor assembly. Rotate the first portion of the crossfire tube to align 104 the anti-rotation surface of the first portion with the corresponding anti-rotation feature in the first collar. The second portion of the crossfire tube is engaged 106 so as to mate with the first portion, and the spring 70 extends from the first portion 58 to the second portion 60. The crossfire tube is compressed 108 from the first position to the second position 108 to form a clearance for insertion of adjacent combustor assemblies or related components.

  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 can be modified to incorporate any number of variations, alternative embodiments, substitutions or equivalent arrangements not heretofore described, but which correspond to the spirit and scope of the invention. Furthermore, while various embodiments of the invention have been described, it should be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.

DESCRIPTION OF SYMBOLS 10 Gas turbine engine 12 Compressor 14 Combustor assembly 16 End cover assembly 18 Combustion chamber 20 Nozzle 21 Nozzle 22 Nozzle 24 Turbine 26 Multiple stage 27 Multiple stage 28 Multiple stage 30 Compressor / turbine shaft 32 Combustor assembly 34 Combustion Chamber 40 Crossfire tube 42 Crossfire tube configuration 44 First end region 46 Combustor liner 48 Sleeve 49 Air shield 50 Second end region 52 Combustor liner 54 Adjacent sleeve 56 Adjacent air shield 58 First portion 60 Second part 62 outer surface 64 inner surface 68 inner region 70 spring 72 outer shield 80 first collar 82 second collar 84 central opening 86 anti-rotation surface 88 at least one anti-rotation element 90 multiple cooling holes 92 mechanical fasteners 94 first Position 96 second position 98 threaded rod 100 method of assembling the combustor structure 102 inserting the first part of the crossfire tube into a part of the combustor assembly 104 rotating the first part of the crossfire tube; Aligning the anti-rotation surface of the first part with the corresponding anti-rotation feature of the first collar 106 Engaging the second part of the cross-fire tube to mate with the first part 108 Compress from the first position to the second position

Claims (20)

A freely nested telescopic crossfire tube,
A crossfire tube including a first portion and a second portion in mating engagement, extending from a first end region to a second end region and fluidly coupling a combustion chamber and an adjacent combustion chamber With a crossfire tube,
An outer shield disposed at an interval on the radially outer side of the crossfire tube and surrounding at least a portion thereof;
A spring extending from near the first end region to the second end region and disposed between the crossfire tube and the outer shield;
The cross fire tube is telescopically movable between a first position and a second position;
Freely nested telescopic crossfire tube. A first collar operably coupled to a combustor assembly component, the rotation corresponding to at least one of the first end region and the second end region of the crossfire tube The freely nested telescopic crossfire tube of claim 1, further comprising a first collar including at least one anti-rotation element that engages the blocking surface. The freely nested telescopic crossfire tube of claim 2, wherein the at least one anti-rotation element includes a non-planar geometry and the corresponding anti-rotation surface includes a corresponding non-planar geometry. The first collar is operably coupled to the combustor assembly component near the first end region and comprises a plurality of cooling holes for cooling the first end region. 2. Freely telescopic cross fire tube according to 2. The swivel telescopic crossfire tube of claim 4, further comprising a second collar operably coupled to an adjacent combustor assembly component near the second end region of the crossfire tube. The freely nested telescopic crossfire tube of claim 2, wherein the at least one anti-rotation element includes a plurality of conical regions, and the corresponding anti-rotation surface includes a plurality of corresponding conical regions. The freely nested telescopic crossfire tube of claim 2, wherein the first collar is welded to the combustor assembly component. The swivel telescopic crossfire tube of claim 2, wherein the combustor assembly component includes at least one of a combustor liner, a sleeve surrounding the combustor liner, and an air shield surrounding the sleeve. A combustor structure of a gas turbine engine,
A combustor assembly and an adjacent combustor assembly, wherein the combustor assembly has a combustion chamber and the adjacent combustor assembly has an adjacent combustion chamber; and
A first collar operably coupled to the combustor assembly;
A crossfire tube extending from a first end region disposed adjacent to the first collar to a second end region disposed proximate to the adjacent combustor assembly;
A spring extending from near the first end region to the second end region and disposed between the crossfire tube and an outer shield surrounding at least a portion of the crossfire tube; A combustor structure. The crossfire tube comprises a first portion and a second portion in mating engagement and is telescopically movable between a first extended position and a second compressed position. Item 10. A combustor structure according to Item 9. The combustor structure of claim 9, wherein the first collar comprises at least one anti-rotation element that engages a corresponding anti-rotation surface near the first end region. The combustor structure of claim 11, wherein the at least one anti-rotation element includes a non-planar geometry and the corresponding anti-rotation surface includes a corresponding non-planar geometry. The combustor structure of claim 9, wherein the first collar comprises a plurality of cooling holes for cooling the first end region. The combustor structure of claim 9, further comprising a second collar operably coupled to the adjacent combustor assembly near the second end region of the crossfire tube. The combustor structure of claim 11, wherein the at least one anti-rotation element includes a plurality of conical regions, and the corresponding anti-rotation surface includes a plurality of corresponding conical regions. The combustor structure of claim 9, wherein the first collar is welded to the combustor assembly. The combustor structure of claim 9, wherein the first collar is welded to at least one of a combustor liner, a sleeve surrounding the combustor liner, and an air shield surrounding the sleeve. A method of assembling a combustor structure,
Inserting a first portion of the crossfire tube into a portion of the combustor assembly;
Rotating the first portion of the crossfire tube aligns the anti-rotation surface of the first portion with a corresponding anti-rotation feature of a first collar operably coupled to the combustor assembly. Step to
Engaging a second portion of the crossfire tube to mate with the first portion, disposing a spring from the first portion to the second portion;
Compressing the crossfire tube from a first position to a second position to form a clearance for inserting an adjacent combustor assembly into the combustor structure. The method of claim 18, further comprising mechanically clamping the first portion to the combustor assembly. The method of claim 18, further comprising extending the crossfire tube to the first position after insertion of the adjacent combustor assembly.