DE102013112879A1 - Super telescopic transverse ignition tube and method for assembling a combustion chamber assembly - Google Patents

Abstract

A super-telescopic cross-fire tube includes a cross-fire tube having a first portion and a second portion that are matingly engaged, the cross-fire tube extending from a first end to a second end to fluidly connect a combustion chamber and an adjacent combustion chamber. Also included is an outer guard that is spaced radially outside of at least a portion of the crossfire tube and surrounds it. Also included is a spring which extends from near the first end region to the second end region and is arranged between the cross-ignition tube and the outer guard, the cross-ignition tube being telescopically movable between a first position and a second position.

Description

GENERAL PRIOR ART

 The subject of the invention described here are gas turbine systems, and in particular a transverse ignition tube, as well as a method for assembling a combustion chamber arrangement.

 Neighboring combustors of a gas turbine are commonly connected via a crossfire tube to ensure substantially simultaneous ignition and balanced pressure in all combustion chambers of the gas turbine. The cross-firing tube is usually connected to the adjacent combustors via various fixtures including, for example, clamps. Geometric constraints and spatial constraints may affect the ability to use these fixtures. The adjacent combustion chambers can also be mounted as a module, which is used as a whole in a combustion chamber arrangement. Such mounting may limit the retention methods that are often necessary for transverse ignition tubes having a relatively rigid structure or a transverse ignition tube with limited flexibility to accommodate the insertion of the module into the combustion chamber assembly, as at least a portion of the transverse ignition tube is typically located in the space is to pick up the module. The installation of the crossfire tube also requires the correct placement of the crossfire tube relative to other components, with the placement being left to the discretion of the plant operator, which often results in human error.

BRIEF DESCRIPTION OF THE INVENTION

 In accordance with one aspect of the invention, a supertelescopic cross-firing tube includes a cross-firing tube having a first portion and a second portion matingly engaged, the cross-firing tube extending from a first end portion to a second end portion, fluidly around a combustion space and an adjacent combustion space connect to. Also included is an outer fender that is spaced radially outside at least a portion of the crosshead and surrounds it. Also included is a spring that extends from near the first end portion to the second end portion and is disposed between the cross-firing tube and the outer fender, the cross-firing tube being telescopically movable between a first position and a second position.

 The supertelescopic cross-firing tube may further include a first ring operatively connected to a combustor assembly part, the first ring having at least one anti-rotation member for engaging a corresponding anti-rotation surface near the first end portion and / or the second end portion of the transverse ignition tube.

 The at least one anti-rotation component of any aforementioned supertelescopic transfuse tube may have a non-planar geometry and the corresponding anti-rotation surface may have a corresponding non-planar geometry.

 The first ring of any aforementioned supertelescopic transfuse tube may be operatively connected to the combustor assembly near the first end region, wherein the first ring includes a plurality of cooling bores for cooling the first end region.

 The super-telescopic cross-fire tube of any of the aforementioned embodiments may further include a second ring operably connected to an adjacent combustor assembly near the second end region of the cross-firing tube.

 The at least one anti-rotation component of any aforementioned supertelescopic cross-firing tube may comprise a plurality of conical regions, wherein the corresponding anti-rotation surface may comprise a plurality of corresponding conical regions.

 The first ring of any aforementioned supertelescopic transfuse tube may be welded to the combustor assembly.

 The combustor assembly of any of the aforementioned supertelescopic cross-firing tubes may include a combustor flame tube, a plate surrounding the combustion chamber flame tube, and / or an air shield plate surrounding the plate.

In another aspect of the invention, a combustor assembly for a gas turbine includes a combustor assembly and an adjacent combustor assembly, wherein the combustor assembly includes a combustion chamber and the adjacent combustor assembly includes an adjacent combustor. Also included is a first ring that is operatively connected to the combustor assembly. Also included is a cross-firing tube disposed from a first end portion disposed adjacent to the first ring to a second end adjacent to the adjacent combustor assembly End area runs. Also included is a spring that extends from near the first end portion to the second end portion and is disposed between the cross-firing tube and an outer fender that surrounds at least a portion of the cross-firing tube.

 The crossfire tube of the combustor assembly may include a first portion and a second portion matingly engaged, the crossfire tube being telescopically movable between a first extended position and a second compressed position.

 The first ring of any of the aforementioned combustor assemblies may include at least one anti-rotation member for engaging a corresponding anti-rotation surface near the first end portion.

 The at least one anti-rotation component of any of the aforementioned combustor assemblies may have a non-planar geometry and the corresponding anti-rotation surface may have a corresponding non-planar geometry.

 The first ring of any of the aforementioned combustor assemblies may include a plurality of cooling bores for cooling the first end portion.

 The combustor assembly of any of the aforementioned embodiments may further include a second ring operatively connected to the adjacent combustor assembly near the second end portion of the crosshead.

 The at least one anti-rotation component of any of the aforementioned combustor assemblies may include a plurality of conical regions, wherein the corresponding anti-rotation surface may comprise a plurality of corresponding conical regions.

 The first ring of any of the aforementioned combustor assemblies may be welded to the combustor assembly.

 The first ring of any of the aforementioned combustor assemblies may be welded to a combustor liner, a metal sheet surrounding the combustor liner, and / or an airshield surrounding the shell.

 In yet another aspect of the invention, a method of assembling a combustor assembly is provided. The method includes inserting a first portion of a crossfire tube into a portion of a combustor assembly. It also includes rotating the first section of the transverse firing tube to align a rotational securing surface of the first section with a corresponding rotational securing feature of a first ring operatively connected to the combustor assembly. Further, it includes matingly engaging a second portion of the transverse firing tube with the first portion, with a spring disposed from the first portion toward the second portion. It further comprises compressing the crosshead tube from a first position to a second position, providing space for inserting an adjacent combustor assembly into the combustor assembly.

 The method may further include mechanically attaching the first portion to the combustor assembly.

 Any previously mentioned method may further include extending the crosshead tube to the first position after insertion of the adjacent combustor assembly.

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

BRIEF DESCRIPTION OF THE DRAWINGS

 The object considered as the invention is particularly pointed out and clearly claimed in the claims at the end of the description. 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:

1 is a simplified illustration of a gas turbine system;

2 is a partial perspective cross-sectional view of a combustion chamber assembly;

3 a perspective view of a cross-firing of the combustion chamber assembly is;

4 is a perspective view of a ring of the transverse ignition tube;

5 a cross-sectional view of an end portion of the transverse ignition tube is;

6 a partial cross-sectional view of a portion of the transverse ignition tube is in engagement with the ring;

7 a perspective view of the transverse ignition tube according to a further aspect of the invention;

8th a perspective view of a mechanical connecting element for securing the transverse ignition tube is;

9 is a partial cross-sectional view of the transverse ignition tube in a compressed state; and

10 FIG. 4 is a flowchart illustrating a method of assembling a combustor assembly. FIG.

 In the detailed description, embodiments of the invention together with advantages and features will be described by way of example with reference to the drawings.

DETAILED DESCRIPTION OF THE INVENTION

Referring to 1 is a simplified gas turbine 10 illustrated, which is constructed according to an embodiment of the present invention. The gas turbine 10 has a compressor 12 and a plurality of combustion chamber assemblies, which are arranged in a ring-tube arrangement, one of which under 14 is specified. As shown, the combustor assembly is shown 14 an end termination assembly 16 put on a combustion chamber 18 sealed and at least partially defined. The end termination assembly 16 carries a variety of nozzles 20 - 22 in the combustion chamber 18 into it. The nozzles 20 - 22 receive fuel via a common fuel inlet (not shown) and compressed air from the compressor 12 , The fuel and compressed air are in the combustion chamber 18 directed and ignited, so that a combustion product or an air flow that has a high temperature and a high pressure and for driving a turbine 24 is used. The turbine 24 has a variety of levels 26 - 28 on, working with the compressor 12 via a compressor / turbine shaft 30 are connected (also referred to as impeller).

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

With reference to 2 As noted previously, a ring-and-tube arrangement of combustion chamber assemblies is in a circumferentially-spaced manner about an axial centerline of the gas turbine engine 10 arranged. For a better understanding of the illustration, a partial view of the ring-tube assembly is shown and includes the combustion chamber assembly 14 and an adjacent combustor assembly 32 on. The combustion chamber 18 the combustion chamber assembly 14 and an adjacent combustion chamber 34 the adjacent combustion chamber assembly 32 are fluid with a transverse ignition tube 40 a transverse ignition tube arrangement 42 connected, wherein the transverse ignition tube 40 at a first end area 44 near a component of the combustion chamber assembly 14 is attached. In the component of the combustion chamber assembly 14 at which the first end area 44 attached, may be various components, including a combustion chamber flame tube 46 one of the combustion chamber flame tube 46 surrounding sheet metal 48 and / or an air shielding plate 49 where both the sheet metal 48 as well as the air shield 49 radially outside the combustion chamber flame tube 46 are spaced. The crossfire tube 40 is at a second end area 50 near a component of the adjacent combustor assembly 32 attached. Similar to the components noted above, the component of the adjacent combustor assembly may be similar 32 at which the second end area 50 is attached to an adjacent combustion chamber flame tube 52 , an adjacent sheet 54 and / or an adjacent air shield 56 each of which acts radially outwardly of the adjacent combustion chamber flame tube 52 is spaced. The crossfire tube 40 usually has a first section 58 and a second section 60 on, which are operatively connected. In one embodiment, the first section becomes 58 referred to as plug-in section, with the second section 60 as the receiving section for receiving the first section 58 is designated, matingly engaged. This arrangement provides a telescopic engagement between the first section 58 and the second section 60 ,

The crossfire tube 40 has an outer surface 62 and an inner surface 64 on, with the inner surface 64 an inner area 68 defined for the fluid coupling of the combustion chamber 18 and the adjacent combustion chamber 34 ensures, whereby the flow of a flame from the combustion chamber 18 to the adjacent combustion chamber 34 or vice versa. This flow is during the start of standalone operation (light-off) of Combustion chamber assemblies of the gas turbine 10 desirable and allows almost simultaneous ignition or reignition of the combustor assemblies.

Along the outer surface 62 is a spring 70 arranged from near the first end area 44 of the transverse ignition tube 40 too close to the second end area 50 of the transverse ignition tube 40 runs. The feather 70 is at least partially covered by an outer fender 72 kept that the outer surface 62 of the transverse ignition tube 40 surrounds. The outer fender 72 is radially outward to the outer surface 62 spaced to accommodate the placement of the spring 70 between the crossfire tube 40 and the outer fender 72 to offer. In the illustrated embodiment, the outer fender is 72 divided so that it only sections of the crossfire tube 40 and the spring 70 surrounds. The outer fender 72 In particular, it surrounds a section of the first section 58 and a section of the second section 60 of the transverse ignition tube 40 , It is understood, however, that the outer fender 72 along an entire, or nearly an entire, length of the transverse firing tube 40 can run. Regardless of the area of the transverse ignition tube 40 that of the outer fender 72 surrounded, the spring practices 70 an elastic spring biasing force on the first section 58 and the second section 60 of the transverse ignition tube 40 out. The crossfire tube 40 is between a illustrated first extended position and a second compressed position upon compression of the spring 70 telescopically movable. As will be described in detail below, the compression of the cross-firing tube is described 40 and the spring 70 during certain phases of assembly of the combustor assembly 14 and the adjacent combustor assembly 32 advantageous.

With reference to 3 - 5 combined with 2 has the transverse ignition tube arrangement 42 a first ring 80 firmly attached to a component of the combustion chamber assembly 14 is secured, for example, the combustion chamber flame tube 46 to which the combustion chamber flame tube 46 surrounding sheet metal 48 and / or the air shield 49 , Likewise, a second ring 82 fixed to a component of the adjacent combustion chamber assembly 32 secured. The first ring 80 and the second ring 82 may be welded to the component and are configured to be in the first end region 44 of the transverse ignition tube 40 or the second end region 50 of the transverse ignition tube 40 intervention. In the description of the first ring 80 and the second ring 82 Similar reference numerals are used because both are similarly designed and perform similar tasks.

Both the first ring 80 as well as the second ring 82 have a central opening 84 for receiving the first end portion 44 or the second end region 50 of the transverse ignition tube 40 on. The first end area 44 and the second end area 50 have a rotation locking surface 86 on, the at least one anti-rotation component 88 of the first ring 80 and the second ring 82 equivalent. In one embodiment, the at least one rotational securing component comprise 88 and the anti-rotation surface 86 corresponding non-planar surfaces, each having conical areas. It should be appreciated that numerous alternative geometries may be used, and it is further contemplated that corresponding protrusions and depressions may be used to form the anti-rotation surface 86 and the at least one rotational securing component 88 can be used. Regardless of the exact design of the anti-rotation surface 86 and the at least one rotational securing component 88 provide the appropriate features for self-alignment of the cross-fire tube assembly 42 , The arrangement of the transverse ignition tube 40 adjoining the first ring 80 and the second ring 82 provides in particular for a fixed rotational position of the transverse ignition tube 40 which allows an operator to make fewer decisions.

During operation of the combustor assembly 14 and the adjacent combustor assembly 32 are the first end area 44 and the second end area 50 through contact with the combustion chamber 18 and the adjacent combustion chamber 34 exposed to particularly high temperatures. For cooling purposes is in the first ring 80 and the second ring 82 in a region adjacent to the first end region 44 and the second end region 50 a variety of cooling holes 90 educated. It should be noted that the first end region 44 and the second end area 50 are formed with smooth, for example, circular, elliptical or similar contours. These smooth contours reduce any disturbances of airflow passing through an annulus between the combustion chamber flame tube 46 and the tin 48 and / or the air shield 49 flows.

With reference to 6 - 9 are various installation methods for the transverse ignition tube arrangement 42 shown. As previously described, the first end region 44 of the first section 58 or the second end region 50 of the second section 60 of the transverse ignition tube 40 in the central opening 84 of the first ring 80 or the second ring 82 be used ( 6 ). When contact between the rotation locking surface 86 and the at least one anti-rotation component 88 becomes the crossfire tube 40 aligned by itself in a fixed rotational position. In the illustrated embodiment, the second section is 60 engaged with the second ring 82 shown. The first paragraph 58 stands with the second section 60 engaged, the spring 70 between the crossfire tube 40 and the outer fender 72 as well as between the first end area 44 and the second end region 50 is inserted. The engagement between the first section 58 and the second section 60 can be before or after arranging the second section 60 with the second ring 82 respectively. It should also be recognized that the first section 58 before engaging with the second section 60 with the first ring 80 can be engaged. As in 7 shown is a threaded rod 98 with the first section 58 and / or the second section 60 be engaged and passes through an opening of the combustion chamber assembly 14 or the adjacent combustor assembly 32 to a mechanical fastener 92 ( 8th ) such as a washer-nut assembly. Such an arrangement is in securing the transverse ignition tube 40 help in a fixed position.

To accommodate sections of the combustor assembly 14 to create, for example, a module that enters the combustion chamber assembly 14 is used is the cross-firing tube 40 between a like in 2 shown first position 94 and a second position 96 ( 9 ) movable. The second position 96 includes a compressed state of the spring 70 and the transverse ignition tube 40 so that components of the combustion chamber assembly 14 can be used in the combustion chamber overall arrangement. The elasticity of the spring 70 leads to the extension of the transverse ignition tube 40 After placing the components far enough into the combustion chamber assembly 14 are inserted into it. The crossfire tube 40 usually has to be compressed over a long distance to provide the space necessary for reliable insertion of the components of the combustion chamber assembly 14 to accomplish. Arranging the spring 70 along substantially the entire length of the transverse ignition tube 40 allows the strong compression of the cross-firing tube 40 ,

As in the flowchart of 10 and with reference to 1 - 9 is also a method of mounting a combustion chamber assembly 100 provided. The gas turbine 10 and the transverse ignition tube assembly 42 have been previously described and concrete structural elements need not be described in more detail. The method of assembling a combustion chamber arrangement 100 includes inserting a first portion of a transverse ignition tube into a portion of a combustor assembly 102 , The first section of the cross firing tube is rotated to align a rotational securing surface of the first section with a corresponding rotational securing feature of a first ring 104 , A second portion of the transverse firing tube is matingly engaged with the first portion 106 , where the spring 70 from the first section 58 to the second section 60 is stretched. The transverse ignition tube is compressed from a first position to a second position 108 providing space for insertion of an adjacent combustor assembly or associated 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 these disclosed embodiments. Rather, the invention may be modified to encompass any number of variations, alterations, substitutions, or equivalent arrangements not heretofore described, but within the spirit and scope of the invention. Additionally, it should be understood that although various embodiments of the invention have been described, aspects of the invention may include only some of the described embodiments. The invention is therefore not to be understood as limited by the foregoing description, but is limited only by the scope of the appended claims.

 A supertelescopic cross-firing tube includes a cross-firing tube having a first portion and a second portion matingly engaged, the cross-firing tube extending from a first end portion to a second end portion to fluidly connect a combustion space and an adjacent combustion space. Also included is an outer fender that is spaced radially outside at least a portion of the crosshead and surrounds it. Also included is a spring that extends from near the first end portion to the second end portion and is disposed between the cross-firing tube and the outer fender, the cross-firing tube being telescopically movable between a first position and a second position.

LIST OF REFERENCE NUMBERS

10

gas turbine

12

compressor

14

combustion chamber assembly

16

Endabschlussbaugruppe

18

combustion chamber

20-22

 jet

24

turbine

26-28

 Variety of levels

30

Compressor / turbine shaft

32

combustion chamber assembly

34

combustion chamber

40

crossfire tube

42

Querzündrohranordnung

44

first end area

46

Combustor flame tube

48

sheet

49

Luftabschirmblech

50

second end area

52

Combustor flame tube

54

adjacent sheet metal

56

adjacent air shield

58

first section

60

second part

62

outer surface

64

palm

68

inner area

70

feather

72

outside apron

80

first ring

82

second ring

84

central opening

86

Rotation locking surface

88

at least one anti-rotation component

90

Variety of cooling holes

92

mechanical connection element

94

first position

96

second position

98

threaded rod

100

Method for mounting a combustion chamber arrangement

102

Inserting a first portion of a crossfire tube into a portion of a combustor assembly

104

A first portion of the transverse firing tube is rotated to align a rotational securing surface of the first portion with a corresponding rotational securing feature of a first ring

106

A second portion of the transverse firing tube is matingly engaged with the first portion

108

The transverse ignition tube is compressed from a first position to a second position

Claims (10)

 Super-telescopic transverse ignition tube, comprising: a cross-firing tube having a first portion and a second portion matingly engaged, the cross-firing tube extending from a first end portion to a second end portion to fluidly connect a combustion space and an adjacent combustion space; an outer fender that is spaced radially outside and surrounds at least a portion of the crosshead tube; and a spring extending from near the first end portion to the second end portion and disposed between the cross-firing tube and the outer fender, the cross-firing tube being telescopically movable between a first position and a second position. The supertelescopic cross-fire tube of claim 1, further comprising a first ring operatively connected to a combustor assembly part, the first ring having at least one anti-rotation member for engaging a corresponding anti-rotation surface near the first end portion and / or the second end portion of the transverse ignition tube. The supertelescopic cross-fire tube of claim 2, wherein the at least one anti-rotation component has a non-planar geometry and the corresponding anti-rotation surface has a corresponding non-planar geometry. The supertelescopic cross-fire tube of claim 2, wherein the first ring is operatively connected to the combustor assembly near the first end region, the first ring including a plurality of cooling bores for cooling the first end region. The supertelescopic cross-fire tube of claim 4, further comprising a second ring operatively connected to an adjacent combustor assembly near the second end region of the crossfire tube. The supertelescopic cross fire tube of claim 2, wherein the at least one anti-rotation component comprises a plurality of conical regions, the corresponding anti-rotation surface comprising a plurality of corresponding conical regions. The super-telescopic cross-fire tube of claim 2, wherein the first ring is welded to the combustion chamber assembly part. The supertelescopic transfuse of claim 2, wherein the combustor assembly comprises a combustor liner, a plate surrounding the combustion liner tube, and / or an airshield surrounding the liner. A combustor assembly for a gas turbine, comprising: a combustor assembly and an adjacent combustor assembly, the combustor assembly including a combustion space and the adjacent combustor assembly including an adjacent combustor space; a first ring operatively connected to the combustor assembly; a transverse ignition tube extending from a first end region disposed adjacent to the first ring a second end portion located near the adjacent combustor assembly; and a spring extending from near the first end portion to the second end portion and disposed between the cross-firing tube and an outer fender surrounding at least a portion of the cross-firing tube. A method of assembling a combustor assembly comprising: Inserting a first portion of a transverse ignition tube into a portion of a combustor assembly; Rotating the first section of the transverse firing tube to align a rotational securing surface of the first section with a corresponding rotational securing feature of a first ring operatively connected to the combustor assembly; matingly engaging a second portion of the transverse firing tube with the first portion, wherein a spring is disposed from the first portion toward the second portion, and

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