US20140137536A1 - Super telescoping cross-fire tube and method of assembling a combustor structure - Google Patents
Super telescoping cross-fire tube and method of assembling a combustor structure Download PDFInfo
- Publication number
- US20140137536A1 US20140137536A1 US13/682,965 US201213682965A US2014137536A1 US 20140137536 A1 US20140137536 A1 US 20140137536A1 US 201213682965 A US201213682965 A US 201213682965A US 2014137536 A1 US2014137536 A1 US 2014137536A1
- Authority
- US
- United States
- Prior art keywords
- cross
- fire tube
- combustor
- end region
- collar
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
- F23R3/48—Flame tube interconnectors, e.g. cross-over tubes
Definitions
- the subject matter disclosed herein relates to gas turbine systems, and more particularly to a cross-fire tube, as well as a method of assembling a combustor structure.
- Adjacent combustors of a gas turbine engine are typically connected by a cross-fire tube to ensure substantially simultaneous ignition and equalized pressure in all combustor chambers of the gas turbine engine.
- the cross-fire tube is typically coupled to the adjacent combustors by a variety of retention devices, including clips, for example. Geometry constraints and spatial limitations may hinder the ability to employ such retention devices. Additionally, the adjacent combustors may be assembled as a module that is inserted as a whole into a combustor structure.
- Assembly in this manner may limit the retention methods that are commonly required for cross-fire tubes having a relatively rigid construction or one of limited flexibility to accommodate the insertion of the module into the combustor structure, as at least a portion of the cross-fire tube is typically disposed in the space that is to receive the module.
- installation of the cross-fire tube requires proper positioning of the cross-fire tube, relative to other components, with the positioning left to an installation operator's discretion or manipulating, thereby often leading to human error.
- a super-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. Also included is an outer shield spaced radially outwardly and surrounding at least a portion of the cross-fire tube. Further included is a spring extending from proximate the first end region to the second end region and disposed between the cross-fire tube and the outer shield, wherein the cross-fire tube is telescopingly moveable between a first position and a second position.
- a combustor structure for a gas turbine engine includes a combustor assembly and an adjacent combustor assembly, the combustor assembly comprising a combustor chamber, the adjacent combustor assembly comprising an adjacent combustor chamber. Also included is a first collar operably coupled to the combustor assembly. Further included is a cross-fire tube extending from a first end region disposed adjacent the first collar to a second end region disposed proximate the adjacent combustor assembly. Yet further included is a spring extending from proximate the first end region to the second end region and disposed between the cross-fire tube and an outer shield surrounding at least a portion of the cross-fire tube.
- a method of assembling a combustor structure includes inserting a first portion of a cross-fire tube into a portion of a combustor assembly. Also included is rotating the first portion of the cross-fire tube to align an anti-rotation surface of the first portion with a corresponding anti-rotation feature of a first collar operably coupled to the combustor assembly. Further included is matably engaging a second portion of the cross-fire tube with the first portion, wherein a spring is positioned from the first portion to the second portion. Yet further included is compressing the cross-fire tube from a first position to a second position providing clearance for insertion of an adjacent combustor assembly into the combustor structure.
- FIG. 1 is a schematic illustration of a gas turbine system
- FIG. 2 is a perspective, partial cross-sectional view of a combustor structure
- FIG. 3 is a perspective view of a cross-fire tube of the combustor structure
- FIG. 4 is a perspective view of a collar of the cross-fire tube
- FIG. 5 is cross-sectional view of an end region of the cross-fire tube
- FIG. 6 is a partial cross-sectional view of a portion of the cross-fire tube engaged with the collar
- FIG. 7 is a perspective view of the cross-fire tube according to another aspect of the invention.
- FIG. 8 is a perspective view of a mechanical fastener for securing the cross-fire tube
- FIG. 9 is a partial cross-sectional view of the cross-fire tube in a compressed condition.
- FIG. 10 is a flow diagram illustrating a method of assembling a combustor structure.
- the gas turbine engine 10 constructed in accordance with an exemplary embodiment of the present invention is schematically illustrated.
- the gas turbine engine 10 includes a compressor 12 and a plurality of combustor assemblies arranged in a can annular array, one of which is indicated at 14 .
- the combustor assembly 14 includes an endcover assembly 16 that seals, and at least partially defines, a combustor chamber 18 .
- a plurality of nozzles 20 - 22 are supported by the endcover assembly 16 and extend into the combustor chamber 18 .
- the nozzles 20 - 22 receive fuel through a common fuel inlet (not shown) and compressed air from the compressor 12 .
- the fuel and compressed air are passed into the combustor chamber 18 and ignited to form a high temperature, high pressure combustion product or air stream that is used to drive a turbine 24 .
- the turbine 24 includes a plurality of stages 26 - 28 that are operationally connected to the compressor 12 through a compressor/turbine shaft 30 (also referred to as a rotor).
- air flows into the compressor 12 and is compressed into a high pressure gas.
- the high pressure gas is supplied to the combustor assembly 14 and mixed with fuel, for example natural gas, fuel oil, process gas and/or synthetic gas (syngas), in the combustor chamber 18 .
- fuel for example natural gas, fuel oil, process gas and/or synthetic gas (syngas)
- syngas synthetic gas
- the fuel/air or combustible mixture ignites to form a high pressure, high temperature combustion gas stream.
- the combustor assembly 14 channels the combustion gas stream to the turbine 24 which converts thermal energy to mechanical, rotational energy.
- a can annular array of combustor assemblies is arranged in a circumferentially spaced manner about an axial centerline of the gas turbine engine 10 .
- a partial view of the can annular array is shown and includes the combustor assembly 14 and an adjacent combustor assembly 32 .
- the combustor chamber 18 of the combustor assembly 14 and an adjacent combustor chamber 34 of the adjacent combustor assembly 32 are fluidly coupled with a cross-fire tube 40 of a cross-fire tube arrangement 42 , with the cross-fire tube 40 fixed at a first end region 44 proximate a component of the combustor assembly 14 .
- the component of the combustor assembly 14 to which the first end region 44 is fixed may be a variety of components, including a combustor liner 46 , a sleeve 48 that surrounds the combustor liner 46 , and/or an air shield 49 , each of the sleeve 48 and the air shield 49 spaced radially outwardly of the combustor liner 46 .
- the cross-fire tube 40 is fixed at a second end region 50 proximate a component of the adjacent combustor assembly 32 .
- the component of the adjacent combustor assembly 32 that the second end region 50 is fixed to may be an adjacent combustor liner 52 , an adjacent sleeve 54 and/or an adjacent air shield 56 , each spaced radially outwardly of the adjacent combustor liner 52 .
- the cross-fire tube 40 typically includes a first portion 58 and a second portion 60 that are operably coupled to each other.
- the first portion 58 is referred to as a male portion that is in mating engagement with the second portion 60 that is referred to as a female portion for receiving the first portion 58 .
- This arrangement provides a telescoping engagement between the first portion 58 and the second portion 60 .
- the cross-fire tube 40 includes an outer surface 62 and an inner surface 64 , with the inner surface 64 defining an interior region 68 that provides the fluid coupling of the combustor chamber 18 and the adjacent combustor chamber 34 , which allows passage of a flame from the combustor chamber 18 to the adjacent combustor chamber 34 , or vice versa. Such passage is desirable during light-off of the combustor assemblies of the gas turbine engine 10 and allows for nearly simultaneous ignition or re-ignition of the combustor assemblies.
- a spring 70 Disposed along the outer surface 62 is a spring 70 that extends from proximate the first end region 44 of the cross-fire tube 40 to proximate the second end region 50 of the cross-fire tube 40 .
- the spring 70 is at least partially retained by an outer shield 72 that surrounds the outer surface 62 of the cross-fire tube 40 .
- the outer shield 72 is spaced radially outwardly from the outer surface 62 to accommodate disposal of the spring 70 between the cross-fire tube 40 and the outer shield 72 .
- the outer shield 72 is segmented to only surround portions of the cross-fire tube 40 and the spring 70 . Specifically, the outer shield 72 surrounds a portion of the first portion 58 and a portion of the second portion 60 of the cross-fire tube 40 .
- the outer shield 72 may extend along an entire, or nearly an entire, length of the cross-fire tube 40 .
- the spring 70 provides a resilient spring biasing force on the first portion 58 and the second portion 60 of the cross-fire tube 40 .
- the cross-fire tube 40 is telescopingly moveable between a first extended position, as shown, and a second compressed position upon compression of the spring 70 .
- compression of the cross-fire tube 40 and the spring 70 is advantageous during certain phases of assembly of the combustor assembly 14 and the adjacent combustor assembly 32 .
- the cross-fire tube arrangement 42 includes a first collar 80 fixedly secured to a component of the combustor assembly 14 , such as the combustor liner 46 , the sleeve 48 that surrounds the combustor liner 46 , and/or the air shield 49 .
- a second collar 82 is fixedly secured to a component of the adjacent combustor assembly 32 .
- the first collar 80 and the second collar 82 may be welded to the component and is configured to engage the first end region 44 of the cross-fire tube 40 and the second end region 50 of the cross-fire tube 40 , respectively. Similar reference numerals will be employed in describing the first collar 80 and the second collar 82 , as both are similarly configured and perform similar functions.
- Both the first collar 80 and the second collar 82 include a central opening 84 for receiving the first end region 44 and the second end region 50 , respectively, of the cross-fire tube 40 .
- the first end region 44 and the second end region 50 include an anti-rotation surface 86 that corresponds to at least one anti-rotation component 88 of the first collar 80 and the second collar 82 .
- the at least one anti-rotation component 88 and the anti-rotation surface 86 comprise corresponding non-planar surfaces each having conical regions. It is to be appreciated that numerous alternative geometries may be employed and furthermore it is contemplated that corresponding protrusions and recesses may be utilized to form the anti-rotation surface 86 and the at least one anti-rotation component 88 .
- the corresponding features provide a self-aligning aspect for the cross-fire tube arrangement 42 .
- disposal of the cross-fire tube 40 into an abutting manner with the first collar 80 and the second collar 82 provides a fixed rotational position of the cross-fire tube 40 , thereby reducing judgment of an installation operator.
- first end region 44 and the second end region 50 are particularly susceptible to high temperatures due to exposure to the combustor chamber 18 and the adjacent combustor chamber 34 .
- a plurality of cooling holes 90 are formed in the first collar 80 and the second collar 82 in a region adjacent the first end region 44 and the second end region 50 for cooling purposes.
- the first end region 44 and the second end region 50 are formed of smooth contours, such as circular, elliptical or the like. These smooth contours reduce any disturbance of an airflow passing through an annulus between the combustor liner 46 and the sleeve 48 and/or the air shield 49 .
- FIGS. 6-9 various installation procedures of the cross-fire tube arrangement 42 are illustrated.
- the first end region 44 of the first portion 58 or the second end region 50 of the second portion 60 of the cross-fire tube 40 may be inserted into the central opening 84 of the first collar 80 or the second collar 82 , respectively ( FIG. 6 ).
- the cross-fire tube 40 is self-aligned into a fixed rotational position.
- the second portion 60 is shown in engagement with the second collar 82 .
- the first portion 58 is engaged with the second portion 60 , with the spring 70 sandwiched between the cross-fire tube 40 and the outer shield 72 , as well as between the first end region 44 and the second end region 50 . Engagement between the first portion 58 and the second portion 60 may take place before or after disposal of the second portion 60 with the second collar 82 . Similarly, it is to be appreciated that the first portion 58 may be engaged with the first collar 80 prior to engagement with the second portion 60 . As shown in FIG. 7 , a threaded rod 98 may be engaged with either or both of the first portion 58 and the second portion 60 and extends through an aperture of the combustor assembly 14 or the adjacent combustor assembly 32 to receive a mechanical fastener 92 ( FIG. 8 ), such as a washer and nut arrangement, for example. Such an arrangement assists in securing the cross-fire tube 40 in a fixed position.
- a mechanical fastener 92 FIG. 8
- the cross-fire tube 40 is moveable between a first position 94 , as shown in FIG. 2 , and a second position 96 ( FIG. 9 ).
- the second position 96 comprises a compressed condition of the spring 70 and the cross-fire tube 40 , such that components of the combustor assembly 14 may be inserted into the overall combustor structure.
- the resiliency of the spring 70 leads to extension of the cross-fire tube 40 after the components are sufficiently inserted into the combustor assembly 14 .
- Large distances of compression of the cross-fire tube 40 are typically required to establish necessary clearance for reliable insertion of the combustor assembly 14 components.
- Disposal of the spring 70 along substantially the entire length of the cross-fire tube 40 allows compression of the cross-fire tube 40 to a large degree.
- the method of assembling a combustor structure 100 includes inserting a first portion of a cross-fire tube into a portion of a combustor assembly 102 .
- the first portion of the cross-fire tube is rotated to align an anti-rotation surface of the first portion with a corresponding anti-rotation feature of a first collar 104 .
- a second portion of the cross-fire tube is matably engaged with the first portion 106 , with the spring 70 extended from the first portion 58 to the second portion 60 .
- the cross-fire tube is compressed from a first position to a second position 108 , thereby providing clearance for insertion of an adjacent combustor assembly or associated components.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Of Fluid Fuel (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A super-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. Also included is an outer shield spaced radially outwardly and surrounding at least a portion of the cross-fire tube. Further included is a spring extending from proximate the first end region to the second end region and disposed between the cross-fire tube and the outer shield, wherein 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 a cross-fire tube, as well as a method of assembling a combustor structure.
- Adjacent combustors of a gas turbine engine are typically connected by a cross-fire tube to ensure substantially simultaneous ignition and equalized pressure in all combustor chambers of the gas turbine engine. The cross-fire tube is typically coupled to the adjacent combustors by a variety of retention devices, including clips, for example. Geometry constraints and spatial limitations may hinder the ability to employ such retention devices. Additionally, the adjacent combustors may be assembled as a module that is inserted as a whole into a combustor structure. Assembly in this manner may limit the retention methods that are commonly required for cross-fire tubes having a relatively rigid construction or one of limited flexibility to accommodate the insertion of the module into the combustor structure, as at least a portion of the cross-fire tube is typically disposed in the space that is to receive the module. Furthermore, installation of the cross-fire tube requires proper positioning of the cross-fire tube, relative to other components, with the positioning left to an installation operator's discretion or manipulating, thereby often leading to human error.
- According to one aspect of the invention, a super-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. Also included is an outer shield spaced radially outwardly and surrounding at least a portion of the cross-fire tube. Further included is a spring extending from proximate the first end region to the second end region and disposed between the cross-fire tube and the outer shield, wherein the cross-fire tube is telescopingly moveable between a first position and a 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 comprising a combustor chamber, the adjacent combustor assembly comprising an adjacent combustor chamber. Also included is a first collar operably coupled to the combustor assembly. Further included is a cross-fire tube extending from a first end region disposed adjacent the first collar to a second end region disposed proximate the adjacent combustor assembly. Yet further included is a spring extending from proximate the first end region to the second end region and disposed between the cross-fire tube and an outer shield surrounding at least a portion of the cross-fire tube.
- According to yet another aspect of the invention, a method of assembling a combustor structure is provided. The method includes inserting a first portion of a cross-fire tube into a portion of a combustor assembly. Also included is rotating the first portion of the cross-fire tube to align an anti-rotation surface of the first portion with a corresponding anti-rotation feature of a first collar operably coupled to the combustor assembly. Further included is matably engaging a second portion of the cross-fire tube with the first portion, wherein a spring is positioned from the first portion to the second portion. Yet further included is compressing the cross-fire tube from a first position to a second position providing clearance for insertion of an adjacent combustor assembly into the combustor structure.
- These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
- The subject matter, which is 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 are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
-
FIG. 1 is a schematic illustration of a gas turbine system; -
FIG. 2 is a perspective, partial cross-sectional view of a combustor structure; -
FIG. 3 is a perspective view of a cross-fire tube of the combustor structure; -
FIG. 4 is a perspective view of a collar of the cross-fire tube; -
FIG. 5 is cross-sectional view of an end region of the cross-fire tube; -
FIG. 6 is a partial cross-sectional view of a portion of the cross-fire tube engaged with the collar; -
FIG. 7 is a perspective view of the cross-fire tube according to another aspect of the invention; -
FIG. 8 is a perspective view of a mechanical fastener for securing the cross-fire tube; -
FIG. 9 is a partial cross-sectional view of the cross-fire tube in a compressed condition; and -
FIG. 10 is a flow diagram illustrating a method of assembling 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 , agas turbine engine 10 constructed in accordance with an exemplary embodiment of the present invention is schematically illustrated. Thegas turbine engine 10 includes acompressor 12 and a plurality of combustor assemblies arranged in a can annular array, one of which is indicated at 14. As shown, thecombustor assembly 14 includes anendcover assembly 16 that seals, and at least partially defines, acombustor chamber 18. A plurality of nozzles 20-22 are supported by theendcover assembly 16 and extend into thecombustor chamber 18. The nozzles 20-22 receive fuel through a common fuel inlet (not shown) and compressed air from thecompressor 12. The fuel and compressed air are passed into thecombustor chamber 18 and ignited to form a high temperature, high pressure combustion product or air stream that is used to drive aturbine 24. Theturbine 24 includes a plurality of stages 26-28 that are operationally connected to thecompressor 12 through a compressor/turbine shaft 30 (also referred to as a rotor). - In operation, air flows into the
compressor 12 and is compressed into a high pressure gas. The high pressure gas is supplied to thecombustor assembly 14 and mixed with fuel, for example natural gas, fuel oil, process gas and/or synthetic gas (syngas), in thecombustor chamber 18. The fuel/air or combustible mixture ignites to form a high pressure, high temperature combustion gas stream. In any event, thecombustor assembly 14 channels the combustion gas stream to theturbine 24 which converts thermal energy to mechanical, rotational energy. - Referring now to
FIG. 2 , as noted above, a can annular array of combustor assemblies is arranged in a circumferentially spaced manner about an axial centerline of thegas turbine engine 10. For illustration clarity, a partial view of the can annular array is shown and includes thecombustor assembly 14 and anadjacent combustor assembly 32. Thecombustor chamber 18 of thecombustor assembly 14 and anadjacent combustor chamber 34 of theadjacent combustor assembly 32 are fluidly coupled with across-fire tube 40 of across-fire tube arrangement 42, with thecross-fire tube 40 fixed at afirst end region 44 proximate a component of thecombustor assembly 14. The component of thecombustor assembly 14 to which thefirst end region 44 is fixed may be a variety of components, including acombustor liner 46, asleeve 48 that surrounds thecombustor liner 46, and/or anair shield 49, each of thesleeve 48 and theair shield 49 spaced radially outwardly of thecombustor liner 46. Thecross-fire tube 40 is fixed at asecond end region 50 proximate a component of theadjacent combustor assembly 32. Similar to the components noted above, the component of theadjacent combustor assembly 32 that thesecond end region 50 is fixed to may be anadjacent combustor liner 52, anadjacent sleeve 54 and/or anadjacent air shield 56, each spaced radially outwardly of theadjacent combustor liner 52. Thecross-fire tube 40 typically includes afirst portion 58 and asecond portion 60 that are operably coupled to each other. In one embodiment, thefirst portion 58 is referred to as a male portion that is in mating engagement with thesecond portion 60 that is referred to as a female portion for receiving thefirst portion 58. This arrangement provides a telescoping engagement between thefirst portion 58 and thesecond portion 60. - The
cross-fire tube 40 includes anouter surface 62 and an inner surface 64, with the inner surface 64 defining aninterior region 68 that provides the fluid coupling of thecombustor chamber 18 and theadjacent combustor chamber 34, which allows passage of a flame from thecombustor chamber 18 to theadjacent combustor chamber 34, or vice versa. Such passage is desirable during light-off of the combustor assemblies of thegas turbine engine 10 and allows for nearly simultaneous ignition or re-ignition of the combustor assemblies. - Disposed along the
outer surface 62 is aspring 70 that extends from proximate thefirst end region 44 of thecross-fire tube 40 to proximate thesecond end region 50 of thecross-fire tube 40. Thespring 70 is at least partially retained by anouter shield 72 that surrounds theouter surface 62 of thecross-fire tube 40. Theouter shield 72 is spaced radially outwardly from theouter surface 62 to accommodate disposal of thespring 70 between thecross-fire tube 40 and theouter shield 72. In the illustrated embodiment, theouter shield 72 is segmented to only surround portions of thecross-fire tube 40 and thespring 70. Specifically, theouter shield 72 surrounds a portion of thefirst portion 58 and a portion of thesecond portion 60 of thecross-fire tube 40. However, it is to be understood that theouter shield 72 may extend along an entire, or nearly an entire, length of thecross-fire tube 40. Irrespective of the amount of thecross-fire tube 40 that is surrounded by theouter shield 72, thespring 70 provides a resilient spring biasing force on thefirst portion 58 and thesecond portion 60 of thecross-fire tube 40. Thecross-fire tube 40 is telescopingly moveable between a first extended position, as shown, and a second compressed position upon compression of thespring 70. As will be described in detail below, compression of thecross-fire tube 40 and thespring 70 is advantageous during certain phases of assembly of thecombustor assembly 14 and theadjacent combustor assembly 32. - Referring now to
FIGS. 3-5 , in conjunction withFIG. 2 , thecross-fire tube arrangement 42 includes afirst collar 80 fixedly secured to a component of thecombustor assembly 14, such as thecombustor liner 46, thesleeve 48 that surrounds thecombustor liner 46, and/or theair shield 49. Similarly, asecond collar 82 is fixedly secured to a component of theadjacent combustor assembly 32. Thefirst collar 80 and thesecond collar 82 may be welded to the component and is configured to engage thefirst end region 44 of thecross-fire tube 40 and thesecond end region 50 of thecross-fire tube 40, respectively. Similar reference numerals will be employed in describing thefirst collar 80 and thesecond collar 82, as both are similarly configured and perform similar functions. - Both the
first collar 80 and thesecond collar 82 include acentral opening 84 for receiving thefirst end region 44 and thesecond end region 50, respectively, of thecross-fire tube 40. Thefirst end region 44 and thesecond end region 50 include ananti-rotation surface 86 that corresponds to at least oneanti-rotation component 88 of thefirst collar 80 and thesecond collar 82. In an exemplary embodiment, the at least oneanti-rotation component 88 and theanti-rotation surface 86 comprise corresponding non-planar surfaces each having conical regions. It is to be appreciated that numerous alternative geometries may be employed and furthermore it is contemplated that corresponding protrusions and recesses may be utilized to form theanti-rotation surface 86 and the at least oneanti-rotation component 88. Irrespective of the precise configuration of theanti-rotation surface 86 and the at least oneanti-rotation component 88, the corresponding features provide a self-aligning aspect for thecross-fire tube arrangement 42. Specifically, disposal of thecross-fire tube 40 into an abutting manner with thefirst collar 80 and thesecond collar 82 provides a fixed rotational position of thecross-fire tube 40, thereby reducing judgment of an installation operator. - During operation of the
combustor assembly 14 and theadjacent combustor assembly 32, thefirst end region 44 and thesecond end region 50 are particularly susceptible to high temperatures due to exposure to thecombustor chamber 18 and theadjacent combustor chamber 34. A plurality of cooling holes 90 are formed in thefirst collar 80 and thesecond collar 82 in a region adjacent thefirst end region 44 and thesecond end region 50 for cooling purposes. It is noted that thefirst end region 44 and thesecond end region 50 are formed of smooth contours, such as circular, elliptical or the like. These smooth contours reduce any disturbance of an airflow passing through an annulus between thecombustor liner 46 and thesleeve 48 and/or theair shield 49. - Referring now to
FIGS. 6-9 , various installation procedures of thecross-fire tube arrangement 42 are illustrated. As described above, thefirst end region 44 of thefirst portion 58 or thesecond end region 50 of thesecond portion 60 of thecross-fire tube 40 may be inserted into thecentral opening 84 of thefirst collar 80 or thesecond collar 82, respectively (FIG. 6 ). Upon contact between theanti-rotation surface 86 and the at least oneanti-rotation component 88, thecross-fire tube 40 is self-aligned into a fixed rotational position. In the illustrated embodiment, thesecond portion 60 is shown in engagement with thesecond collar 82. Thefirst portion 58 is engaged with thesecond portion 60, with thespring 70 sandwiched between thecross-fire tube 40 and theouter shield 72, as well as between thefirst end region 44 and thesecond end region 50. Engagement between thefirst portion 58 and thesecond portion 60 may take place before or after disposal of thesecond portion 60 with thesecond collar 82. Similarly, it is to be appreciated that thefirst portion 58 may be engaged with thefirst collar 80 prior to engagement with thesecond portion 60. As shown inFIG. 7 , a threadedrod 98 may be engaged with either or both of thefirst portion 58 and thesecond portion 60 and extends through an aperture of thecombustor assembly 14 or theadjacent combustor assembly 32 to receive a mechanical fastener 92 (FIG. 8 ), such as a washer and nut arrangement, for example. Such an arrangement assists in securing thecross-fire tube 40 in a fixed position. - To provide clearance for portions of the
combustor assembly 14, such as a module that is inserted into thecombustor assembly 14, thecross-fire tube 40 is moveable between a first position 94, as shown inFIG. 2 , and a second position 96 (FIG. 9 ). The second position 96 comprises a compressed condition of thespring 70 and thecross-fire tube 40, such that components of thecombustor assembly 14 may be inserted into the overall combustor structure. The resiliency of thespring 70 leads to extension of thecross-fire tube 40 after the components are sufficiently inserted into thecombustor assembly 14. Large distances of compression of thecross-fire tube 40 are typically required to establish necessary clearance for reliable insertion of thecombustor assembly 14 components. Disposal of thespring 70 along substantially the entire length of thecross-fire tube 40 allows compression of thecross-fire tube 40 to a large degree. - As illustrated in the flow diagram of
FIG. 10 , and with reference toFIGS. 1-9 , a method of assembling acombustor structure 100 is also provided. Thegas turbine engine 10 and thecross-fire tube arrangement 42 have been previously described and specific structural components need not be described in further detail. The method of assembling acombustor structure 100 includes inserting a first portion of a cross-fire tube into a portion of acombustor assembly 102. The first portion of the cross-fire tube is rotated to align an anti-rotation surface of the first portion with a corresponding anti-rotation feature of afirst collar 104. A second portion of the cross-fire tube is matably engaged with thefirst portion 106, with thespring 70 extended from thefirst portion 58 to thesecond portion 60. The cross-fire tube is compressed from a first position to asecond position 108, thereby providing clearance 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 such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to 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.
Claims (20)
1. A super-telescoping cross-fire tube comprising:
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;
an outer shield spaced radially outwardly and surrounding at least a portion of the cross-fire tube; and
a spring extending from proximate the first end region to the second end region and disposed between the cross-fire tube and the outer shield, wherein the cross-fire tube is telescopingly moveable between a first position and a second position.
2. The super-telescoping cross-fire tube of claim 1 , further comprising a first collar operably coupled to a combustor assembly component, the first collar including at least one anti-rotation component for engaging a corresponding anti-rotation surface proximate at least one of the first end region and the second end region of the cross-fire tube.
3. The super-telescoping cross-fire tube of claim 2 , wherein the at least one anti-rotation component comprises a non-planar geometry and the corresponding anti-rotation surface comprises a corresponding non-planar geometry.
4. The super-telescoping cross-fire tube of claim 2 , wherein the first collar is operably coupled to the combustor assembly component proximate the first end region, wherein the first collar comprises a plurality of cooling holes for cooling the first end region.
5. The super-telescoping cross-fire tube of claim 4 , further comprising a second collar operably coupled to an adjacent combustor assembly component proximate the second end region of the cross-fire tube.
6. The super-telescoping cross-fire tube of claim 2 , wherein the at least one anti-rotation component comprises a plurality of conical regions, wherein the corresponding anti-rotation surface comprises a plurality of corresponding conical regions.
7. The super-telescoping cross-fire tube of claim 2 , wherein the first collar is welded to the combustor assembly component.
8. The super-telescoping cross-fire tube of claim 2 , wherein the combustor assembly component comprises at least one of a combustor liner, a sleeve surrounding the combustor liner, and an air shield surrounding the sleeve.
9. A combustor structure for a gas turbine engine comprising:
a combustor assembly and an adjacent combustor assembly, the combustor assembly comprising a combustor chamber, the adjacent combustor assembly comprising an adjacent combustor chamber;
a first collar operably coupled to the combustor assembly;
a cross-fire tube extending from a first end region disposed adjacent the first collar to a second end region disposed proximate the adjacent combustor assembly; and
a spring extending from proximate the first end region to the second end region and disposed between the cross-fire tube and an outer shield surrounding at least a portion of the cross-fire tube.
10. The combustor structure of claim 9 , wherein the cross-fire tube comprises a first portion and a second portion in mating engagement, the cross-fire tube telescopingly moveable between a first extended position and a second compressed position.
11. The combustor structure of claim 9 , wherein the first collar comprises at least one anti-rotation component for engaging a corresponding anti-rotation surface proximate the first end region.
12. The combustor structure of claim 11 , wherein the at least one anti-rotation component comprises a non-planar geometry and the corresponding anti-rotation surface comprises a corresponding non-planar geometry.
13. The combustor structure of claim 9 , wherein the first collar comprises a plurality of cooling holes for cooling the first end region.
14. The combustor structure of claim 9 , further comprising a second collar operably coupled to the adjacent combustor assembly proximate the second end region of the cross-fire tube.
15. The combustor structure of claim 11 , wherein the at least one anti-rotation component comprises a plurality of conical regions, wherein the corresponding anti-rotation surface comprises a plurality of corresponding conical regions.
16. The combustor structure of claim 9 , wherein the first collar is welded to the combustor assembly.
17. 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.
18. A method of assembling a combustor structure comprising:
inserting a first portion of a cross-fire tube into a portion of a combustor assembly;
rotating the first portion of the cross-fire tube to align an anti-rotation surface of the first portion with a corresponding anti-rotation feature of a first collar operably coupled to the combustor assembly;
matably engaging a second portion of the cross-fire tube with the first portion, wherein a spring is positioned from the first portion to the second portion; and
compressing the cross-fire tube from a first position to a second position providing clearance for insertion of an adjacent combustor assembly into the combustor structure.
19. The method of claim 18 , further comprising mechanically fastening the first portion to the combustor assembly.
20. The method of claim 18 , further comprising extending the cross-fire tube to the first position subsequent to insertion of the adjacent combustor assembly.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/682,965 US20140137536A1 (en) | 2012-11-21 | 2012-11-21 | Super telescoping cross-fire tube and method of assembling a combustor structure |
JP2013237659A JP2014102067A (en) | 2012-11-21 | 2013-11-18 | Adjustable telescoping cross-fire tube and method of assembling combustor structure |
DE201310112879 DE102013112879A1 (en) | 2012-11-21 | 2013-11-21 | Super telescopic transverse ignition tube and method for assembling a combustion chamber assembly |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/682,965 US20140137536A1 (en) | 2012-11-21 | 2012-11-21 | Super telescoping cross-fire tube and method of assembling a combustor structure |
Publications (1)
Publication Number | Publication Date |
---|---|
US20140137536A1 true US20140137536A1 (en) | 2014-05-22 |
Family
ID=50625744
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/682,965 Abandoned US20140137536A1 (en) | 2012-11-21 | 2012-11-21 | Super telescoping cross-fire tube and method of assembling a combustor structure |
Country Status (3)
Country | Link |
---|---|
US (1) | US20140137536A1 (en) |
JP (1) | JP2014102067A (en) |
DE (1) | DE102013112879A1 (en) |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140123619A1 (en) * | 2012-11-08 | 2014-05-08 | General Electric Company | Combustor assembly |
US20140144122A1 (en) * | 2012-11-29 | 2014-05-29 | General Electric Company | Crossfire tube assembly between adjacent combustors |
EP2955447A1 (en) * | 2014-06-13 | 2015-12-16 | Rolls-Royce Corporation | Combustor with spring-loaded crossover tubes |
WO2016036377A1 (en) * | 2014-09-05 | 2016-03-10 | Siemens Aktiengesellschaft | Cross ignition flame duct |
US20160298853A1 (en) * | 2015-04-09 | 2016-10-13 | Siemens Energy, Inc. | Service-friendly cross flame tube with twist lock attachment for can-annular gas turbines |
CN107866773A (en) * | 2016-09-28 | 2018-04-03 | 通用电气公司 | Connect the suite of tools and method of flame tube component in gas-turbine unit for disconnecting |
EP3306198A1 (en) * | 2016-10-10 | 2018-04-11 | General Electric Company | Tool for decoupling cross-fire tube assemblies in gas turbine engines |
US10156363B2 (en) | 2016-07-20 | 2018-12-18 | General Electric Company | Compact multi-piece spring-loaded crossfire tube |
EP3751201A1 (en) * | 2019-06-13 | 2020-12-16 | General Electric Company | Cross fire tube installation/removal methods and apparatus |
US11067282B2 (en) * | 2018-09-11 | 2021-07-20 | Doosan Heavy Industries & Construction Co., Ltd. | Crossfire tube, combustor including the same, and gas turbine including the same |
Citations (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2406234A (en) * | 1946-08-20 | Expansion joint | ||
US2437385A (en) * | 1941-11-21 | 1948-03-09 | Dehavilland Aircraft | Jet propulsion plant |
US2679136A (en) * | 1950-10-21 | 1954-05-25 | Gen Motors Corp | Combustion chamber with crossover tubes |
US2722803A (en) * | 1951-05-23 | 1955-11-08 | Gen Electric | Cooling means for combustion chamber cross ignition tubes |
US2818704A (en) * | 1952-10-30 | 1958-01-07 | Gen Motors Corp | Turbine engine starting system |
US2832195A (en) * | 1956-04-16 | 1958-04-29 | Gen Electric | Cross-ignition tube assembly for gas turbine combustion system |
US3344601A (en) * | 1966-01-18 | 1967-10-03 | United Aircraft Corp | Interconnection for flametubes |
US3650106A (en) * | 1968-10-18 | 1972-03-21 | Bennes Marrel Sa | Combustion chamber for gas turbine |
US3991560A (en) * | 1975-01-29 | 1976-11-16 | Westinghouse Electric Corporation | Flexible interconnection for combustors |
US4249372A (en) * | 1979-07-16 | 1981-02-10 | General Electric Company | Cross-ignition assembly for combustion apparatus |
US5402635A (en) * | 1993-09-09 | 1995-04-04 | Westinghouse Electric Corporation | Gas turbine combustor with cooling cross-flame tube connector |
US5407237A (en) * | 1993-02-26 | 1995-04-18 | The United States Of America As Represented By The Secretary Of The Air Force | Flexible coupling |
US5603531A (en) * | 1994-12-06 | 1997-02-18 | United Technologies Corporation | Blind assembly-swivel crossover tube |
US5964250A (en) * | 1997-12-01 | 1999-10-12 | General Electric Company | Low leakage, articulating fluid transfer tube |
US6606865B2 (en) * | 2001-10-31 | 2003-08-19 | General Electric Company | Bellows type outer crossfire tube |
US6834491B2 (en) * | 2000-06-02 | 2004-12-28 | Nuovo Pignone Holding S.P.A. | Flame-passage device for non-annular gas turbine combustion chambers |
US6912838B2 (en) * | 2003-03-06 | 2005-07-05 | Power Systems Mfg, Llc | Coated crossfire tube assembly |
US7712302B2 (en) * | 2006-01-05 | 2010-05-11 | General Electric Company | Crossfire tube assembly for gas turbines |
US20140123619A1 (en) * | 2012-11-08 | 2014-05-08 | General Electric Company | Combustor assembly |
US20140144122A1 (en) * | 2012-11-29 | 2014-05-29 | General Electric Company | Crossfire tube assembly between adjacent combustors |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5439710Y2 (en) * | 1973-12-24 | 1979-11-24 | ||
JPS6321418A (en) * | 1986-07-15 | 1988-01-29 | Hitachi Ltd | Flame propagation tube system for gas turbine burner |
JPH066881U (en) * | 1991-01-30 | 1994-01-28 | 株式会社スイケンテクノロジー | Temporary fixing structure of joint pipe in expansion joint |
JPH1114056A (en) * | 1997-06-23 | 1999-01-22 | Hitachi Ltd | Gas turbine combustor |
-
2012
- 2012-11-21 US US13/682,965 patent/US20140137536A1/en not_active Abandoned
-
2013
- 2013-11-18 JP JP2013237659A patent/JP2014102067A/en active Pending
- 2013-11-21 DE DE201310112879 patent/DE102013112879A1/en not_active Withdrawn
Patent Citations (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2406234A (en) * | 1946-08-20 | Expansion joint | ||
US2437385A (en) * | 1941-11-21 | 1948-03-09 | Dehavilland Aircraft | Jet propulsion plant |
US2679136A (en) * | 1950-10-21 | 1954-05-25 | Gen Motors Corp | Combustion chamber with crossover tubes |
US2722803A (en) * | 1951-05-23 | 1955-11-08 | Gen Electric | Cooling means for combustion chamber cross ignition tubes |
US2818704A (en) * | 1952-10-30 | 1958-01-07 | Gen Motors Corp | Turbine engine starting system |
US2832195A (en) * | 1956-04-16 | 1958-04-29 | Gen Electric | Cross-ignition tube assembly for gas turbine combustion system |
US3344601A (en) * | 1966-01-18 | 1967-10-03 | United Aircraft Corp | Interconnection for flametubes |
US3650106A (en) * | 1968-10-18 | 1972-03-21 | Bennes Marrel Sa | Combustion chamber for gas turbine |
US3991560A (en) * | 1975-01-29 | 1976-11-16 | Westinghouse Electric Corporation | Flexible interconnection for combustors |
US4249372A (en) * | 1979-07-16 | 1981-02-10 | General Electric Company | Cross-ignition assembly for combustion apparatus |
US5407237A (en) * | 1993-02-26 | 1995-04-18 | The United States Of America As Represented By The Secretary Of The Air Force | Flexible coupling |
US5402635A (en) * | 1993-09-09 | 1995-04-04 | Westinghouse Electric Corporation | Gas turbine combustor with cooling cross-flame tube connector |
US5603531A (en) * | 1994-12-06 | 1997-02-18 | United Technologies Corporation | Blind assembly-swivel crossover tube |
US5964250A (en) * | 1997-12-01 | 1999-10-12 | General Electric Company | Low leakage, articulating fluid transfer tube |
US6834491B2 (en) * | 2000-06-02 | 2004-12-28 | Nuovo Pignone Holding S.P.A. | Flame-passage device for non-annular gas turbine combustion chambers |
US6606865B2 (en) * | 2001-10-31 | 2003-08-19 | General Electric Company | Bellows type outer crossfire tube |
US6912838B2 (en) * | 2003-03-06 | 2005-07-05 | Power Systems Mfg, Llc | Coated crossfire tube assembly |
US7712302B2 (en) * | 2006-01-05 | 2010-05-11 | General Electric Company | Crossfire tube assembly for gas turbines |
US20140123619A1 (en) * | 2012-11-08 | 2014-05-08 | General Electric Company | Combustor assembly |
US20140144122A1 (en) * | 2012-11-29 | 2014-05-29 | General Electric Company | Crossfire tube assembly between adjacent combustors |
Cited By (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140123619A1 (en) * | 2012-11-08 | 2014-05-08 | General Electric Company | Combustor assembly |
US9335052B2 (en) * | 2012-11-08 | 2016-05-10 | General Electric Company | Cross-fire tube mounting assembly for a gas turbine engine combustor |
US20140144122A1 (en) * | 2012-11-29 | 2014-05-29 | General Electric Company | Crossfire tube assembly between adjacent combustors |
US9353952B2 (en) * | 2012-11-29 | 2016-05-31 | General Electric Company | Crossfire tube assembly with tube bias between adjacent combustors |
US10161635B2 (en) * | 2014-06-13 | 2018-12-25 | Rolls-Royce Corporation | Combustor with spring-loaded crossover tubes |
EP2955447A1 (en) * | 2014-06-13 | 2015-12-16 | Rolls-Royce Corporation | Combustor with spring-loaded crossover tubes |
US20160010868A1 (en) * | 2014-06-13 | 2016-01-14 | Rolls-Royce Corporation | Combustor with spring-loaded crossover tubes |
WO2016036377A1 (en) * | 2014-09-05 | 2016-03-10 | Siemens Aktiengesellschaft | Cross ignition flame duct |
US10533750B2 (en) | 2014-09-05 | 2020-01-14 | Siemens Aktiengesellschaft | Cross ignition flame duct |
US20160298853A1 (en) * | 2015-04-09 | 2016-10-13 | Siemens Energy, Inc. | Service-friendly cross flame tube with twist lock attachment for can-annular gas turbines |
US10156363B2 (en) | 2016-07-20 | 2018-12-18 | General Electric Company | Compact multi-piece spring-loaded crossfire tube |
CN107866773A (en) * | 2016-09-28 | 2018-04-03 | 通用电气公司 | Connect the suite of tools and method of flame tube component in gas-turbine unit for disconnecting |
EP3312403A3 (en) * | 2016-09-28 | 2018-06-06 | General Electric Company | Tool kit and method for decoupling cross-fire tube assemblies in gas turbine engines |
US10837644B2 (en) | 2016-09-28 | 2020-11-17 | General Electric Company | Tool kit and method for decoupling cross-fire tube assemblies in gas turbine engines |
EP3306198A1 (en) * | 2016-10-10 | 2018-04-11 | General Electric Company | Tool for decoupling cross-fire tube assemblies in gas turbine engines |
US10247421B2 (en) | 2016-10-10 | 2019-04-02 | General Electric Company | Tool and method for decoupling cross-fire tube assemblies in gas turbine engines |
US11067282B2 (en) * | 2018-09-11 | 2021-07-20 | Doosan Heavy Industries & Construction Co., Ltd. | Crossfire tube, combustor including the same, and gas turbine including the same |
EP3751201A1 (en) * | 2019-06-13 | 2020-12-16 | General Electric Company | Cross fire tube installation/removal methods and apparatus |
Also Published As
Publication number | Publication date |
---|---|
JP2014102067A (en) | 2014-06-05 |
DE102013112879A1 (en) | 2014-05-22 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US20140137536A1 (en) | Super telescoping cross-fire tube and method of assembling a combustor structure | |
US8104290B2 (en) | Combustion liner damper | |
US8448444B2 (en) | Method and apparatus for mounting transition piece in combustor | |
US9322556B2 (en) | Flow sleeve assembly for a combustion module of a gas turbine combustor | |
US9400114B2 (en) | Combustor support assembly for mounting a combustion module of a gas turbine | |
US8549861B2 (en) | Method and apparatus to enhance transition duct cooling in a gas turbine engine | |
US8177495B2 (en) | Method and apparatus for turbine interstage seal ring | |
US9631812B2 (en) | Support frame and method for assembly of a combustion module of a gas turbine | |
US9273868B2 (en) | System for supporting bundled tube segments within a combustor | |
CN108006696B (en) | Burner assembly and burner | |
US8033113B2 (en) | Fuel injection system for a gas turbine engine | |
US10041415B2 (en) | Burner seal for gas-turbine combustion chamber head and heat shield | |
EP3312510A1 (en) | Combustor assembly with air shield for a radial fuel injector | |
JP2013170814A (en) | Combustion liner guide stopper and method for assembling combustor | |
EP2660523B1 (en) | System and method for assembling an end cover of a combustor | |
CN107917443B (en) | Tool and method for separating cross-fire tube assembly in gas turbine engine | |
US9423136B2 (en) | Bundled tube fuel injector aft plate retention | |
US10156363B2 (en) | Compact multi-piece spring-loaded crossfire tube | |
US20080053096A1 (en) | Fuel injection system and method of assembly | |
EP2543824B1 (en) | Support assembly for a turbine system and corresponding turbine system | |
US20180087776A1 (en) | Mounting assembly for gas turbine engine fluid conduit | |
US20130333389A1 (en) | Cross fire tube retention system for a gas turbine engine | |
US9416679B2 (en) | Borescope assembly and method of installing borescope plugs | |
US11732609B2 (en) | Connecting arrangement between components of an aircraft engine | |
US20120304655A1 (en) | Turbomachine combustor assembly including a liner stop |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:CLONINGER, JOEL RUSSELL;MELTON, PATRICK BENEDICT;STOIA, LUCAS JOHN;AND OTHERS;REEL/FRAME:029335/0516 Effective date: 20121119 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |