瑞士专利CH709578B1 Combustion chamber for a gas turbine, with a fuel supply system.

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专利摘要:
The invention relates to a combustion chamber for a gas turbine. A fuel delivery system includes a fuel tube (130) and a mounting assembly. The fuel tube (130) extends from a downstream injector (84) (e.g., a late lean injection injector) to a mounting ring (92) of the combustor (50) and is movably attached to the mounting ring (92) using the mounting assembly. Accordingly, the exemplary fuel supply system may supply fuel to the downstream injector (84) while simultaneously accommodating thermal expansion or contraction of the fuel tube (130) along an axial direction of the combustor (50).
公开号:CH709578B1
申请号:CH00514/15
申请日:2015-04-14
公开日:2019-02-15
发明作者:Joseph Rohrssen Robert；William Cihlar David；Benedict Melton Patrick；John Stoia Lucas
申请人:Gen Electric；
IPC主号:

专利说明:

description
Field of the Invention The present disclosure relates generally to a combustor for a gas turbine, or more particularly to a fuel delivery system for a downstream injector in a combustor for a gas turbine.
Background of the Invention Turbines are widely used in industrial and commercial operations. A combustion section of a gas turbine generally contains a plurality of combustors arranged in an annular arrangement around an outer casing, e.g. a compressor outlet housing is arranged. Pressurized air flows from a compressor to the compressor outlet housing and is directed to each combustion chamber. In each combustor, fuel is mixed with the compressed air from a fuel nozzle to form a combustible mixture within a primary combustion zone of the combustor. The combustible mixture is burned to produce hot combustion gases at high pressure and high speed.
In a typical combustor, the combustion gases are directed to an inlet of a turbine of the gas turbine through a hot gas path that is at least partially defined by an annular combustor liner and an annular transition duct that extends downstream from the combustor liner and at the inlet to the turbine ends. Thermal and kinetic energy are transferred from the combustion gases to the turbine to cause the turbine to rotate and thereby perform mechanical work. For example, the turbine may be connected to a shaft that drives a generator to generate electricity.
In certain combustors, a downstream combustion module is used to inject a substantially lean fuel / air mixture into the hot gas path downstream of the primary combustion zone. The combustion module generally includes an annular fuel rail and fuel injector assembly. The fuel rail circumferentially surrounds a portion of a cap assembly that partially surrounds the fuel nozzle. The annular fuel manifold can support the combustion chamber on the combustion chamber ejection housing, thereby creating a high pressure plenum that surrounds at least a portion of the respective combustion chamber. In addition, the annular fuel distributor contains a plurality of fuel outlets on the rear side in the high-pressure plenum.
The fuel injection assembly of the downstream combustion module includes a plurality of radially extending fuel injectors, also known as late lean fuel injection injectors, which inject the combustible lean fuel / air mixture into the hot gas path downstream of the primary combustion zone. As a result of the late lean fuel injection, the combustion gas temperature is increased and the thermodynamic efficiency of the combustion chamber is improved without a corresponding increase in the generation of undesirable emissions, e.g. of nitrogen oxides (ΝΟχ).
The downstream combustor module also includes fuel lines that extend from the late lean fuel injectors to the fuel outlets in the annular fuel rail. Due to deviations in the thermal conditions during the operation of the gas turbine, the fuel lines can expand or contract. Accordingly, existing fuel lines may generally include multiple segments and corresponding connection points behind the fuel rail in the high pressure plenum to accommodate expansion and contraction. However, there may be certain problems with such a structure. The segmented structure can increase complexity, for example, during the installation of the fuel lines. In addition, the fuel connections can offer a possibility for fuel leakage in the connections behind the fuel distributor. Accordingly, a fuel delivery system would be advantageous that could deliver fuel to the late lean fuel injectors without requiring segmentation of the fuel lines.
Brief Description of the Invention Aspects and advantages of the invention will be set forth in the description below, or may be obvious from the description, or may be learned by practice of the invention.
According to the invention, a combustion chamber for a gas turbine is created, the combustion chamber defining an axial direction and containing a mounting ring for fastening the combustion chamber to a housing of the gas turbine. The combustion chamber also contains an injection device, which is arranged for injecting a fuel into a hot gas path of the combustion chamber behind the mounting ring along the axial direction. The combustor also includes a fuel tube that extends from the injector toward the mounting ring and a mounting assembly. The fuel pipe is movably attached to the mounting ring using the mounting arrangement to accommodate thermal expansion and contraction of the fuel pipe along the axial direction.
CH 709 578 B1 In the aforementioned combustion chamber, the mounting ring may define a through hole that extends substantially along the axial direction through the mounting ring, wherein the fuel tube may extend continuously from the injector to the through hole through the Mounting ring is defined.
In addition, the fuel tube may extend continuously from the injector through the through hole defined by the mounting ring.
In the combustion chamber of any of the types mentioned above, the mounting arrangement may include a bellows assembly that is attached to the fuel tube and that is attached to the mounting ring, the bellows assembly defining a variable length along the axial direction.
In addition, the bellows assembly may be attached to the fuel tube at a second end using a pipe fitting.
In an alternative or further additionally, the fastening arrangement can further comprise a fuel pipe flange, wherein the bellows arrangement can be fastened to the mounting ring at a first end using the fuel pipe flange.
Still further, the mounting ring may define a through hole that extends substantially along the axial direction through the mounting ring, wherein the fuel tube flange may extend through the through hole defined by the mounting ring.
In the combustion chamber of any type mentioned above, the mounting ring may be attached to or integrally formed with a front housing of the combustion chamber.
In a combustion chamber configuration of any of the aforementioned types, the mounting assembly may include a slide seal located adjacent a through hole defined by the mounting ring, the fuel tube being movably attached to the mounting ring using the sliding seal.
[0017] In addition, the sliding seal can be a lip seal.
In an alternative or further in addition, the fuel tube may extend continuously from the injector and through the sliding seal.
In a combustor configuration of any of the aforementioned types, the mounting ring can support the combustor on a compressor outlet housing of the gas turbine.
The combustor of any type mentioned above may include a combustor liner, the injector being a late lean mixture injection injector that extends at least partially through the combustor liner.
[0021] In a further invention, a gas turbine is created. The gas turbine has a compressor section, a combustion chamber arrangement in connection with the compressor section and a turbine section in connection with the combustion chamber arrangement. The combustion chamber arrangement contains a combustion chamber, the combustion chamber defining an axial direction and containing a mounting ring for mounting the combustion chamber on a housing of the gas turbine. The combustor also includes an injector that is arranged for injecting fuel into a hot gas path of the combustor behind the mounting ring along the axial direction. The combustor also includes a fuel tube that extends continuously from the injector toward the mounting ring and a mounting assembly. The fuel tube is movably attached to the mounting ring using the mounting arrangement to accommodate thermal expansion or contraction of the fuel tube along the axial direction.
In the aforementioned gas turbine, the mounting ring may define a through hole that extends substantially along the axial direction through the mounting ring, wherein the fuel pipe may extend continuously from the injector toward the through hole defined by the mounting ring is.
In addition, the fuel pipe may extend continuously from the injector through the through hole defined by the mounting ring.
In the gas turbine of any type mentioned above, the mounting arrangement may have a bellows assembly that is attached to the fuel pipe and the mounting ring, the bellows assembly defining a variable length along the axial direction.
In addition, the fastening arrangement can further comprise a fuel pipe flange, wherein the bellows arrangement can be fastened to the mounting ring by the fuel pipe flange.
In the gas turbine of any type mentioned above, the mounting ring may be attached to or integrally formed with a front housing of the combustion chamber.
Additionally or as an alternative, the mounting arrangement may include a slide seal located adjacent a through hole defined by the mounting ring, the fuel tube being slidably attached to the mounting ring using the sliding seal, the fuel tube continuously extending from the Injector can extend from and through the sliding seal.
CH 709 578 B1 [0028] These and other features, aspects and advantages of the present disclosure will be better understood with reference to the following description and the appended claims. The accompanying drawings, which are incorporated in and constitute a part of this disclosure, illustrate embodiments of the disclosure and, together with the description, serve to explain the principles of the disclosure.
Brief Description of the Drawings A complete and feasible disclosure of the present invention, including its best mode, which is directed to a person skilled in the art is given in particular in the rest of the description, which makes reference to the attached figures, in which shows:
1 shows a functional block diagram of a gas turbine according to an exemplary embodiment of the present invention;
2 is a cross-sectional side view of a portion of an exemplary gas turbine that includes a combustor according to an exemplary embodiment of the present invention;
3 is an exploded perspective view of a fuel delivery system according to an exemplary embodiment of the present disclosure;
4 is a side view of the exemplary fuel delivery system of FIG. 3;
5 is a sectional side view of a portion of the exemplary fuel delivery system of FIG. 3;
6 is a cross-sectional side view of the example fuel delivery system of FIG. 3 installed in a combustor of a gas turbine in accordance with an example embodiment of the present disclosure;
7 is an exploded perspective view of a fuel delivery system according to another exemplary embodiment of the present disclosure; and
8 is a cross-sectional view of the example fuel delivery system of FIG. 7 installed in a combustor of a gas turbine in accordance with an example embodiment of the present disclosure.
Detailed Description of the Invention Reference will now be made in detail to present embodiments of the invention, one or more examples of which are illustrated in the drawings. The detailed description uses numerals and letters to refer to features in the drawings. Same or similar designations in the drawings and in the description are used to refer to the same or similar parts of the invention. As used herein, the terms "first ...", "second ...", and "third ..." can be used interchangeably to distinguish one component from another, and are not intended to indicate the location or meaning of the individual Show components. The terms "upstream" and "downstream" refer to the relative direction with respect to fluid flow in a fluid flow path. For example, "upstream" refers to the direction from which the fluid flows and "downstream" refers to the direction in which the fluid flows. Similarly, "front" generally refers to an upstream direction in the gas turbine or an upstream section of the gas turbine, while "rear" generally refers to a downstream direction in the gas turbine or a downstream section of the gas turbine. In addition, the term "radial" refers to the relative direction that is substantially perpendicular to an axial centerline of a particular component, and the term "axial" refers to the relative direction that is substantially parallel to an axial centerline of a particular component Component runs.
Each example is given in the context of an explanation of the invention and not a limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For example, features shown or described as part of one embodiment can be used in another embodiment to provide yet another embodiment of the invention. Thus, the present invention is intended to embrace such modifications and variations insofar as they come within the scope of the appended claims and their equivalents. Although exemplary embodiments of the present invention are described for purposes of illustration generally in the context of a combustor contained in a gas turbine, it should be readily apparent from the teachings contained herein that embodiments of the present invention can be applied to any combustor operating in a Any turbomachine can be included, and are not limited to a combustion chamber of a gas turbine, unless it is specifically stated in the claims.
CH 709 578 B1 [0032] Certain exemplary embodiments of the present disclosure include a fuel delivery system for a gas turbine combustor. The exemplary fuel delivery system includes a fuel pipe and mounting assembly. The fuel tube extends from a downstream injector (e.g., a late lean mixture injector) toward a mounting ring of the combustion chamber and is movably attached to the mounting ring using the mounting assembly. Accordingly, the exemplary fuel delivery system may deliver fuel to a downstream injector while simultaneously absorbing thermal expansion or contraction of the fuel tube along an axial direction of the combustion chamber.
Referring to the drawings, wherein like reference numerals designate like parts throughout the figures, FIG. 1 shows a functional block diagram of an exemplary gas turbine 10 that may include various embodiments of the present invention. As illustrated, gas turbine 10 generally includes an inlet portion 12, which may include a series of filters, cooling coils, liquid separators, and / or other devices to purify and other working fluid (eg, air) 14 entering gas turbine 10 Way to process. The working fluid 14 flows to a compressor section in which a compressor 16 increasingly provides kinetic energy to the working fluid to produce a compressed working fluid 18 in a high energy state.
The compressed working fluid 18 is mixed with a fuel 20 from a fuel supply 22 to form a combustible mixture in one or more combustion chambers 50 within a combustion chamber arrangement 24. The combustible mixture is burned to produce combustion gases 26 that are high in temperature and pressure. The combustion gases 26 flow through a turbine section 28 of a turbine section to perform work. For example, the turbine 28 may be connected to a shaft 30 such that rotation of the turbine drives the compressor 16 to generate the compressed working fluid 18. Alternatively or additionally, the shaft 30 can connect the turbine 28 to a generator 32 for generating electricity. Exhaust gases 34 from the turbine 28 flow through an exhaust gas section 36, which connects the turbine 28 to an exhaust duct 38 downstream of the turbine 28. For example, the exhaust section 36 may include a heat recovery steam generator (not shown) for cleaning and extracting additional heat from the exhaust gases 34 before they are released to the environment.
Referring to FIG. 2, a sectional side view of a portion of an exemplary gas turbine 10 with an exemplary combustor 50 is shown. As shown, the combustion chamber 50 is at least partially from an outer housing 52, e.g. a compressor outlet housing 54, which is arranged downstream of the compressor 16. The outer housing 52 is in fluid communication with the compressor 16 and at least partially defines a high-pressure plenum 58 that surrounds at least a portion of the combustion chamber 50. An end cover 60 is connected to a front housing 56 of the combustion chamber 50 at a front end 61 of the combustion chamber 50.
2, the combustion chamber 50 generally includes at least one fuel nozzle 62 that is located downstream of the end cover 60 and that extends along an axial direction A of the combustion chamber 50 (see FIG. 6). An annular cap assembly 64 is also included that extends radially and axially within the outer housing 52 downstream of the end cover 60. In addition, an annular hot gas path channel or combustor tube 66 extends downstream from the cap assembly 64 and an annular flow sleeve 68 surrounds at least a portion of the combustor tube 66. The combustor tube 66 defines a hot gas path 70 for directing the combustion gases 26 through the combustion chamber 50 and in the direction of the Turbine 28 (see Fig. 1).
The example combustor 50 further includes a main fuel flange 90 to deliver the fuel 20 from the fuel source 22 (see FIG. 1) to the one or more axially extending nozzle (s) 62. The axially extending fuel nozzle (s) 62 extends at least partially through the cap assembly 64 to provide a first combustible mixture primarily composed of the fuel 20 and a portion of compressed working fluid 18 from the compressor 16. to a primary combustion zone 82 defined within the combustor liner 66 downstream of the cap assembly 64.
There is also a mounting ring 92 to attach the combustion chamber 50 to the outer housing 52 of the gas turbine 10. In the exemplary embodiment of FIG. 2, the mounting ring 92 is an annular mounting flange (similar to what is referred to as a "fuel rail" in prior art embodiments) that is on a front of the front housing 56 of the combustion chamber 50 and on the front rear side of the outer housing 52 of the gas turbine 10 is attached. However, it should be appreciated that, in other exemplary embodiments of the present disclosure, mounting ring 92 may be an extension of front housing 56 of combustion chamber 50 or other attachment to front housing 56 of combustion chamber 50, instead or in combination.
2, combustor 50 further includes one or more downstream injectors 84, also known as late lean fuel injectors, located at a location downstream of the axially extending fuel nozzle (s) (n) and located downstream of or behind the mounting ring 92, through the flow sleeve 68 and the combustor liner 66. In such an exemplary embodiment, combustor liner 66 further defines a secondary combustion zone 88 that is proximate fuel injector (s) 84 and downstream of the primary combustion zone
CH 709 578 B1 ne 82. In addition, in the exemplary embodiment of FIG. 2, a secondary fuel flange 94, or a later lean fuel injector flange, is included that is disposed in front of the mounting ring 92 to supply fuel 20 from the fuel source 22 (see FIG. 1). A manifold cover 98 is also provided which is attached to the front housing 56 and which extends at least partially around the secondary fuel flange 94. As described below with reference to FIGS. 3-6, a fuel supply system 100 may be included to supply fuel from the secondary fuel flange 94 through the mounting ring 92 to the downstream injector (s) 84.
However, it should be appreciated that the exemplary combustor 50 and gas turbine 10 as described herein with reference to FIGS. 1 and 2 are described as an example only, and in other exemplary embodiments, any other suitable configuration can have. For example, although in FIG. 2 the combustor liner 66 and the flow sleeve 68 are each shown as separate units, in other embodiments the combustor liner 66 and / or the flow sleeve 68 may instead consist of two or more parts that are joined together in any manner. Additionally, in other exemplary embodiments, combustor 50 and / or gas turbine 10 may be any other suitable configuration of one or more fuel flange (s) 90, one or more secondary fuel flange (s) 94, one or more nozzle (s) 62, one front housing 56, an outer housing 52, etc. included.
3-6, an exemplary fuel delivery system 100 for supplying fuel 20 from the secondary fuel flange 94, in front of the mounting ring 92, to one or more downstream fuel injectors 84, behind the mounting ring 92 is provided. The exemplary fuel delivery system 100 generally includes a fuel tube 130 that extends from the fuel injector 84 toward the mounting ring 92 (see FIG. 6). The fuel pipe 130 is movably attached to the mounting ring 92 using a mounting assembly 101. Such a configuration may allow the exemplary fuel delivery system 100, including the fuel tube 130, to accommodate thermal expansion or contraction along the axial direction A of the combustion chamber 50 during operation of the gas turbine 10.
As shown, the fuel tube 130 extends continuously between a rear end 134 and a front end 132, and is attached to the injector 84 at the rear end 134. The fuel pipe 130 may be attached to the injector 84 at the rear end 134 in any suitable manner. For example, the rear end 134 may be welded directly to the injector 84 or alternatively may be attached using an interconnect. The fuel pipe 130 is movably attached to the mounting ring 92 near the front end 132 using the mounting assembly 101. The exemplary fastener assembly 101 of FIGS. 3-6 generally includes a rear pipe fitting 128, a bellows assembly 116, a flange 104, and a front pipe fitting 102. The front end 132 of the fuel pipe 130 extends through the rear pipe fitting 128, through the bellows assembly 116 through and through the flange 104.
The bellows assembly 116 defines a first end 118 and a second end 120, which correspond to a front end and a rear end, respectively, in the exemplary embodiment of Figs. 3-6. The bellows assembly 116 is attached to the fuel pipe 130 at the second end 120 using the rear pipe fitting 128. The exemplary rear pipe fitting 128 from FIGS. 3-6 is attached to the fuel pipe 130 using a non-positive part 129 and a threaded screw connection to the second end 120 of the bellows assembly 116. Similarly, the bellows assembly 116 is attached to the mounting ring 92 at the first end 118 using the flange 104. In particular, the first end 118 of the bellows assembly 116 is attached to the rear end 114 of the flange 104 using a threaded screw connection. The flange 104 in turn contains a plurality of fastening points 108 for fastening the flange 104 to the mounting ring 92. In addition, in the exemplary embodiment in FIGS. 3-6, the flange 104 contains a sealing groove 106 for positioning a suitable sealing element (not shown) between the flange 104 and the mounting ring 92 to further ensure that a proper seal is created between the flange 104 and the mounting ring 92.
It should be appreciated, however, that although the exemplary bellows assembly 116 is shown in FIGS. 3-6 as attached to the flange 104 and the rear pipe fitting 128 using threaded screw connections, in other exemplary embodiments, any other connecting means can be provided. For example, the bellows assembly 116 on the flange 104 and / or on the rear pipe fitting 128 may be permanent (e.g., by welding or by being integral with one another) or releasable (e.g., using a quick connect coupling, a screw connection, a compression fitting connection, a non-positive connection or one In addition, in other exemplary embodiments, any other suitable means may be provided for attaching the pipe fitting 128 to the fuel pipe 130 or for attaching the flange 104 to the mounting ring 92. In other exemplary embodiments, the flange 104 For example, be made integrally with the mounting ring 92.
5, the example bellows assembly 116 additionally defines an axial length L, and includes a plurality of annular compensating elements 122 that are arranged radially between an inner shell 124 and an outer shell 126. The inner jacket 124 defines an internal channel 121 that has a cross-sectional shape along a radial direction R that is complementary to a cross-sectional shape along the radial direction R of the fuel pipe 130. The compensating elements 122 give the bellows arrangement 116
CH 709 578 B1
Flexibility, while the inner sheath 124 and / or the outer sheath 126 enable a substantially uniform cross-sectional shape along the radial direction R. In particular, the bellows assembly 116 allows the axial length L of the assembly 116 to increase and decrease while maintaining connections at the first and second ends 118, 120 and a substantially constant cross-sectional shape along the radial direction R. For example, in some exemplary embodiments, the axial length L of the bellows assembly 116 may be designed to expand or contract from the axial rest length L by more than about 2%, more than about 5%, more than about 7% or more. Alternatively, however, in other exemplary embodiments, the bellows assembly may be designed to expand or contract less than about 2% from an axial rest length L. Accordingly, the axial length L of the bellows assembly 116 is a variable length.
With further reference to FIG. 5, the exemplary flange 104 includes a cylindrical extension 110 that defines an inner channel 111 that corresponds to the shape of the fuel tube 130. The fuel tube 130 can extend into the inner channel of the extension 110, so that the front end 132 of the fuel tube is arranged close to a front end 112 of the cylindrical extension 110 of the flange 104.
In the exemplary embodiment shown, the front end 112 of the cylindrical extension 110 is attached to the front pipe fitting 102 using a threaded screw connection. The front pipe fitting 102 may then be connected to the secondary fuel flange 94 directly or by means of a connecting fuel pipe 95 (see FIG. 6) using a non-positive part 103. The exemplary system 100 is constructed such that there is a gap 113 along the axial direction A between the front end 132 of the fuel pipe 130 and the front pipe fitting 102 to allow the fuel pipe 130 to expand and contract. However, it should be appreciated that in other exemplary embodiments of the present disclosure, flange 104 may completely lack extension 110 and that front pipe fitting 102 may instead be directly attached to fuel pipe 130 in front of flange 104.
With particular reference to the cross-sectional view shown in FIG. 6, an example fuel delivery system 100 is shown installed in an example combustion chamber 50. As described above, the mounting ring 92 is attached to the combustion chamber 50 of the outer casing 52 of the gas turbine 10, thereby creating a seal that enables a high pressure plenum 58 that surrounds at least a portion of the combustion chamber 50. The fuel 20 is supplied to the downstream fuel injector 84 by the fuel delivery system 100 from a secondary fuel flange 94 (see FIG. 2). The fuel delivery system 100 extends through a through hole 96 defined by the mounting ring 92. The through hole 96 extends substantially along the axial direction A through the mounting ring 92. As used herein, "substantially along the axial direction" refers to any direction that extends from a front side of the mounting ring 92 to a rear side of the mounting ring 92, and is not limited to a hole that extends directly from one Extends to the other side.
The secondary fuel flange 94 is in fluid communication with the front end 132 of the fuel tube 130 via the intermediate fuel line 95. As shown, the exemplary fuel tube 130 of FIG. 6 extends continuously from the rear end 134 (which attaches to the injector 84 is) into the through hole 96 of the mounting ring 92. The mounting arrangement 101 movably or more specifically slidably attaches the mounting ring 92 to allow thermal expansion or contraction of the fuel tube 130 along the axial direction A. As described, the mounting assembly 101 includes the bellows assembly 116 which is secured (by means of the flange 104) to the mounting ring 92 at the first end 118 and is arranged in a fixed position with respect thereto. The second end 120 of the bellows assembly 116 is fixed to the fuel pipe 130 and is movable along the axial direction A with respect to the mounting ring 92. Such a structure enables the fuel tube 130 to expand (ie, without connection points) continuously from the injector 84 to the mounting ring 92. In particular, in the exemplary embodiment of FIG. 6, the fuel tube 130 extends continuously from the injector 84 in and the through hole 96 therein Mounting ring 92 in and through this, and it is in fluid communication with the secondary fuel flange 94 in front of the mounting ring 92. The foregoing construction can reduce a risk of fuel leakage outside of the combustion chamber 50, behind the mounting ring 92, by eliminating the need for connection points in the fuel pipe 130 between the injector 84 and the mounting ring 92.
7 and 8, another exemplary embodiment of a fuel delivery system 100 of the present disclosure is provided. Similar to the example system 100 of FIGS. 3-6, the example system 100 of FIGS. 7 and 8 generally includes a fuel tube 130 that extends from the injector 84 (not shown) toward the mounting ring 92 and a mounting assembly 101. The exemplary fastener assembly 101 of FIGS. 7 and 8 includes a cylindrical sleeve 140, a flange 142, and a sliding seal 146. As shown, the cylindrical sleeve 140 extends around the fuel tube 130. The fuel tube 130 and at least a portion of the sleeve 140 extend through the flange 142 and the sliding seal 146 and into the through hole 96 defined by the mounting ring 92. In the exemplary embodiment of FIGS. 7 and 8, the pipe 130 also extends through the through hole 96 and is directly attached to the front pipe fitting 102.
CH 709 578 B1 The flange 142 is attached to a rear side of the mounting ring 92 using a plurality of attachment points 144 and defines an annular sealing groove 150 that is adapted to receive a sealing element (not shown) to provide a seal between the flange 142 and the mounting ring 92 continue to effect. The sliding seal 146 is arranged in a correspondingly shaped groove 148 in the mounting ring 92 and is held in position by the flange 142. The flange 142 also acts to seal the sliding seal 146 against the mounting ring 92. The sliding seal 146 in turn provides a seal with the sleeve 140 and / or the fuel pipe 130, while the fuel pipe 130 is still allowed to move along the axial direction A with respect to the mounting ring 92. The sliding seal 146 may be any seal that is suitable for maintaining a seal with the fuel pipe and / or the sleeve 140 while at the same time allowing movement along the axial direction A. The sliding seal 146 can be a lip seal, for example. Accordingly, the fuel pipe 130 is movably attached to the mounting ring 92 using the mounting assembly 101 and the sliding seal 146. Such a structure may allow the fuel tube 130 to continuously (i.e., without any intermediate attachment points) extend from and through the injector 84 to the mounting ring 92, or more specifically, through the mounting assembly 101 and the sliding seal 146. Accordingly, such a structure can accommodate thermal expansion or contraction of the fuel pipe 130 during operation of the gas turbine 10 while further reducing a risk of fuel leakage outside the combustion chamber 50, behind the mounting ring 92.
As shown in FIGS. 7 and 8, the fuel pipe 130 is attached to the front end 132 by means of an intermediate fuel line 95 on the secondary fuel flange 94 and on the front pipe fitting 102. In addition, in the exemplary embodiment of FIGS. 7 and 8, the mounting ring 92 is an extension of the front housing 56 of the combustion chamber 50.
However, it should be appreciated that the exemplary embodiment of FIGS. 7 and 8 is given as an example only, and that the fastening arrangement 101 may have any other structure in other embodiments. For example, in other embodiments, the mounting assembly 101 need not include the cylindrical sleeve 140, and the sliding seal 146 may instead be slidably attached directly to the fuel tube 130. In addition, in other exemplary embodiments, the mounting ring 92 may define a recess for receiving the flange 142 (or the flange 104) so that the flange 142 (or the flange 104) is created as a counterbore in the mounting ring 92.
This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including the manufacture and use of any device or system, and implementation of any methods included. The patentable scope of the invention is defined by the claims, and may include other examples that those skilled in the art will recognize. Such other examples are intended to fall within the scope of the claims if they include structural elements that do not differ from the precise language of the claims.

权利要求:
Claims (10)
[1]
claims
1. Combustion chamber for a gas turbine, the combustion chamber defining an axial direction and comprising: a mounting ring for mounting the combustion chamber on a housing of the gas turbine;
an injector arranged for injecting a fuel into a hot gas path of the combustion chamber behind the mounting ring along the axial direction;
a fuel tube extending from the injector toward the mounting ring; and a mounting assembly that movably attaches the fuel tube to the mounting ring to accommodate thermal expansion and contraction of the fuel tube along the axial direction.
[2]
2. The combustion chamber of claim 1, wherein the mounting ring defines a through hole that extends substantially along the axial direction through the mounting ring, and wherein the fuel tube extends continuously from the injector to the through hole defined by the mounting ring;
wherein the fuel tube preferably extends continuously from the injector through the through hole defined by the mounting ring.
[3]
3. Combustion chamber according to claim 1 or 2, wherein the fastening arrangement comprises a bellows arrangement which is fastened to the fuel pipe and is fastened to the mounting ring, the bellows arrangement defining a variable length along the axial direction;
wherein the bellows assembly is preferably attached to the fuel tube at a second end using a pipe fitting.
[4]
4. Combustion chamber according to claim 3, wherein the fastening arrangement further comprises a fuel pipe flange and wherein the bellows arrangement is fastened to the mounting ring at a first end using the fuel pipe flange.
[5]
5. With the fuel pipe flange extending through the through hole defined by the mounting ring.
CH 709 578 B1
[6]
6. Combustion chamber according to one of the preceding claims, wherein the mounting ring is attached to a front housing of the combustion chamber or is integrally produced therewith; and / or wherein the mounting ring is designed to hold the combustion chamber on a compressor outlet housing of the gas turbine.
[7]
7. Combustion chamber according to one of the preceding claims, wherein the fastening arrangement has a sliding seal, which is arranged next to one or the through hole, which is defined by the mounting ring, wherein the fuel pipe is movably attached to the mounting ring using the sliding seal.
[8]
8. Combustion chamber according to claim 7, wherein the sliding seal is a lip seal; and / or wherein the fuel pipe extends continuously from the injection device and through the sliding seal.
[9]
9. Combustion chamber according to one of the preceding claims, wherein the combustion chamber has a combustion chamber flame tube and wherein the injection device is an injector for late lean mixture injection, which extends at least partially through the combustion chamber flame tube.
[10]
10. Gas turbine, which has:
a compressor section;
a combustor assembly in communication with the compressor section; and a turbine section in connection with the combustor assembly, the combustor assembly having a combustor, the combustor defining and having an axial direction:
a mounting ring for mounting the combustion chamber on a housing of the gas turbine;
an injector arranged for injecting fuel into a hot gas path of the combustion chamber behind the mounting ring in the axial direction;
a fuel tube extending from the injector toward the mounting ring; and a mounting assembly that movably attaches the fuel tube to the mounting ring to accommodate thermal expansion or contraction of the fuel tube along the axial direction.
CH 709 578 B1
IO

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DE102013114905A1|2014-07-10|Fuel injector for combustion chamber of gas turbine, has annular main body, fluid circuit which is partially extended through main body, and axially extended inner body which extends in inner side of main body

DE102013114903A1|2014-09-04|Combustion arrangement and method for reducing pressure fluctuations of a combustion arrangement

CH702556A2|2011-07-15|Nozzle and method for fuel supply by working with opposite swirl nozzle.

DE102013109553A1|2014-03-13|Compressor fairing segment

DE202017104258U1|2017-10-12|Compact multipart spring-loaded rollover tube

DE112013007627T5|2016-08-18|Fuel nozzle cartridge and method of assembly

DE112015004452T5|2017-07-27|Robust insulated fuel injector for a gas turbine engine

DE102018114521A1|2018-12-20|Dual fuel fuel nozzle with gas and liquid fuel operability

同族专利:

公开号 | 公开日

CH709578A2|2015-10-30|

JP6628493B2|2020-01-08|

CN105042636B|2019-11-05|

US9803555B2|2017-10-31|

CN105042636A|2015-11-11|

JP2015210075A|2015-11-24|

DE102015105578A1|2015-10-29|

US20150308349A1|2015-10-29|

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法律状态:
2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |

优先权:

申请号 | 申请日 | 专利标题

US14/259,443|US9803555B2|2014-04-23|2014-04-23|Fuel delivery system with moveably attached fuel tube|

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