• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A combustor cap assembly (100) includes an annular shell (102) and a baffle (116) joined to the shell (102). The baffle plate (116) at least partially defines a plurality of impingement cooling bores (126) and a cooling flow return passage (128). A cap plate (126) is joined to the baffle plate (116). The cap plate (136) has a bounce side directed toward a second side part of the baffle plate (116), the bounce side being axially spaced from the second side part to define a baffle air space (144) therebetween. The cooling flow return passage (128) is in fluid communication with the impingement air space (144). A fluid conduit extends from a first side portion of the baffle plate (116) to a first end portion (110) of the shell (102). The fluid conduit (148) is in fluid communication with the cooling flow return passage (128) and provides fluid communication from the impingement air space (144).
    公开号:CH710052A2
    申请号:CH01176/15
    申请日:2015-08-14
    公开日:2016-02-29
    发明作者:Lucas John Stoia；Patrick Benedict Melton；Carolyn Ashley Antoniono
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    FIELD OF THE INVENTION
    The present invention generally relates to a burner for a gas turbine. More particularly, the invention relates to a system for cooling a cap plate of a combustion cap assembly disposed in the burner.
    BACKGROUND OF THE INVENTION
    In an air induction turbomachine (e.g., a gas turbine engine), air enters a compressor and is increasingly compressed as it is directed to a combustor. The compressed air is premixed with a fuel and ignited in a combustion chamber defined in the combustion chamber, thereby generating hot combustion gases. The combustion gases are then directed from the combustion chamber via a liner and / or adapter into a turbine section of the turbomachine where the combustion gases flow over alternating rows of vanes and rotor blades secured to a rotor shaft. As the combustion gases flow over the rotor blades, kinetic and / or thermal energy is transferred to the rotor blades, causing the rotor shaft to rotate.
    In order to increase turbine efficiency, modern combustors are operated at high temperatures that produce high thermal loads at various mechanical components located within the combustor. As a result, at least a portion of the compressed air supplied to the combustion chamber is used to cool these components. For example, certain combustors have a generally annular cap assembly that at least partially surrounds one or more fuel nozzles in the combustor. Certain configurations of the cap assembly include a cap plate disposed at a downstream end of the cap assembly. The fuel nozzles extend at least in part through the cap plate, which is typically disposed substantially adjacent to the combustion chamber. As a result, the cap plate is generally exposed to extremely high temperatures.
    One way to cool the cap plate is to direct a portion of the compressed air into the cap assembly and to an upstream side of the cap plate. The compressed air is then passed through numerous cooling holes that pass through the cap plate. This process is known in the industry as effusion cooling. However, the compressed air flowing through the numerous cooling holes is generally not mixed with fuel as it enters the combustion chamber. As a result, too much NOx and / or CO2 can be produced and the overall efficiency of the turbine can be reduced. Therefore, an improved system for cooling the cap plate would be useful.
    BRIEF DESCRIPTION OF THE INVENTION
    Aspects and advantages of the invention will be set forth in the description which follows, or may be learned from the description, or may be learned by practice of the invention.
    One embodiment of the present invention is a combustor cap assembly. The combustor cap assembly includes an annular jacket having a first end portion and a second end portion. A baffle plate is joined to the shell near the second end portion. The baffle plate has a first side part, a second side part and an outer band part. The baffle plate defines at least in part a plurality of impingement cooling bores and a cooling flow return passage. A cap plate is assembled with the baffle plate and includes a bounce side, which is directed to the second side part of the baffle plate. The impact side is axially spaced from the second side part to define an impingement air space between it and this. The cooling flow recirculation passage is in fluid communication with the impingement air space. The combustor cap assembly further includes a fluid conduit in fluid communication with the cooling flow return passage. The fluid line extends from the first side part of the baffle plate to the first end part of the shell.
    In any embodiment of the cap assembly, it may be advantageous for an outlet end of the fluid conduit to be in fluid communication with a cooling air discharge opening.
    [0008] In any embodiment of the cap assembly, it may be advantageous for an inlet to the cooling flow return passage to be defined along the second side portion of the baffle plate, with a portion of the second side portion surrounding the inlet being raised toward the baffle side of the cap plate.
    [0009] In any embodiment of the cap assembly, it may be advantageous for the cap assembly to further include a plurality of cooling passages extending radially in the vicinity of an inlet to the cooling flow return passage radially through the outer band portion of the baffle plate, wherein the cooling passages for fluid communication from the impingement air space ,
    In any embodiment of the cap assembly, it may be advantageous for the baffle plate and the cap plate to at least partially define a fuel nozzle passage that extends axially therethrough.
    In any embodiment of the cap assembly, it may be advantageous for the cap assembly to further include a flange extending radially inwardly from the shell, wherein the fluid conduit extends at least in part through the flange.
    In any embodiment of the cap assembly, it may be advantageous that the shell and the first side part of the baffle plate at least partially define a cooling air space, wherein the plurality of baffles provide a fluid connection between the cooling air space and the baffle air space.
    In any embodiment of the cap assembly, it may be advantageous that the fluid conduit defines a Kühlstromabführungsdurchlass within the cooling air space, which is fluidically isolated from the cooling air space.
    Another embodiment of the present invention is one of the combustion chamber. The combustion chamber has a fuel nozzle axially extending in an outer housing and a Brennkammerkappenanordnung surrounding at least a portion of the fuel nozzle in the circumferential direction. The jacket defines at least in part an annular flow passage within the outer housing. The combustor cap assembly further includes a baffle plate mated with a second end portion of the mantle. The baffle plate has a first side part, a second side part and an outer band part. The baffle plate defines at least in part a plurality of impingement cooling bores and a cooling flow return passage. The shell and the first side portion of the baffle plate at least partially define a cooling air space in fluid communication with the annular flow passage. A cap plate is assembled with the baffle plate and includes a bounce side, which is directed to the second side part of the baffle plate. The impact side is axially spaced from the second side part to define an impingement air space between it and this. The plurality of impingement cooling bores provide fluid communication between the cooling air space and the impingement air space. The cooling flow return passage allows fluid flow out of the impingement air space. A fluid conduit is in fluid communication with the cooling flow return passage. The fluid conduit extends within the cooling air space and is in fluid communication with the annular flow passage.
    In any embodiment of the combustion chamber, it may be advantageous that the fluid line extends within the cooling air space from the first side part of the baffle plate to the first end part of the second jacket.
    In any embodiment of the combustion chamber, it may be advantageous that the fluid line defines a Kühlstromabführungsdurchlass within the cooling air space, which is fluidically isolated from the cooling air space.
    In any embodiment of the combustion chamber, it may be advantageous for an inlet to the cooling flow return passage to be defined along the second side portion of the baffle plate, with a portion of the second side portion surrounding the inlet being raised toward the impact side of the cap plate.
    In any embodiment of the combustion chamber, it may be advantageous that the combustion chamber further includes a plurality of cooling passages extending radially in the vicinity of an inlet to the cooling flow recirculation passage through the outer band portion of the baffle plate, wherein the cooling passages for fluid communication from the impingement air space out ,
    In any embodiment of the combustion chamber, it may be advantageous for the fuel nozzle to pass through a fuel nozzle passage defined at least in part by the baffle plate and the cap plate.
    In any embodiment of the combustion chamber, it may be advantageous that the combustion chamber further comprises a flange which extends radially inwardly from the jacket, wherein the fluid conduit extends at least in part through the flange.
    Another embodiment of the present invention is a gas turbine. The gas turbine includes a compressor section, a combustion section downstream of the compressor section, and a turbine disposed downstream of the combustion section. The combustion section has a combustion chamber that is at least partially surrounded by an outer housing. The combustion chamber has a fuel nozzle that extends axially in the outer housing, and a Brennkammerkappenanordnung that surrounds at least a portion of the fuel nozzle in the circumferential direction. The combustor cap assembly includes an annular jacket having a first end portion and a second end portion. The jacket defines at least in part an annular flow passage within the outer housing. A baffle plate is joined to the shell near the second end portion. The baffle plate has a first side part which is axially spaced from a second side part. The baffle plate defines a plurality of impingement cooling holes and a cooling flow return passage. A cooling air space is at least partially defined by the jacket and the first side part of the baffle plate. A cap plate is joined to the baffle plate and an impingement air space is defined between the second side part of the baffle plate and an impact side of the cap plate. The plurality of impingement cooling bores permit fluid flow into the impingement air space, and the cooling flow recirculation passage allows fluid flow out of the impingement air space. The combustor cap assembly further includes a fluid conduit in fluid communication with the cooling flow return passage. The fluid conduit defines a cooling flow discharge passage within the cooling air space fluidly isolated from the cooling air space.
    In any embodiment of the gas turbine, it may be advantageous for an outlet end of the fluid conduit to be in fluid communication with a cooling air discharge opening, the cooling air discharge opening defining a flow path into the annular flow passage.
    In any embodiment of the gas turbine, it may be advantageous for an inlet to the cooling flow return passage to be defined along the second side portion of the baffle plate, with a portion of the second side portion surrounding the inlet being raised toward the impact side of the cap plate.
    In any embodiment of the gas turbine, it may be advantageous that the gas turbine further includes a plurality of cooling passages extending radially in the vicinity of an inlet to the cooling flow recirculation passage radially through the outer band portion of the baffle plate, wherein the cooling passages for a fluid connection from the impingement air space out ,
    In any embodiment of the gas turbine, it may be advantageous that the gas turbine further comprises a flange which extends radially inwardly from the jacket, wherein the fluid line extends at least partially through the flange.
    Those skilled in the art will better understand the features and aspects of these and other embodiments after reading the description.
    BRIEF DESCRIPTION OF THE DRAWINGS
    A complete and comprehensible disclosure of the present invention, including the best mode for carrying it out, will be more particularly described in the following part of the description, reference being made to the accompanying drawings, in which:<Tb> FIG. 1 <SEP> shows a functional diagram of an example of a gas turbine, which may include at least one embodiment of the present invention;<Tb> FIG. 2 is a side cross-sectional view of a portion of an example of a combustion section of a gas turbine having an example of a combustor according to one or more embodiments of the present invention;<Tb> FIG. 3 is a perspective cross-sectional view of a portion of a combustor cap assembly according to one or more embodiments of the present invention;<Tb> FIG. FIG. 4 is a rear perspective view of a portion of the combustor cap assembly illustrated in FIG. 3 in accordance with one or more embodiments of the present invention; FIG.<Tb> FIG. FIG. 5 is a front perspective view of a portion of the combustor cap assembly illustrated in FIG. 3 in accordance with one embodiment of the present invention; FIG.<Tb> FIG. FIG. 6 is an enlarged perspective view of a portion of the combustor cap assembly illustrated in FIG. 4 in accordance with one embodiment of the present invention; FIG. and<Tb> FIG. FIG. 7 is a perspective view of a portion of the combustor cap assembly illustrated in FIG. 3 in operation in accordance with one or more embodiments of the present invention. FIG.
    DETAILED DESCRIPTION OF THE INVENTION
    Reference will now be made in detail to present embodiments of the invention, for which one or more examples are shown in the accompanying drawings. The detailed description uses numbers and letters as names to refer to features in the drawings. Like or similar terms in the drawings and the description are used to refer to the same or similar parts of the invention. As used herein, the terms "first / first / first," "second / second / second," and "third / third / third" may be used interchangeably to distinguish one component from another, and are not intended to indicate arrangement or importance mean individual components. The terms "upstream" and "downstream" refer to a relative direction with respect to a fluid flow in a fluid flow passage. For example, "upstream" means the direction from which the fluid comes, and "downstream" means the direction in which the fluid flows. 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 and / or coaxially aligned with an axial centerline of a particular one Component.
    Each example is given to illustrate the invention, but not for the purpose of limiting the invention. In fact, those skilled in the art will recognize that modifications and changes may be made to the present invention without departing from its scope or spirit. For example, features illustrated or described as part of one embodiment may be used in another embodiment to yield still another embodiment. Thus, the present invention is intended to cover such modifications and changes that come within the scope of the appended claims and their equivalents. Although shown and described herein as a commercial or stationary gas turbine, the present invention as shown and described herein is not limited to a stationary and / or commercial gas turbine unless otherwise specified in the claims. For example, the invention described herein may be used as a gas turbine in an aircraft or as a gas turbine in a ship.
    Referring now to the drawings, wherein like reference numerals denote like elements throughout the figures, and in which Figure 1 shows a functional block diagram of an example of a gas turbine 10 that may incorporate various embodiments of the present invention. As shown, the gas turbine 10 generally includes an inlet portion 12 that may include a series of filters, cooling coils, moisture separators, and / or other devices to clean or remove a working fluid (eg, air 14) entering the gas turbine engine 10 conditioned in another way. The working fluid 14 flows to a compressor section where a compressor 16 communicates increasing kinetic energy to the working fluid 14 to produce a compressed or pressurized air 18.
    The compressed air 18 is mixed with fuel 20 from a fuel source 22, such as a fuel rail, to form a combustible mixture in one or more burners 24. The combustible mixture is burned to produce combustion gases 26 having a high temperature, a high pressure and a high speed. The combustion gases 26 pass through a turbine 28 of a turbine section to produce work. For example, the turbine 28 may be connected to a shaft 30 such that rotation of the turbine 28 drives the compressor 16 to produce the compressed air 18. Alternatively or additionally, the shaft 30 may connect the turbine 28 to a generator 32 to produce electricity. Exhaust gases 34 from the turbine 28 flow through an exhaust section 36 that connects the turbine 28 to an exhaust stack 38 downstream of the turbine 28. The exhaust section 36 may include, for example, a heat recovery steam generator (not shown) for purifying the exhaust gases 34 and extracting heat therefrom before discharging them into the environment.
    FIG. 2 is a side cross-sectional view of a portion of an example combustor 24 according to one or more embodiments of the present invention. FIG. As shown in Fig. 2, the combustion chamber 24 is at least partially surrounded by at least one outer housing 40, such as a compressor pressure housing. The outer housing 40 is in fluid communication with the compressor 16 (FIG. 1) such that it receives at least a portion of the compressed air 18 therefrom. In one embodiment, an end cover 42 is joined to the outer housing 40 as shown in FIG. 2 to provide a seal around an opening defined within the outer housing 40. The opening is generally so large that it can receive the combustion chamber 24. The outer housing 40 and the end cover 42 at least partially define a high pressure air space 44 that at least partially surrounds the combustion chamber 24.
    At least one fuel nozzle 46 extends axially within the outer housing 40 with respect to an axial centerline of the combustor 24. As shown in FIG. 2, the combustor 24 may include a plurality of fuel nozzles 46 extending axially within the outer housing 40. The fuel nozzle 46 may be joined to the end cover 42 at a first end. A second or downstream end of the fuel nozzle 46 terminates near a combustion chamber or zone 48 defined in the outer housing 40.
    A combustion liner 50 extends downstream from the fuel nozzle 46 and may at least partially define the combustion chamber 48. In addition, the combustion liner 50 may at least partially define an annular flow passage 52 within the outer housing 40. In certain embodiments, the annular flow passage 52 may be further defined by one or more baffles or bushings 54 surrounding the combustion chamber liner 50. In certain embodiments, the annular flow passage 52 may be further defined by the outer housing 40, the end cover 42, and / or other liners or features provided in the outer housing 40.
    At least a portion of the fuel nozzle 46 extends axially through a combustion cap assembly 100. The combustion cap assembly 100 extends radially, circumferentially and axially within the outer casing 40. The combustor cap assembly 100 includes at least one annular shell 102 that supports at least a portion of the fuel nozzle 46 surrounds in the circumferential direction. The sheath 102 may comprise a single or one-piece sheath, or may comprise a plurality of sheaths joined together by bolts, by welding, or by any other suitable mechanical fastener at or near their respective ends. In one embodiment, the jacket 102 includes a first annular jacket 104 joined to a second annular jacket 106.
    In certain embodiments, the shroud 102 at least partially defines the annular flow passage 52 within the outer housing 40. In one embodiment, an outer surface or surface 108 of the outer shroud 102 at least partially defines the annular flow passage 52 within the outer housing 40. The annular flow passage 52 defines a fluid flow path to direct at least a portion of the pressurized air 18 from the high pressure air space 44 and / or the compressor 16 (FIG. 16) to the end cap 42.
    FIG. 3 provides a perspective cross-sectional view of a portion of the combustor cap assembly 100 as illustrated in FIG. 2, in accordance with one or more embodiments of the present invention. FIG. 4 provides a rear perspective view of a portion of the combustor cap assembly 100 illustrated in FIGS. 2 and 3, in accordance with one or more embodiments. FIG. 5 provides a front perspective view of a portion of the combustor cap assembly 100 illustrated in FIG. 3 in accordance with an embodiment of the present invention. As shown in FIGS. 3 and 4, the shell 102 has a first end portion 110 that is axially separated from a second end portion 112. In one embodiment, as shown in FIGS. 3 and 4, a flange 114 extends radially inward from the shell 102 toward an axial centerline of the shell 102. The flange 114 may be disposed proximate the first end portion 110. The flange 114 may be used to join the first and second shells 104, 106 together.
    As shown in FIGS. 3, 4, and 5, the combustor cap assembly 100 further includes a baffle 116. In one embodiment, the baffle plate 116 is joined to the shell 102 near the second end portion 112. The baffle 116 extends radially and circumferentially at least partially over the second end portion 112 of the shell 102. The baffle 116 may at least partially define at least one fuel nozzle passage 118 axially therethrough to receive the fuel nozzle 46 (FIG. 2). ,
    As shown in FIGS. 3 and 4, the baffle 116 has a first or upstream side portion 120. As shown in FIGS. 3 and 5, the baffle plate 116 has a second or downstream side portion 122, and as shown in FIGS. 3, 4 and 5, the baffle plate 116 has an outer band portion 124. The outer band portion 124 at least partially defines a radially outer edge of the baffle 116. In various embodiments, as shown in FIG. 3, the baffle 116 at least partially defines a plurality of impingement cooling bores 126. The baffles 126 thus extend through the first side portion 120 and the second Side part 122, that they provide a fluid connection through the baffle 116.
    As shown in FIG. 3, the baffle plate 116 further defines at least one cooling flow return passage 128. In one embodiment, the cooling flow return passage 128 extends substantially axially through the baffle 116. As shown, the cooling flow return passage 128 extends through the first side portion 120 and second side portion 122 to provide through the baffle plate 116 for fluid communication. As illustrated in FIG. 5, an inlet 130 to the cooling flow return passage 128 is defined along the second side portion 122 of the baffle 116. In one embodiment, a raised portion 132 of the second side portion 122 surrounds the inlet 130. The raised portion 132 is raised axially outward with respect to the remainder of the second side portion 122.
    In one embodiment, as shown in FIGS. 3 and 5, the outer band portion 124 at least partially defines a plurality of cooling passages 134 that extend substantially radially through the outer band portion 124 of the baffle plate 116. In one embodiment, as shown in FIG. 5, a greater number of the cooling passages 134 may be formed or concentrated near the inlet 130 of the cooling flow return passage 128 than along portions of the outer hinge portion 124 that are not so close to the cooling flow return passage 128.
    As shown in FIGS. 3 and 4, the combustor cap assembly 100 further includes a cap plate 136 that mates with the baffle plate 116. FIG. 6 provides an enlarged perspective view of a portion of the combustor cap assembly 100 illustrated in FIG. 4 in accordance with an embodiment of the present invention. In one embodiment, as shown in FIG. 6, an outer edge 138 of the cap plate 136 is joined or connected to the outer band portion 124 of the baffle plate 116. As shown in FIG. 6, the cap plate 136 has an impact side 140 which faces the second side part 122 of the baffle plate 116. An opposite or hot side 142 of the cap plate 136 faces the firing zone or combustion chamber 48.
    The baffle 140 is axially spaced from the second side member to define a baffle 144 between itself and this. The impingement cooling bores 126 provide fluid communication into the impingement air space 144, and the cooling flow recirculation passage 128 provides fluid communication from the impingement air space 144. In one embodiment, the cooling passages 134 also provide fluid communication from the impingement air space 144. In one embodiment, the cap plate 136 defines how 3, and fuel nozzle passage 118.
    In one embodiment, as shown in FIG. 4, the shell 102 and the baffle 116, particularly the first side portion 120, at least partially define a cooling air space 146 within the combustor cap assembly 100. As shown in FIGS. 3 and 6 the plurality of impingement cooling bores 126 for fluid communication between the cooling air space 146 and the impingement air space 144. The cooling air space 146 may at least partially surround a portion of the fuel nozzle 46 (FIG. 1).
    In various embodiments, as shown in FIG. 3, the combustor cap assembly 100 further includes at least one fluid conduit 148 in fluid communication with the cooling flow return passage 128. In one embodiment, the fluid conduit 148 is aligned coaxially with the cooling flow return passage 128. The fluid conduit 148 extends substantially axially from the first side portion 120 of the baffle plate 116 to the first end portion 110 of the shell 102.
    In one embodiment, an outlet end 150 of the fluid conduit 148 extends at least in part through the flange 114, as shown in FIG. 4. In one embodiment, the outlet end 150 of the fluid conduit 148 is in fluid communication with a cooling air discharge opening 152, as shown in FIG. 3. The cooling air discharge opening 152 provides fluid communication between the impingement air space 144 and the annular flow passage 52. As shown in FIG. 3, the fluid conduit 148 defines a cooling flow discharge passage 154 within the cooling air space 146 which is fluidically isolated from the cooling air space 146.
    Fig. 7 provides a perspective view of a portion of the combustor cap assembly illustrated in Figs. 2-6 in operation in accordance with one or more embodiments of the present invention. As shown in FIG. 2, the compressed air 18 flows from the high-pressure space 44 along the annular flow passage 52 toward the end cover 42, where it reverses its flow direction. A portion of the compressed air 18 flows through the fuel nozzles where it is mixed with fuel upstream of ignition 48 upstream of the combustion chamber 48. A portion of the compressed air 18 is directed into the combustor cap assembly 100 and into the cooling air space 146 (FIG. 7) where it may be used to provide cooling to the fuel nozzle 46 (FIG. 2).
    Referring now to FIG. 7, it is shown that the compressed air 18 from the cooling air space 146 flows through the impingement cooling holes 126 and strikes the impact side 140 of the cap plate 136. As a result, heat energy is transferred from the cap plate 136 to the compressed air 18, thereby allowing convection and / or impingement jet cooling for the cap plate 136. Heated compressed air 156 is then directed via the cooling flow return passage 128 out of the impingement air space 144 and into the fluid line 148. In one embodiment, the raised portion 132 of the second side portion 122 of the baffle 116 surrounding the inlet 130 reduces localized hotspots that may form on the cap plate 136 by reducing an axial gap between the second side portion 122 of the baffle 116 and Impact side 140 of the cap plate 136, whereby the flow velocity of the heated compressed air 156 is increased.
    The heated compressed air 156 is then sent to the outlet end 150 of the fluid line 148 and via the exhaust outlet 152 from the fluid line 148. The heated compressed air 156 is then fed back into the annular flow passage 52 where it exits with compressed air 18 the high pressure space 44 mixes (Fig. 2). The reintroduction of the heated compressed air 156 back into the stream of compressed air 18 flowing out of the high pressure space provides additional air for the fuel / air reaction in the fuel nozzle. The additional air reduces engine emissions, especially NOx emissions.
    The description uses examples which disclose the invention including the best mode and is intended to enable one skilled in the art to practice the invention, including the manufacture and use of devices or systems and the practice of any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that may occur to one skilled in the art. These and other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they have equivalent structural elements that are not materially different from the literal language of the claims.
    A combustor cap assembly includes an annular shell and a baffle plate joined to the shell. The baffle plate defines at least in part a plurality of impingement cooling bores and a cooling flow return passage. A cap plate is assembled with the baffle plate. The cap plate has an impact side which is directed to a second side part of the baffle plate, wherein the impact side is axially spaced from the second side part to define a baffle between them and this. The cooling flow recirculation passage is in fluid communication with the impingement air space. A fluid conduit extends from a first side portion of the baffle plate to a first end portion of the shell. The fluid conduit is in fluid communication with the cooling flow return passage and provides fluid communication from the impingement air space.
    LIST OF COMPONENTS
    [0052]<Tb> 10 <September> Gas Turbine<Tb> 12 <September> inlet section<Tb> 14 <September> working fluid<Tb> 16 <September> compressor<tb> 18 <SEP> Compressed air<Tb> 20 <September> Fuel<Tb> 22 <September> fuel source<Tb> 24 <September> combustion chamber<Tb> 26 <September> combustion gases<Tb> 28 <September> Turbine<Tb> 30 <September> wave<Tb> 32 <September> generator / motor<Tb> 34 <September> exhaust<Tb> 36 <September> exhaust section<Tb> 38 <September> exhaust stack<tb> 40 <SEP> Outer case<Tb> 42 <September> end cover<Tb> 44 <September> high pressure air space<Tb> 46 <September> fuel<Tb> 48 <September> combustion chamber<Tb> 50 <September> combustion chamber lining<tb> 52 <SEP> Annular flow passage<Tb> 54 <September> impingement sleeve / bush<tb> 55-99 <SEP> Not used<Tb> <September><Tb> 100 <September> combustor cap assembly<Tb> 102 <September> coat<tb> 104 <SEP> First coat<tb> 106 <SEP> Second coat<Tb> 108 <September> outside / Area<tb> 110 <SEP> First end part<tb> 112 <SEP> Second end part<Tb> 114 <September> flange<Tb> 116 <September> Flapper<Tb> 118 <September> fuel nozzle passage<tb> 120 <SEP> First / upstream side panel<tb> 122 <SEP> Second / downstream side part<tb> 124 <SEP> Outer band part<Tb> 126 <September> impingement cooling hole<Tb> 128 <September> cooling flow return passage<Tb> 130 <September> inlet<tb> 132 <SEP> Sublime part<Tb> 134 <September> cooling passage<Tb> 136 <September> cap plate<Tb> 138 <September> outer edge<Tb> 140 <September> baffle / cooling side<tb> 142 <SEP> Opposite / hot side<Tb> 144 <September> Impact airspace<Tb> 146 <September> cooling airspace<Tb> 148 <September> fluid line<Tb> 150 <September> outlet<Tb> 152 <September> exhaust outlet<Tb> 154 <September> cooling flow discharge passage<tb> 156 <SEP> Heated exhaust air
    权利要求:
    Claims (10)
    [1]
    A combustor cap assembly comprising:an annular shell having a first end portion and a second end portion;a baffle plate mated with the shell proximate the second end portion, the baffle plate having a first side portion, a second side portion, and an outer band portion, the baffle plate at least partially defining a plurality of impingement cooling bores and a cooling flow return passage;a cap plate joined to the baffle plate, the cap plate having an impact side facing the second side part of the baffle plate, the bounce side being axially spaced from the second side part to define an impingement air space therebetween, the cooling flow recirculation passage having the baffle air space in fluid communication; anda fluid conduit in fluid communication with the cooling flow return passage, the fluid conduit extending from the first side portion of the baffle plate toward the first end portion of the shell.
    [2]
    2. The combustor cap assembly of claim 1, wherein an outlet end of the fluid conduit is in fluid communication with a cooling air discharge opening; and / or wherein an inlet to the cooling flow return passage is defined along the second side part of the baffle plate, a part of the second side part surrounding the inlet being raised toward the bounce side of the cap plate.
    [3]
    3. The combustor cap assembly of claim 1 or 2, further comprising a plurality of cooling passages extending radially in the vicinity of an inlet to the cooling flow recirculation passage through the outer band portion of the baffle plate, wherein the cooling passages for a fluid connection out of the impingement air space.
    [4]
    4. A combustor cap assembly according to any one of the preceding claims, wherein the baffle plate and the cap plate at least partially define a fuel nozzle passage extending axially therethrough.
    [5]
    5. combustor cap assembly according to one of the preceding claims, further comprising a flange which extends radially inwardly from the jacket, wherein the fluid line extends at least partially through the flange.
    [6]
    6. combustion chamber cap assembly according to one of the preceding claims, wherein the jacket and the first side part of the baffle plate at least partially define a cooling air space, wherein the plurality of baffles provide a fluid connection between the cooling air space and the baffle air space.
    [7]
    7. The combustor cap assembly of claim 6, wherein the fluid conduit defines a cooling flow discharge passage within the cooling air space fluidly isolated from the cooling air space.
    [8]
    8. combustion chamber comprising:a fuel nozzle that extends axially within an outer housing; anda combustor cap assembly having an annular jacket circumferentially surrounding at least a portion of the fuel nozzle, the jacket defining at least in part an annular flow passage within the outer housing, the combustor cap assembly further comprising:a baffle plate mated with a second end portion of the shell, the baffle plate having a first side portion, a second side portion and an outer band portion, the baffle plate defining, at least in part, a plurality of impingement cooling holes and a cooling flow return passage, the shell and the first side portion At least in part, the baffle plate defining a cooling air space in fluid communication with the annular flow passage;a cap plate mated with the baffle plate, the cap plate having a bounce side facing the second side part of the baffle plate, the bounce side being axially spaced from the second side part to define an impingement air space therebetween, the plurality of baffled cooling holes for a baffle Providing fluid communication between the cooling air space and the impingement air space, the cooling flow recirculation passage providing fluid communication from the impingement air space; anda fluid conduit in fluid communication with the cooling flow return passage, the fluid conduit extending within the cooling air space, the fluid conduit being in fluid communication with the annular flow passage.
    [9]
    9. Combustion chamber according to claim 8, wherein the fluid conduit extends within the cooling air space from the first side part of the baffle plate to the first end part of the second jacket.
    [10]
    10. Gas turbine, comprising:a compressor section, a combustion section downstream of the compressor section and a turbine disposed downstream of the combustion section, the combustion section having a combustion chamber at least partially surrounded by an outer housing, the combustion chamber having a fuel nozzle located axially within the outer housing extending, and having a Brennkammerkappenanordnung surrounding at least a portion of the fuel nozzle in the circumferential direction; andwherein the combustor cap assembly comprises:an annular shell having a first end portion and a second end portion, the shell defining, at least in part, an annular flow passage within the outer housing;a baffle plate mated with the shell adjacent the second end portion, the baffle plate having a first side portion axially spaced from a second side portion, the baffle plate defining a plurality of impingement cooling holes and a cooling flow return passage;a cooling air space defined at least in part by the shell and the first side part of the baffle plate;a cap plate joined to the baffle plate;an impingement air space defined between the second side part of the baffle plate and an impact side of the cap plate, the plurality of impingement cooling bores allowing fluid flow into the impingement air space and allowing the cooling flow recirculation passage to allow fluid flow out of the impingement air space; anda fluid conduit in fluid communication with the cooling flow return passage, the fluid conduit defining a cooling flow delivery passage within the cooling air space fluidly isolated from the cooling air space.
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    同族专利:
    公开号 | 公开日
    DE102015113006A1|2016-02-25|
    CN105371302A|2016-03-02|
    US9470421B2|2016-10-18|
    US20160054004A1|2016-02-25|
    JP6602094B2|2019-11-06|
    JP2016044677A|2016-04-04|
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2019-03-29| AZW| Rejection (application)|
    优先权:
    申请号 | 申请日 | 专利标题
    US14/462,646|US9470421B2|2014-08-19|2014-08-19|Combustor cap assembly|
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