• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
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    • 专利摘要:
    A combustor cap assembly (100) includes a baffle plate (120) coupled to an annular shell (104) and a cap plate (140) coupled to the baffle plate (120) for communicating therebetween a baffle collecting space (146) form. The combustor cap assembly (100) further includes a flow conditioning plate (102) coupled to a forward end portion (114) of the shell (104). The flow conditioning plate (102) has an inner band portion (152), an outer band portion (154) and an annular portion (156). The annular portion (156) defines a plurality of flow conditioning passages (162). The inner band portion (152) at least partially defines a cooling air plenum (110) within the combustor cap assembly (100). The inner band portion (152) further defines an exhaust duct (166) in fluid communication with the impingement air plenum (146) and with an exhaust air outlet (168). The flow conditioning plate (102) further defines a cooling air passage (176) that provides cooling air flow into the cooling air plenum (110).
    公开号:CH710060A2
    申请号:CH01187/15
    申请日:2015-08-17
    公开日:2016-02-29
    发明作者:Carolyn Ashley Antoniono；Jonathan Hale Kegley；Lucas John Stoia；Patrick Benedict Melton；William Francis Carnell Jr
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    The present invention generally relates to a Brennkamnaerkappenanordnung. In particular, the invention includes recirculation of cooling air used to cool a cap plate of the combustor cap assembly for use in combustion.
    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 combustion chamber. The compressed air is mixed with a fuel and ignited in a combustion chamber defined in the combustion chamber, thereby generating combustion gases of high temperature. The combustion gases are then directed from the combustion chamber via a liner and / or transition piece into a turbine section of the turbomachine where the combustion gases flow over alternating rows of stationary vanes and blades secured to a rotor shaft. As the combustion gases flow over the blades, kinetic and / or thermal energy is transferred to the 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 delivered to the combustor 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 within 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 arranged adjacent to the combustion chamber substantially. 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 in the cap assembly and on 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, emissions such as nitrogen oxides (NOx) can be increased, and turbine efficiency can be reduced. Therefore, an improved system for cooling the cap plate would be useful, which recycles the compressed air used to cool the cap plate so that it can be premixed with fuel prior to combustion.
    Brief description of the drawings
    Aspects and advantages of the invention are set forth below in the following description, or may be obvious from the description, or may be learned by practice of the invention.
    One embodiment of the present invention is a combustion cap assembly having a baffle plate coupled to an annular shell. A cap plate is coupled to the baffle and the cap plate and the baffle define an impingement air space between each other. A flow conditioning plate is coupled to a forward end portion of the shell. The flow conditioning plate has an inner band portion, an outer band portion and an annular portion extending radially therebetween. The annular portion defines a plurality of flow conditioning passages extending generally axially therethrough. The inner band portion at least partially defines a cooling air plenum within the combustor cap assembly. The inner band portion defines, at least in part, an exhaust air passage in fluid communication with the baffle air collecting space and with an exhaust air outlet. The flow conditioning plate further defines a cooling air passage. The cooling air passage provides cooling air flow through the flow conditioning plate into the cooling air plenum.
    In the aforementioned combustion cap assembly, the cooling air passage may pass through the outer band portion, the annular portion and the inner band portion.
    Additionally or alternatively, the cooling air passage of each of the flow conditioning passages may be fluidically isolated.
    Further additionally or as a further alternative thereto, the cooling air passage may be angled within the flow conditioning plate to impart an angular twist to the flow of cooling air within the cooling air plenum.
    The combustor cap assembly of any of the above-mentioned types may further include a fluid conduit extending within the shell between the baffle plate and the inner band portion of the flow conditioning plate, wherein the fluid conduit may provide fluid communication between the baffle plenum and the exhaust duct.
    In one embodiment, the exhaust outlet extends through a radially outer surface of the inner band portion upstream of the plurality of flow conditioning passages.
    In another embodiment, the exhaust outlet extends through a radially outer surface of the inner band portion downstream of the plurality of flow conditioning passages.
    The exhaust outlet may be disposed within one or more flow conditioning passages of the plurality of flow conditioning passages.
    In the combustor cap assembly of each of the above-mentioned types, the flow conditioning plate may define a bleed passage in fluid communication with the cooling air passage, wherein the bleed passage is formed in the annular section.
    In the last-mentioned combustor cap assembly, the bleed passage may provide fluid communication through a downstream side of the annular portion.
    Another embodiment of the present invention is a combustion chamber. The combustion chamber has a fuel nozzle extending substantially axially within an outer housing defining a high pressure air space within the combustion chamber. The combustion chamber also has a combustion chamber cap arrangement. The combustor cap assembly includes a baffle plate coupled to a rear end portion of an annular shell and a cap plate coupled to the baffle plate. The cap plate and the baffle plate define a baffle collecting space between each other. A flow conditioning plate is coupled to a forward end portion of the shell. The flow conditioning plate has an inner band portion, an outer band portion and an annular portion extending radially therebetween. The annular portion defines a plurality of flow conditioning passages that provide for fluid flow through the annular portion. The inner band portion and the outer shell at least partially define a cooling air plenum. The inner band portion defines, at least in part, an exhaust air passage in fluid communication with the baffle air collecting space and with an exhaust air outlet. The flow conditioning plate defines a cooling air passage that provides cooling air flow through the flow conditioning plate into the cooling air plenum.
    In the aforementioned combustion chamber, the cooling air can pass through the outer band portion, the annular portion and the inner band portion.
    Additionally or alternatively, the cooling air passage of each of the flow conditioning passages may be fluidically isolated.
    Further additionally or as a further alternative thereto, the cooling air passage may be angled within the flow conditioning plate to impart an angular twist to the cooling air flow within the cooling air plenum.
    In an embodiment, the flow conditioning plate may define a bleed passage in fluid communication with the cooling air passage, wherein the bleed passage may be formed in the annular section.
    In the last-mentioned combustor embodiment, the bleed passage may provide fluid communication through a downstream side of the annular portion.
    Another embodiment of the present invention is a gas turbine. The gas turbine has a compressor section and a combustion section located downstream of the compressor section. The combustion section has an outer housing that at least partially surrounds a combustion chamber, wherein the outer housing forms a high pressure air space around the combustion chamber and is in fluid communication with the compressor section. A turbine section is located downstream of the combustion section. The combustion chamber has a fuel nozzle axially extending within the outer housing and a combustion cap assembly surrounding at least a portion of the fuel nozzle along the circumference. The combustor cap assembly includes a baffle plate coupled to a rear end portion of an annular shell, a cap plate coupled to the baffle plate, and a flow conditioning plate coupled to a forward end portion of the shell. The cap plate and the baffle plate define a baffle collecting space between each other. The flow conditioning plate has an inner band portion, an outer band portion and an annular portion extending radially therebetween. The annular portion defines a plurality of flow conditioning passages that allow substantially axial fluid flow through the annular portion. The inner band portion and the outer band portion at least partially define a cooling air plenum within the combustor cap assembly. The inner band portion defines, at least in part, an exhaust air passage in fluid communication with the baffle air collecting space and with an exhaust air outlet. The flow conditioning plate further defines a cooling air passage that provides cooling air flow from the high pressure air space through the flow conditioning plate into the cooling air plenum.
    In the aforementioned gas turbine, the cooling air passage may extend through the outer band portion, the annular portion, and the inner band portion.
    Additionally or alternatively, the cooling air passage of each of the flow conditioning passages may be fluidically isolated.
    In one embodiment of the gas turbine of any of the aforementioned types, the flow conditioning plate may define a bleed passage in fluid communication with the cooling air passage, wherein the bleed passage may be formed in the annular section and wherein the bleed passage is for fluid communication through a downstream side of the annular passage Section through can provide.
    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 full and enabling disclosure of the present invention, including the best mode for carrying it out, is more particularly described in the remainder of the specification, reference being made to the accompanying drawings, in which:<Tb> FIG. 1 <SEP> is a functional diagram of an example of a gas turbine that may include at least one embodiment of the present invention;<Tb> FIG. FIG. 2 is a side cross-sectional view of a portion of an exemplary combustion section including an example of a combustor that may accommodate various embodiments of the invention; FIG.<Tb> FIG. 3 <SEP> is a perspective cross-sectional view of a portion of an exemplary combustor cap assembly in accordance with one or more embodiments of the present invention;<Tb> FIG. 4 is a front and 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;<Tb> FIG. 5 is a front 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;<Tb> FIG. 6 <SEP> is a front view of the combustor cap assembly according to one or more embodiments;<Tb> FIG. 7 is a side cross-sectional view of a portion of an exemplary combustor cap assembly according to at least one embodiment of the present invention;<Tb> FIG. 8 is a side cross-sectional view of a portion of an exemplary combustor cap assembly according to at least one embodiment of the present invention;<Tb> FIG. 9 <SEP> is a side cross-sectional view of a portion of an exemplary combustor cap assembly according to at least one embodiment of the present invention;<Tb> FIG. 10 is a side cross-sectional view of a portion of an exemplary combustor cap assembly according to at least one embodiment of the present invention;<Tb> FIG. 11 <SEP> is a cross-sectional view in the downstream direction or a perspective view from the front of a part of the combustion cap assembly according to at least one embodiment of the present invention;<Tb> FIG. FIG. 12 is a front cross-sectional view of the combustor cap assembly shown in FIG. 11; FIG.<Tb> FIG. 13 is a side cross-sectional view of a portion of an exemplary combustor cap assembly according to at least one embodiment of the present invention; and<Tb> FIG. 14 is a flowchart of an exemplary in-service combustor cap assembly according to at least one embodiment of the present invention.
    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 be an order or importance mean the individual components. The terms "upstream" and "downstream" refer to a relative direction with respect to 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 coaxial with an axial centerline of a particular component is aligned.
    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 an industrial or land based gas turbine, the present invention as shown and described herein is not limited to a land-based and / or industrial 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 designate like elements throughout the figures, wherein Figure 1 shows a functional block diagram of an example of a gas turbine engine 10 which may incorporate various embodiments of the present invention. As shown, the gas turbine 10 generally includes an inlet section 12 which may include a series of filters, cooling coils, moisture separators, and / or other devices to clean or otherwise treat a working fluid, such as air 14, entering the gas turbine engine 10 Way to condition. The air 14 flows to a compressor section where a compressor 16 communicates increasing amount of kinetic energy to the air 14 to produce compressed air or pressurized air 18.
    The compressed air 18 is mixed with fuel 20 from a fuel source 22, such as a fuel supply unit, to form a combustible mixture in one or more combustors 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 perform 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 generate 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 illustrated in FIG. 2, combustor 24 is at least partially surrounded by at least one outer housing 40, such as a compressor outlet housing. The outer housing 40 is in fluid communication with the compressor 16 (FIG. 1) so as to receive at least a portion of the compressed air 18 therefrom.
    As shown in FIG. 2, an end cover 42 is coupled to the outer housing 40 to provide a seal around an opening defined in the outer housing 40. The opening is generally so large that it can receive the combustion chamber 24. The outer housing 40 and / or the end cover 42 at least partially define a high pressure air space 44 that at least partially surrounds the combustion chamber 24. A head end portion 46 of the combustion chamber 24 is defined at least in part by the end cover 42 and the outer housing 40. The head end portion 46 defines an area within the combustor 24 in which a portion of the compressed air 18 from the high pressure air space 44 reverses its direction of flow.
    At least one fuel nozzle 48 extends within the outer housing substantially axially with respect to an axial centerline of the combustion chamber 24 and / or an axial centerline of the end cover 42. As shown in FIG. 2, the combustor 24 may include a plurality of fuel nozzles 48 axially extending inside the outer housing 40. The fuel nozzle 48 may be coupled to the end cover 42 at a first end. A second or downstream end of the fuel nozzle 48 terminates proximate a combustion chamber or combustion zone 50 defined in a combustor liner 52 extending downstream from the fuel nozzle 48.
    The combustor liner 52 may at least partially define an annular flow passage 54 within the outer housing 40. In certain embodiments, the annular flow passage 54 may be defined by one or more baffles or bushings 56 surrounding the combustor liner 52. In certain embodiments, the annular flow passage 54 may be defined or further defined by one or more of the outer housing 40, the end cover 42, and / or other liners or features, such as an inner wall, disposed within the outer housing 40 To be defined. The annular passage 54 provides fluid communication between the high pressure air space 44 and the head end portion 46 of the combustor 24.
    In various embodiments, at least a portion of the fuel nozzle 48 extends axially through a combustor cap assembly 100. The combustor cap assembly 100 extends radially, circumferentially, and axially within the outer housing 40. In one embodiment, the combustor cap assembly 100 includes an annular flow conditioning plate 102 and a annular shell 104 on. In certain embodiments, the combustor cap assembly 100 may include an annular secondary jacket 106 extending from a forward end portion 108 of the flow conditioning plate 102 toward the end cover 42. The sheath 104 and / or the secondary sheath 106 may be coaxially aligned with the flow conditioning plate 102.
    As shown in FIG. 2, the flow conditioning plate 102, the shell 104, and / or the secondary shell 106 surround at least a portion of the fuel nozzle 48 along the circumference. In one embodiment, as shown in FIG. 2, the flow conditioning plate 102 and the shell 104 at least partially define a cooling air plenum 110 around the fuel nozzle 48 within the combustor cap assembly 100. In other embodiments, the cooling air plenum 110 may be further defined by the secondary shell 106 , The cooling air plenum 110 is in fluid communication with the head end portion 46 of the combustor 24.
    FIG. 3 provides a cross-sectional perspective 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. 4 is a rear perspective view of a portion of the combustor cap assembly illustrated in FIG. 100, according to one or more embodiments. 5 is a front perspective view of a portion of the combustor cap assembly 100 illustrated in FIG. 100, in accordance with one or more embodiments. 6 provides a front view of the combustor cap assembly 100 in accordance with one or more embodiments.
    In one embodiment, as shown in FIG. 3, the shell 104 extends axially away from the rear end portion 112 of the flow conditioning plate 102. The jacket 104 has a first or forward end portion 114 that is axially separated from a second or rear end portion 116. In one embodiment, as shown in FIGS. 3 and 4, a flange 118 extends radially inwardly from the shell 104 toward an axial centerline of the shell 104. In one embodiment, the flange 118 is proximate the first End portion 114 arranged. The flange 118 may be used to couple the sheath 104 to a fastener (not shown) of the flow conditioning plate 102. For example, one or more bolts or other suitable fasteners 118 (not shown) may pass through the flange to secure or join the two components together.
    As shown in FIGS. 3 and 4, the combustion chamber cap assembly 100 further includes a baffle plate 120. In one embodiment, the baffle plate 120 is coupled to the shell 104 near the second end portion 116. The baffle plate 120 extends radially and circumferentially at least partially over the second end portion 116 of the shell 104. The baffle plate 120 may at least partially define at least one fuel nozzle passage 122 that extends substantially axially therethrough to receive the fuel nozzle 48 (FIG 2).
    As shown in FIGS. 3 and 4, the baffle plate 120 has a first or upstream side portion 124. As shown in FIGS. 3 and 5, the baffle plate 120 also has a second or downstream side portion 126. As shown in FIG. 3, the baffle plate 120 further includes an outer band portion 128. The outer band portion 128 at least partially defines a radially outer edge of the baffle plate 120. In various embodiments, as shown in FIGS. 3 and 4, the baffle plate 120 at least partially defines a plurality of baffle cooling holes 130. The baffle holes 130 thus extend through the first side portion 124 and the second side portion 126 (FIGS. 3 and 5) to provide fluid communication from the cooling air plenum 112 through the baffle plate 120.
    In one embodiment, as shown in FIG. 3, the baffle plate 120 further defines at least one cooling flow return passage 132. As shown, the cooling flow return passage 132 extends through the first side portion 124 and the second side portion 126 for fluid communication through the baffle plate 120 to worry about. In one embodiment, the cooling flow return passage 132 extends substantially axially through the baffle plate 120.
    As illustrated in FIG. 5, an inlet 134 to the cooling flow recirculation passage 132 is defined at the second side portion 126 of the baffle plate 120. In one embodiment, a raised portion or portion 136 of the second side portion 126 surrounds the inlet 134. The raised portion 136 is raised axially outward with respect to the surrounding second side portion 126.
    In certain embodiments, as shown in FIGS. 3 and 5, the outer band portion 128 at least partially defines a plurality of cooling passages 138 that extend substantially radially through the outer band portion 128 of the baffle plate 120. In one embodiment, as shown in FIG. 5, a greater number of the cooling passages 138 may be formed or concentrated near the inlet 134 of the cooling flow return passage 132 than along portions of the outer band portion 128 that are not close to the cooling flow return passage 132.
    As shown in FIGS. 2, 3, and 6, the combustor cap assembly 100 further includes a cap plate 140 that is coupled to the baffle plate 120. The cap plate 140 may be coupled to the outer band portion 128 of the baffle plate 120. As shown in FIG. 6, the cap plate 140 extends circumferentially and radially above the baffle plate 120. As shown in FIG. 3, the cap plate 140 has an impact side 142 facing the second side portion 126 of the baffle plate 120. An opposite or hot side 144 of the cap plate 140 faces the firing zone or combustion chamber 50 (FIG. 2) when installed in the combustion chamber 24.
    As shown in FIG. 3, the baffle 140 is axially spaced from the second side 126 to define a baffle 146 therebetween. The impingement cooling holes 130 provide fluid communication from the cooling air plenum 110 into the impingement air plenum 146. The impingement cooling holes 130 may be oriented substantially to direct a jet of compressed air 18 directly to the impact side 142 of the cap plate 140 during operation of the combustion chamber 24, thereby providing the blast cooling of the latter. Cooling flow return passage 132 provides fluid communication out of baffle plenum 146. In one embodiment, the cooling passages 138 also provide fluid communication from the baffle plenum 146. In one embodiment, the cap plate 140 further defines the fuel nozzle passage 122, as shown in FIG. 3.
    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 impingement air plenum 146 via the cooling flow recirculation passage 132. In one embodiment, the fluid conduit 148 is coaxially aligned with the cooling flow return passage 132. The fluid conduit 148 extends substantially axially from the first side portion 124 of the baffle plate 120 to the first end portion 114 of the shell 104. In various embodiments, the combustor cap assembly 100 may include a plurality of fluid conduits 148. Although shown as a generally circular tube, the fluid conduit 148 may have any cross-sectional shape.
    In one embodiment, an outlet end 150 of the fluid conduit 148 extends at least in part through the flange 118, as shown in FIGS. 3 and 4. The fluid conduit 148 defines an exhaust passage that extends from the impingement air plenum 146 and / or from the cooling flow recirculation passage 132 through the cooling air plenum 112 and that is fluidly isolated from the cooling air plenum 112.
    In various embodiments, as illustrated in FIG. 3, the flow conditioning plate 102 is coupled to the forward end portion 114 and / or the flange 118 of the shell 104. The flow conditioning plate 102 may be coupled to the forward end portion 114 and / or the flange 118 of the shell 104 via mechanical fasteners (such as bolts or the like), and / or by welding or other suitable connection means (not shown).
    In certain embodiments, as illustrated in FIG. 3, the flow conditioning plate 102 has an inner band portion 152, an outer band portion 154, and an annular portion 156. The annular portion 156 extends axially and radially between the inner and outer band portions 152, 154. When installed in the combustor 24, as shown in FIG. 2, the annular portion 156 extends radially and axially within the annular flow passage 54 In certain embodiments, the annular portion 156 fluidly separates the high-pressure air space 44 from the head end portion 46. As shown in FIG. 3, the annular portion 156 has an upstream side 158 and a downstream side 160. A plurality of flow conditioning passages 162 provide fluid communication through the annular portion 156, particularly through the upstream and downstream sides 158, 160.
    As shown in FIG. 3, the annular portion 156 has a relatively wide axial thickness so that the flow conditioning passages 162 become elongated tubes formed between inlets 164 formed on the upstream side 158 of the annular portion 156 and outlets formed on the downstream side 160. Although other shapes are possible, the flow conditioning passages 162 may have a cylindrical shape. The flow conditioning passages 162 may be parallel to each other and may also be aligned parallel to a center axis of the combustor 24. As illustrated, the upstream side 158 of the annular portion 156 may include a planar surface that is approximately perpendicular to the flow direction through the annular flow passage 54. The inlets 164 of the flow conditioning passages 162 may be formed through the upstream side 158.
    The upstream end 160 of the annular portion 156 may also include a planar surface that is oriented approximately perpendicular to the flow direction through the annular flow passage 54. The outlets 165 of the flow conditioning passages 162 may be formed through this downstream side 160. The number of flow conditioning passages 162 included in the annular portion 156 of the flow conditioning plate 102 may vary depending on the application. In one embodiment, the number of flow conditioning passages 162 may be between 100 and 200.
    As shown in FIG. 6, the flow conditioning passages 162 in the annular portion 156 may be configured to have circumferentially arranged rows of the flow conditioning passages 162 formed therein. As shown, the rows may include an inner radial row and an outer radial row with the inner radial row closer to the inner band portion 152. As also shown, the flow conditioning passages 162 of the inner radial row and the outer radial row may be timed or configured to be angularly offset from one another. In the case where the flow conditioning passages 162 are arranged to form an inner radial row and an outer radial row in radial rows, each row may have between 50 and 100 flow conditioning passages 162, although other configurations are possible.
    As illustrated in FIG. 3, at least some of the flow conditioning passages 162 may have a cross-sectional diameter D that varies between the upstream side 158 and the downstream side 160. For example, a flow conditioning passage 162 may have a first cross-sectional diameter Di close to the inlet 164 of the flow conditioning passage 162 and a second cross-sectional diameter D2 downstream of the first cross-sectional diameter Di. In one embodiment, the first cross-sectional diameter Di is smaller than the second cross-sectional diameter D2. The variable cross-sectional diameter generally enables conditioning of the stream of compressed air 18 as it passes from the high pressure air space 44 through the flow conditioning plate 102 and to the head end 46. For example, the flow conditioning passages 162 may reduce flow turbulences and / or reduce a flow pressure between the high pressure air space 44 and the head end 46, thereby improving mixing with the fuel prior to combustion.
    In various embodiments, as shown in FIG. 3, the inner band portion 152 of the flow conditioning plate 102 at least partially defines an exhaust duct 166. The exhaust duct 166 is in fluid communication with the impingement air plenum 146 and an exhaust vent 168. In various embodiments, the fluid conduit 148 extends within the shell 104 and / or the cooling air collecting space 110 between the baffle 120 and the inner band portion 152 of the flow conditioning plate 102. In this way, the fluid conduit 148 provides fluid communication between the baffle chamber 146 and the exhaust duct 166 ,
    In one embodiment, as shown in FIG. 3, the exhaust vent 168 is disposed along and / or passes through a radially outer surface 170 of the inner band section 152 upstream of the inlets 164 of the flow conditioning passages 162. In one embodiment, as shown in FIG. 7, the exhaust vent 168 is disposed along a radially outer surface 172 of the inner band portion 152 downstream of the outlets 165 of the flow conditioning passages 162 and / or the downstream side 160 of the annular portion 156. In one embodiment, as shown in FIG. 7, the inner band portion 152 at least partially defines a cooling air outlet space 174 that extends substantially circumferentially within the inner band portion 152. The cooling air outlet space 174 is in fluid communication with the exhaust duct 166 and the exhaust outlet 168. The cooling air outlet space 174 may be in fluid communication with a plurality of exhaust passages and / or a plurality of exhaust outlets 168.
    In certain embodiments, as shown in FIG. 8, the exhaust duct 166 is defined at least in part within the annular portion 156 of the flow conditioning plate 102. In one embodiment, the exhaust outlet 168 is disposed within a flow conditioning passage 162 of the plurality of flow conditioning passages 162. In one embodiment, the exhaust outlet 168 is disposed within a variable cross-sectional diameter flow conditioning passage 162. For example, a first cross-sectional diameter Di is smaller or smaller than a second cross-sectional diameter D2.
    In certain embodiments, as shown in FIG. 9, the exhaust duct 166 is defined at least in part within the annular portion 156 of the flow conditioning plate 102, and the exhaust vent 168 is disposed along the downstream side 160 of the annular portion 156. In this manner, the exhaust duct 166 extends through a portion of the annular portion 156 and is fluidly isolated from the flow conditioning passages 162 (not shown). In one embodiment, as shown in FIG. 9, the exhaust duct 166 and / or the exhaust space 174 may be in fluid communication with a plurality of exhaust outlets 168 disposed along the downstream side 160 of the annular portion 156.
    FIG. 10 provides a side cross-sectional view of a portion of the combustor cap assembly 100 according to at least one embodiment of the present invention. FIG. 11 provides a cross-sectional perspective view, downstream or front, of a portion of the combustor cap assembly 100 with the jacket 104, the baffle plate 120 12 provides a front cross-sectional view of the combustor cap assembly shown in FIG. 11, and FIG. 13 provides a side cross-sectional view of a portion of combustor cap assembly 100 according to at least one embodiment of the present invention. In various embodiments, as illustrated in FIGS. 3, 10, 11, 12, and 13, the flow conditioning plate 102 defines a cooling air passage 176 that provides cooling air flow from the high pressure cooling chamber 44 (FIG. 2) into the cooling air plenum 110. In other embodiments, as illustrated in FIGS. 11 and 12, the flow conditioning plate 102 defines a plurality of cooling air passages 176 annularly spaced at intervals within the flow conditioning plate 102.
    In certain embodiments, as shown in FIGS. 3, 10, 11, 12, and 13, the cooling air passage 176 extends through the outer band portion 154, the annular portion 156, and the inner band portion 152. In certain embodiments, an inlet 178 defined in the cooling air passage 176 along a radially outer surface 180 of the outer band portion 154. An outlet 182 from the cooling air passage 176 is defined along a radially inner surface 184 of the inner band portion 152.
    In certain embodiments, the cooling air passage 176 is fluidly isolated from the individual flow conditioning passages 162. In one embodiment, as shown in FIGS. 3, 11 and 12, the cooling air passage 176 is angled or at an angle with respect to an axial centerline of the cap assembly 102 within the flow conditioning plate 102 to angularly rotate the cooling air flow within the cooling air plenum 112 to rent.
    In one embodiment, as illustrated in FIGS. 12 and 13, the flow conditioning plate 102 defines at least one bleed passage 186. In certain embodiments, the flow conditioning plate 102 defines a plurality of bleed passages 186 in fluid communication with the cooling air passage 176. The bleed passage 186 is formed in the annular portion 156 and is in fluid communication with the cooling air passage 176. As shown in FIG. 13, the bleed passage 186 provides fluid communication from the cooling air passage 176 through the downstream side 160 of the annular portion 156.
    During operation, the compressed air 18 flows from the high pressure air space 44 along the annular flow passage 54 through the flow conditioning passages 162 of the flow conditioning plate 102 and into the head end portion 46 of the combustor 24. The flow conditioning passages 162 may condition uneven flow characteristics or distributions upstream of the head end portion 46 and thereby make the flow of compressed air more uniform prior to entering the combustor cap assembly 100 and / or the fuel nozzle 48. A first portion of the compressed air 18 passes through the fuel nozzle 48 or nozzles where it is mixed with fuel prior to ignition upstream of the combustor 50.
    FIG. 14 provides a flow schematic of a portion of the combustor cap assembly 100 during operation in accordance with an embodiment of the present invention. As shown in FIG. 14, a second portion of the compressed air 18 is directed from the high pressure air space 44 (FIG. 2) via the cooling flow passage 176 into the cooling air plenum 112. In one embodiment, at least a portion of the compressed air 18 is bleeded out of the cooling flow passage 176 via the bleed air passage 186 (FIGS. 12 and 13) and flows downstream from the flow conditioning plate 102 toward the head end portion 46 of the combustion chamber 24. In one embodiment, in FIG the cooling air passage 176 is angled within the flow conditioning plate 102, as shown in Fig. 12, the compressed air 18 within the cooling air collecting space 112 is swirled.
    As shown in FIG. 14, the second part of the compressed air 18 flows out of the cooling air plenum 112 via the impingement cooling holes 130 into the impingement air plenum 146. The impingement cooling holes 130 direct jets of compressed air 18 onto the impingement side 142 of the cap plate 140. As a result Thermal energy is transferred from the cap plate 140 to the compressed air 18, thereby providing baffle or convection cooling of the cap plate 140, thereby producing cooling exhaust air 188 within the baffle air collection chamber 146. The cooling exhaust air 188 then flows out of the impingement air plenum 146 via the cooling flow recirculation passage 132 and flows through the cooling air plenum 110 via the fluid line 148. The fluid line 148 fluidly isolates the cooling exhaust air 188 from the compressed air 18 flowing in the cooling air plenum 110. The cooling exhaust air 188 then exits the fluid line 148 and enters the exhaust duct 166.
    In various embodiments, the cooling exhaust air 188 flows out of the exhaust duct 166 through the exhaust outlet 168 and into the annular flow passage 54 where it is mixed with compressed air 18 from the high pressure air space 44 to burn with the fuel before combustion To be mixed in advance. In one embodiment, as shown in FIG. 14, the cooling exhaust air 188 is directed through the exhaust outlet 168 upstream of the inlets 164 into the flow conditioning passages 162 of the annular section 156. In one embodiment, as shown in FIG. 7, the cooling exhaust air 188 is directed through the exhaust outlet 168 downstream of the flow conditioning passages 162 of the annular portion 156. In another embodiment, as shown in FIG. 8, the cooling exhaust air 188 is directed through an exhaust outlet 168 disposed within at least one of the flow conditioning passages 162. In another embodiment, as shown in FIG. 9, the cooling exhaust air 188 is directed through an exhaust outlet 168 disposed on the downstream side 160 of the annular portion 156.
    The specification uses examples which disclose the invention, including the best mode, and seek to enable one skilled in the art to practice the invention, including making and using any devices or systems and carrying out 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 100 includes a baffle plate 120 coupled to an annular shell 104 and a cap plate 140 coupled to the baffle plate 120 to define an impingement air space 146 therebetween. The combustor cap assembly 100 further includes a flow conditioning plate 102 coupled to a forward end portion 114 of the shell 104. The flow conditioning plate 102 has an inner band portion 152, an outer band portion 154, and an annular portion 156. The annular portion 156 defines a plurality of flow conditioning passages 162. The inner band portion 152 at least partially defines a cooling air plenum 110 within the combustor cap assembly 100. The inner band portion 152 further defines an exhaust duct 166 which is in fluid communication with the impingement air plenum 146 and with an exhaust vent 168 , The flow conditioning plate 102 further defines a cooling air passage 176 that provides cooling air flow into the cooling air plenum 110.
    component list
    [0069]<Tb> reference numeral <September> Component<Tb> 10 <September> Gas Turbine<Tb> 12 <September> inlet section<Tb> 14 <September> working fluid / air<Tb> 16 <September> compressor<tb> 18 <SEP> Compressed air<Tb> 20 <September> Fuel<Tb> 22 <September> fuel source<Tb> 24 <September> combustion chambers<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> Hochdrucklufträum<Tb> 46 <September> head end<Tb> 48 <September> fuel<Tb> 50 <September> combustion chamber<Tb> 52 <September> focal combs liner<tb> 54 <SEP> Annular flow passage<Tb> 56 <September> impingement sleeve / bush<tb> 57-99 <SEP> Not used<Tb> 100 <September> focal Kammer cap assembly<Tb> 102 <September> flow conditioning plate<Tb> 104 <September> coat<tb> 106 <SEP> Secondary Coat<tb> 108 <SEP> Rear End Section<Tb> 110 <September> cooling air plenum<tb> 112 <SEP> Front End Section<tb> 114 <SEP> First / Front End Section<tb> 116 <SEP> Second / Rear End Section<Tb> 118 <September> flange<Tb> 120 <September> Flapper<Tb> 122 <September> fuel nozzle passage<tb> 124 <SEP> First / upstream page section<tb> 126 <SEP> Second / downstream side portion<tb> 128 <SEP> Outer band section<Tb> 130 <September> impingement cooling holes<Tb> 132 <September> cooling flow return passage<Tb> 134 <September> inlet<tb> 136 <SEP> Eclipse area<Tb> 138 <September> cooling passage<Tb> 140 <September> cap plate<Tb> 142 <September> Impact page<tb> 144 <SEP> Opposite / Hot Page<Tb> 146 <September> impingement air plenum<Tb> 148 <September> fluid line<Tb> 150 <September> outlet<tb> 152 <SEP> Inner band section<tb> 154 <SEP> Outer band section<tb> 156 <SEP> Annular section<tb> 158 <SEP> Upstream page<tb> 160 <SEP> Downstream page<Tb> 162 <September> flow passage<Tb> 164 <September> inlet<Tb> 165 <September> outlet<Tb> 166 <September> exhaust air duct<Tb> 168 <September> exhaust outlet<tb> 170 <SEP> Radial outer surface<tb> 172 <SEP> Radial outer surface<Tb> 174 <September> Kühlluftauslassraum<Tb> 176 <September> cooling air passage<Tb> 178 <September> inlet<tb> 180 <SEP> Radial outer surface<Tb> 182 <September> outlet<tb> 184 <SEP> Radial inner surface<Tb> 186 <September> bleed air passage<tb> 188 <SEP> Cooling exhaust air
    权利要求:
    Claims (10)
    [1]
    A combustor cap assembly (100) comprising:a baffle plate (120) coupled to an annular shell (104);a cap plate (140) coupled to the baffle plate (120), the cap plate (140) and the baffle plate (120) defining a baffle collecting space (146) therebetween; anda flow conditioning plate (102) coupled to a forward end portion (112) of the shell (104), the flow conditioning plate (102) having an inner band portion (152), an outer band portion (154) and an annular band portion (156), extending radially therebetween, the annular band portion (156) defining a plurality of flow conditioning passages (162), the inner band portion (152) at least partially defining a cooling air plenum (110) within the combustor cap assembly (100);wherein the inner band portion (152) of the flow conditioning plate (102) at least partially defines an exhaust duct (166) in fluid communication with the impingement air plenum (110) and an exhaust vent (168);wherein the flow conditioning plate (102) defines a cooling air passage (176) that provides cooling air flow into the cooling air plenum (110).
    [2]
    The combustor cap assembly (100) of claim 1, wherein the cooling air passage (176) extends through the outer band portion (154), the annular portion (156) and the inner band portion (152).
    [3]
    The combustor cap assembly (100) of claim 1 or 2, wherein the cooling air passage (176) is fluidically isolated from each of the flow conditioning passages (162); and orwherein the cooling air passage within the flow conditioning plate is angled to impart an angular twist to the flow of cooling air within the cooling air collection space.
    [4]
    The combustor cap assembly (100) of any one of the preceding claims, further comprising a fluid conduit (148) extending within the shell (104) between the baffle plate (120) and the inner band portion (152) of the flow conditioning plate (102) the fluid line (148) provides fluid communication between the baffle plenum (146) and the exhaust duct (166).
    [5]
    The combustor cap assembly (100) of claim 4, wherein the exhaust vent (168) extends through a radially outer surface of the inner band portion upstream of the plurality of flow conditioning passages (162); orwherein the exhaust outlet (168) extends through a radially outer surface (170) of the inner band portion (152) downstream of the plurality of flow conditioning passages (162).
    [6]
    The combustor cap assembly (100) of any of claims 4 or 5, wherein the exhaust vent (168) is disposed within one or more flow conditioning passages (162) of the plurality of flow conditioning passages (162).
    [7]
    The combustor cap assembly of any one of the preceding claims, wherein the flow conditioning plate (102) defines a bleed passage (186) in fluid communication with the cooling air passage (176), the bleed passage (186) being formed in the annular portion (156).
    [8]
    The combustor cap assembly of claim 7, wherein the bleed passage (186) provides fluid communication through a downstream side (160) of the annular portion (156).
    [9]
    A gas turbine combustor (24) comprising:a fuel nozzle (48) extending axially within an outer housing (40), the outer housing (40) defining a high pressure air space (44) within the combustion chamber (24); anda combustor cap assembly (100) having a baffle plate (120) coupled to a rear end portion (116) of an annular shell (104), a cap plate (102) coupled to the baffle plate (120), the cap plate (120); 102) and the baffle plate (120) define a baffle plenum (146) between each other and a flow conditioning plate (104) coupled to a forward end portion (114) of the shell (104);wherein the flow conditioning plate (104) includes an inner band portion (152), an outer band portion (154) and an annular portion (156) extending radially therebetween, the annular portion (156) defining a plurality of flow conditioning passages (162) inner band portion (152) and theouter band portion (104) at least partially define a cooling air plenum (110);wherein the inner band portion (152) of the flow conditioning plate (102) at least partially defines an exhaust duct (166) in fluid communication with the impingement air plenum (146) and an exhaust vent (168);wherein the flow conditioning plate (102) defines a cooling air passage (176) that provides cooling air flow through the flow conditioning plate (102) into the cooling air plenum (110).
    [10]
    10. Gas turbine (10), comprising:a compressor section;a combustion section downstream of the compressor section, the combustion section including an outer housing (40) surrounding a combustion chamber (24), the outer housing (40) forming a high pressure air space (44) in fluid communication with the compressor section; anda turbine section disposed downstream of the combustion section;wherein the combustor (24) includes a fuel nozzle (48) extending axially within the outer housing (40) and a combustor cap assembly (100) surrounding at least a portion of the fuel nozzle (48) along the circumference;wherein the combustor cap assembly (100) includes a baffle plate (120) coupled to a rearward end portion (116) of an annular shell (104), a capping plate (102) coupled to the baffle plate (120), and a flow conditioning plate (104 ) coupled to a forward end portion (114) of the shell (104), the capping plate (102) and the baffle plate (120) defining an impingement air collecting space (146) therebetween;wherein the flow conditioning plate (104) includes an inner band portion (152), an outer band portion (154) and an annular portion (156) extending radially therebetween, the annular portion (156) defining a plurality of flow conditioning passages (162) inner band portion (152) and outer band portion (104) at least partially define a cooling air plenum (110);wherein the inner band portion (152) of the flow conditioning plate (102) at least partially defines an exhaust duct (166) in fluid communication with the impingement air plenum (146) and an exhaust vent (168);wherein the flow conditioning plate (102) defines a cooling air passage (176) providing cooling air flow from the high pressure air space (44) through the flow conditioning plate (102) into the cooling air plenum (110).
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    同族专利:
    公开号 | 公开日
    US20160054002A1|2016-02-25|
    DE102015113418A1|2016-02-25|
    JP6659269B2|2020-03-04|
    CN105371303A|2016-03-02|
    JP2016044680A|2016-04-04|
    CN105371303B|2020-10-27|
    US9964308B2|2018-05-08|
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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
    US14/462,637|US9964308B2|2014-08-19|2014-08-19|Combustor cap assembly|
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