• 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 combustion chamber flame tube is disclosed. The combustor liner has an upstream portion, a downstream end portion (72) extending from the upstream portion along a generally longitudinal axis of the combustion chamber in the combustor when the combustor flame tube is installed, and a cover layer (78) having an inner surface (78). 74) of the downstream end portion (72) is connected. The downstream end portion (72) has the inner surface (74) and an outer surface (76), the inner surface (74) having a number of microchannels (80). The downstream end portion (72) further includes a number of passages (90) extending between the inner surface (74) and the outer surface (76). The plurality of microchannels (80) are in fluid communication with the plurality of passages (90) and configured to pass a coolant (64) therethrough which cools the combustor flame tube.
    公开号:CH703549B1
    申请号:CH00966/11
    申请日:2011-06-07
    公开日:2016-01-15
    发明作者:Benjamin Paul Lacy；Mert Enis Berkman
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Field of the invention
    The subject matter disclosed herein relates generally to gas turbine systems, and more particularly to a system for cooling a fire tube in a combustor of a gas turbine system.
    Background of the invention
    Gas turbine systems are widely used in areas such as power generation. A conventional gas turbine system includes a compressor, a combustor, and a turbine. During operation of the gas turbine system, various components in the system are exposed to high temperature flows which may cause the components to fail. Because higher temperature flows generally result in increased performance, increased efficiency, and increased output of the gas turbine system, the components exposed to high temperature flows must be cooled to allow the gas turbine system to operate at elevated temperatures.
    [0003] A gas turbine system component that should be cooled is the combustor liner or flame tube. When high temperature flows generated by the combustion of an air-fuel mixture in the combustion chamber are passed through the combustion chamber, the high temperature flows heat the flame tube, which could lead to failure of the flame tube. In particular, the downstream end portion of the fire tube may be connected to other components of the combustion chamber, such as e.g. a transition element, connected via a seal and therefore not be exposed to the various air currents that can cool the rest of the combustion chamber fire tube. Thereby, the downstream end portion may be a life limiting portion of the flame tube which could fail due to being exposed to high temperature flows. Thus, the downstream end portion must be cooled to increase the life of the fire tube.
    In the art, various strategies for cooling the downstream end portion of the flame tube of a combustion chamber are known. For example, For example, a portion of the air flow supplied from the compressor through fuel nozzles into the combustion chamber may be passed through an annular enclosure to channels formed in the outer surface of the downstream end portion of the flame tube. As the airflow is directed through these channels, the airflow may cool the downstream end portion. However, the cooling of the downstream end portion by the air flow in these channels is generally limited by the thickness of the downstream end portion, which reduces the proximity of the channels to the high temperature flows within the flame tube, thereby reducing the cooling efficiency of the channels. Further, cooling of the fire tube by passages formed in the outer surface of the downstream end portion of the fire tube generally results in comparatively low heat transfer rates and non-uniform flame tube temperature profiles.
    Accordingly, an improved cooling system for a flame tube of a combustion chamber would be desirable in the art. For example, a cooling system would be advantageous which provides relatively high heat transfer rates and relatively uniform temperature profiles in the downstream end portion of the fire tube. In addition, a cooling system for a fire tube is desirable which reduces the amount of cooling flow needed to cool the fire tube.
    Brief description of the invention
    The invention provides a combustion chamber flame tube according to claim 1.
    Further variants of the invention are shown in the dependent claims 2 to 15.
    These and other features, aspects, and advantages of the present invention will become better understood with reference to the following description and appended claims.
    Brief description of the drawings
    A complete and preliminary disclosure of the present invention, which includes the best mode thereof and which is directed to a person skilled in the art, is set forth in the description which refers to the attached figures:<Tb> FIG. 1 <SEP> is a schematic representation of a gas turbine system;<Tb> FIG. FIG. 2 <SEP> is a side sectional view of one embodiment of various components of the gas turbine system of the present disclosure; FIG.<Tb> FIG. 3 <SEP> is a perspective view of an embodiment of the downstream end portion of the fire tube of the present disclosure;<Tb> FIG. FIG. 4 is an exploded perspective view of another embodiment of the downstream end portion of the fire tube of the present disclosure; FIG.<Tb> FIG. FIG. 5 is an exploded perspective view of another embodiment of the downstream end portion of the fire tube of the present disclosure; FIG.<Tb> FIG. FIG. 6 is a perspective view of another embodiment of the downstream end portion of the fire tube of the present disclosure; FIG.<Tb> FIG. FIG. 7 is a perspective view of another embodiment of the downstream end portion of the fire tube of the present disclosure; FIG.<Tb> FIG. 8 <SEP> is a sectional view of an embodiment of the downstream end portion of the fire tube of the present disclosure;<Tb> FIG. 9 <SEP> is a sectional view of another embodiment of the downstream end portion of the fire tube of the present disclosure; and<Tb> FIG. 10 <SEP> is a sectional view of another embodiment of the downstream end portion of the fire tube of the present disclosure.
    Detailed description of the invention
    [0010] Reference will now be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is given only for the purpose of illustrating the invention, but not for the purpose of limiting the invention.
    FIG. 1 is a schematic illustration of a gas turbine system 10. The system 10 may include a compressor 12, a combustor 14, a turbine 16, and a fuel nozzle 20. Furthermore, the system 10 may include a number of compressors 12, combustors 14, turbines 16, and fuel nozzles 20. The compressor 12 and the turbine 16 may be coupled by a shaft 18. The shaft 18 may be a single shaft or a number of shaft segments connected together to form the shaft 18.
    The gas turbine system 10 may comprise a liquid or gaseous fuel, such as e.g. Use natural gas or a hydrogen-rich syngas to operate the system 10. The fuel nozzles 20 may be e.g. receive a supplied fuel 22 and an oxidizing medium 24 (see FIG. 2) from the compressor 12, mix the supplied fuel 22 with the oxidizing medium 24 to form a coolant-fuel mixture, and the coolant-fuel mixture the combustion chamber 14 deliver. The oxidizing medium 24 may be air in exemplary embodiments. It should be appreciated, however, that the oxidizing medium 24 of the present disclosure is not limited to air but could be any suitable fluid. The coolant-fuel mixture received by the combustor 14 may combust within the combustor 14, creating a hot pressurized exhaust or stream 26 of hot gas. The combustor 14 may direct the hot gas stream 26 into the turbine 16 through a hot gas path 28 in the combustor 14. As the hot gas stream 26 passes through the turbine 16, the turbine 16 may cause the shaft 18 to rotate. The shaft 18 may be connected to various components of the turbine system 10 including the compressor 12. Thus, the rotation of the shaft 18 may actuate the compressor 12, thereby compressing the oxidizing medium 24.
    As a result, the oxidizing medium 24 may enter the turbine system 10 during operation and be pressurized in the compressor 12. The oxidizing medium 24 may then be mixed in the combustion chamber 14 for combustion with fuel 22 supplied. The fuel nozzles 20 may be e.g. introduce a fuel-coolant mixture into the combustion chamber 14 in an appropriate ratio for optimal combustion, optimum emissions, fuel economy and power output. The combustion may generate a hot gas stream 26 that may be supplied to the turbine 16 through the combustor 14.
    As shown in Fig. 2, the combustion chamber is generally connected in fluid communication with the compressor 12 and the turbine 16. The compressor 12 may include a diffuser 30 and an exit chamber 32, which are connected in fluid communication with each other to allow the routing of the oxidizing medium 24 to the combustion chamber 14. After the oxidizing medium 24 has been compressed in the compressor 12, it may e.g. flow through the diffuser 30 and the discharge chamber 32 are supplied. The oxidizing medium 24 may then flow out of the exit chamber 32 through the fuel nozzles 20 to the combustor 14.
    The combustion chamber 14 may have a cover plate 34 at the upstream end of the combustion chamber 14. The cover plate 34 may at least partially support the fuel nozzles 20 and provide a path through which oxidizing medium 24 and supplied fuel 22 may be directed to the fuel nozzles 20.
    The combustor may include a hollow annular wall configured to provide oxidizing medium 24. The combustion chamber 14 may be e.g. a flame tube 40, which is arranged in a flow sleeve 42. The arrangement of the flame tube 40 and flow sleeve 42, as shown in FIG. 2, is generally concentric and may form therebetween an annular channel or flow path 44. In certain embodiments, the flow sleeve 42 and the flame tube 40 may form a first or upstream hollow annular wall of the combustion chamber 14. The flow sleeve 42 may include a number of inlets 46 that provide a flow path for at least a portion of the oxidizing medium 24 from the compressor 12 through the exit chamber 32 into the flow path 44. In other words, the flow sleeve 42 may be perforated with a pattern of apertures to form a perforated annular wall. The interior of the flame tube 40 may form a substantially cylindrical or annular combustion chamber 48 and at least partially form the hot gas path 28 through which the hot gas stream 26 may be passed.
    Downstream of the flame tube 40 and the flow sleeve 42, a baffle sleeve 50 may be connected to the flow sleeve 42. The flow sleeve 42 may include a mounting flange 52 which is adapted to receive a fastener 54 of the impact sleeve 50. A transition element 56 may be disposed within the impingement sleeve 50 so that the impact sleeve 50 surrounds the transition element 56. A concentric arrangement of the impingement sleeve 50 and the transition element 56 may form an annular channel or flow path 58 between them. The impingement sleeve 50 may include a number of inlets 60 that provide a flow path for at least a portion of the oxidizing medium 24 from the compressor 12 through the exit chamber 32 into the flow path 58. In other words, the impingement sleeve 50 may be perforated with a pattern of apertures to form a perforated annular wall. An internal cavity 62 of the transition element 56 may further form the hot gas path 28 through which the hot gas stream 26 may be directed from the combustion chamber 48 into the turbine 16.
    As shown, the flow path 58 is connected in fluid communication with the flow path 44. Thus, the flow paths 44 and 58 together form a flow path configured to supply oxidizing medium 24 from the compressor 12 and the discharge chamber 32 to the fuel nozzles 20, the combustor 14 also being cooled.
    As explained above, the turbine system 10 may in operation draw in an oxidizing medium 24 and supply the oxidizing medium 24 to the compressor 12. The compressor 12, which is driven by the shaft 18, can rotate and compress the oxidizing medium 24. The compressed oxidizing medium 24 may then be discharged into the diffuser 30. The majority of the compressed oxidizing medium 24 may thereafter be discharged from the compressor 12 via the diffuser 30 through the discharge chamber 32 into the combustion chamber 14. In addition, a small portion (not shown) of the compressed oxidizing medium 24 may be directed downstream for cooling other components of the turbine plant 10.
    A portion of the compressed oxidizing medium 24 within the exit chamber 32 may flow into the flow path 58 via the inlets 60. As discussed below, a portion of the oxidizing medium 24, shown as a coolant 64, may be directed from the flow path 58 to the flame tube 40 and serve to cool the flame tube 40. The remaining oxidizing medium 24 in the flow path 58 may then be passed upstream through the flow path 44, such that the oxidizing medium 24 is passed over the flame tube 40. Thus, a flow path in the upstream direction is formed by the flow path 58 (formed from the impingement sleeve 50 and the transition member 56) and the flow path 44 (formed from the flow sleeve 42 and the flame tube 40). Accordingly, the flow path 44 may receive oxidizing medium 24 from both the flow path 58 and the inlets 46. The oxidizing medium 24 may thereafter be directed through the flow path 44 upstream of the fuel nozzles 20 where the oxidizing medium 24 may be mixed with the supplied fuel 22 and ignited within the combustion chamber 48 to produce the hot gas stream 26. The hot gas stream 26 may then be passed through the combustion chamber 48 along the hot gas path 28 into the transition member cavity 62 and through a turbine nozzle 66 to the turbine 16.
    Figures 3-7 illustrate perspective views of various embodiments of portions of the fire tube 40 in accordance with the present disclosure. The fire tube 40 may generally include an upstream portion 70 and a downstream end portion 72 extending from the upstream portion 70 along one of the upstream portions extending generally in the longitudinal direction of the combustion chamber axis 73 extends. The downstream end portion 72 may be that part of the flame tube 40 that is connected to the transition element 56. Furthermore, the downstream end portion 72 may include an inner surface 74 and an outer surface 76. The inner surface 74 may be the surface generally associated with the hot gas path 28, while the outer surface 76 may be the surface generally associated with the transition element 56. It should be appreciated that the upstream portion 70 and the downstream end portion 72 may have any suitable structure, such as the like. can have any suitable lengths, radii and tapered or non-tapered sections.
    The fire tube 40 according to the present disclosure may further include a cover layer 78. The cover layer may be bonded to the inner surface 74 of the downstream end portion 72, as explained below.
    The inner surface 74 of the downstream end portion 72 may form a number of microchannels 80. The microchannels 80 may be configured to allow a coolant 64 to flow therethrough which generally cools the downstream end portion 72 and the flame tube. The microchannels 80 may be e.g. generally open channels formed and formed on the inner surface 74. In addition, the cover layer 78 bonded to the inner surface 74 may cover the microchannels 80 and further form in exemplary embodiments. The coolant 64 directed through the microchannels 80 may flow through the microchannels 80 between the inner surface 74 and the cover layer 78 as discussed below, cooling the downstream end portion 72 and the cover layer 78, and thereafter discharging out of the microchannels 80 it is explained below. The microchannels 80 may be formed in the downstream end portion 72, e.g. laser machining, water jet machining, electrochemical machining (ECM), spark erosion (EDM), photolithography, or any other method suitable for providing suitable microchannels 80 with adequate masses and tolerances.
    The microchannels 80 may have depths 82 in the range of from about 0.2 mm to about 3 mm, such as 2 mm. from about 0.5 mm to about 1 mm. Furthermore, the microchannels 80 may have widths 84 in the range of about 0.2 mm to about 3 mm, such as, e.g. from about 0.5 mm to about 1 mm. Furthermore, the microchannels 80 may have lengths 86. The lengths 86 of the microchannels 80 may be approximately equal to the length of the downstream end portion 72 or less than or greater than the length of the downstream end portion 72. It should further be appreciated that the depths 82, widths 84 and lengths 86 of the microchannels 80 need not be identical for the individual microchannels 80, but may vary between the microchannels 80.
    In an exemplary embodiment, the depth 82 of each of the plurality of microchannels 80 may be substantially constant over the length 86 of the microchannel 80. However, in another exemplary embodiment, the depth 82 of each one of the plurality of microchannels 80 could taper. The depth 82 of the individual ones of the plurality of microchannels 80 could be e.g. be reduced over the length 86 of the microchannel 80 in the flow direction of the coolant 64 through the microchannel 80. Alternatively, the depth 82 of the individual ones of the plurality of microchannels 80 could be increased over the length 86 of the microchannel 80 in the flow direction of the coolant through the microchannel 80. It should be appreciated that the depth 82 of each of the plurality of microchannels 80 may vary in any manner across the length 86 of the microchannel 80 by being reduced or increased, as desired. Furthermore, it should be appreciated that different microchannels 80 may have substantially constant depths 82, while other microchannels may have tapered depths 82.
    In an exemplary embodiment, the width 84 of each one of the plurality of microchannels 80 may be substantially constant over the length 86 of the microchannel 80. However, in another exemplary embodiment, the width 84 of each of the plurality of microchannels 80 may be tapered. The width 84 of a single one of the plurality of microchannels 80 may be e.g. be reduced over the length 86 of the microchannel 80 in the flow direction of the coolant 64 through the microchannel 80. Alternatively, the width 84 of each one of the plurality of microchannels 80 over the length 86 of the microchannel 80 in the flow direction of the coolant 64 through the microchannel 80 could also be increased. It should be appreciated that the width 84 of each of the plurality of microchannels 80 may vary in any manner across the length 86 of the microchannel 80 by being scaled down and enlarged, as desired. Furthermore, it should be appreciated that different microchannels 80 may have substantially constant widths 84, while other microchannels 80 may have tapered widths 84.
    The microchannels 80 may have cross-sections of any geometric shape, e.g. a rectangular, oval, triangular or any other geometric shape suitable for supplying the flow of coolant 64 through the microchannel 80. It should be appreciated that some microchannels 80 may have cross sections with certain geometric shapes, while other microchannels 80 could have cross sections with a variety of other geometric shapes.
    In certain embodiments, the microchannels 80 may extend rectilinearly through the downstream end portion 72 with respect to the longitudinal axis 73. Alternatively, the microchannels 80 may extend helically about the downstream end portion 72 with respect to the longitudinal axis 73. In further alternative embodiments, the microchannels 80 may be generally curved, sinusoidal, or serpentine microchannels 80.
    In exemplary embodiments, each of the plurality of microchannels 80 may have a substantially smooth surface. The surface of the microchannels 80 may be e.g. be substantially or completely free of protrusions, depressions or surface structures. However, in an alternative embodiment, each one of the plurality of microchannels 80 may have a surface having a number of surface structures. The surface structures may be discrete protrusions extending out of the surface of the microchannel 80. The surface structures may e.g. rib-shaped protrusions, cylindrical protrusions, annular protrusions, angular protrusions, raised portions between transverse grooves formed in the microchannel 80, or any combination thereof, as well as any other suitable geometric shapes. It should be appreciated that the dimensions of the surface features may be selected to generally optimize the cooling of the downstream end portion 72 and the flame tube 40 while meeting the geometric requirements for the microchannels 80.
    In some embodiments, each of the microchannels 80 may be a single discrete microchannel 80. However, in other embodiments, each of the microchannels 80 or any part of the microchannels 80 may branch off from individual microchannels 80 to form multiple microchannel branches.
    The downstream end portion 72 may further form a number of passages 90. The passages 90 may extend between the inner surface 74 and the outer surface 76 of the downstream end portion 72. The plurality of microchannels 80 may be in fluid communication with the plurality of passages 90. The passages 90 may be e.g. in the downstream end portion 72 in generally annular rows as shown in Figs. 3, 4 and 5 and / or in relatively rectilinear patterns as shown in Figs. 4 and 5 or in any other suitable patterns or fields. The coolant 64, which is supplied to the flame tube 40, can thus be passed through the passages 90 and the microchannels 80 are supplied.
    Furthermore, each of the plurality of passages 90 may be configured to provide the cover layer 78 with impingement cooling. The passages 90 may be e.g. generally at a right angle with respect to the cover layer 78 in the downstream end portion 72. Thus, as the coolant 64 flows through the passages 90 and is supplied to the microchannels 80, the coolant 64 may be discharged from the passages 90 and impinge on the cover layer 78, causing impingement cooling of the cover layer 78.
    After the coolant 64 flows through the microchannels 80 and cools the downstream end portion 72 and the flame tube 40 and cools the cover layer 78, the coolant 64 may be discharged from the microchannels 80. In one embodiment, as shown in Figs. 3, 4 and 5, the coolant 64 may be e.g. are discharged directly from the microchannels 80. The coolant 64 can thereby flow from the microchannels 80 directly into the hot gas path 28.
    As shown in FIGS. 6 and 7, alternatively, the coolant 64 may be dispensed into the hot gas path 28 adjacent the cover layer 78. The cover layer 78 may e.g. have multiple outlets 92. Furthermore, the inner surface 74 of the downstream end portion 72 may form a chamber 94 or a number of chambers 94. As shown in FIG. 7, the chamber 94 or chambers 94 may be configured to receive coolant from the plurality of microchannels 80 or at least a portion of the plurality of microchannels 80. Generally, the chamber 94 or the chambers 94 may be relative to the hot gas stream 26, e.g. annularly formed around the downstream end of the downstream end portion 72 and in fluid communication with the plurality of microchannels 80. Thereby, the coolant 64 flowing through the microchannels 80 may exit the microchannels 80 into the chamber 94 and, in exemplary embodiments, may be distributed throughout the chamber before being discharged from the downstream end portion 72.
    Each of the outlets 92 may be in fluid communication with one of the plurality of microchannels 80, as shown in FIG. 6, or with a chamber 94, as shown in FIG. Furthermore, each of the outlets 92 may be configured to receive coolant from the plurality of microchannels 80 or from the chamber 94 and to allow the coolant 64 to exit adjacent to the cover layer 78. The outlets 92 may be e.g. generally between an inner surface 102 and an outer surface 104 (see FIGS. 8-10) of the cover layer 78 and in fluid communication with the microchannels 80 or the chamber 94. The hot gas stream 26 may flow past the inner surface 102 of the cover layer 78 at a pressure generally lower than the pressure in the passages 90 and microchannels 80. This pressure difference may cause the coolant 64 flowing through the microchannels 80 to flow in and out of the microchannels 80 into the outlets 92 and exit the outers 92 into the hot gas path 28 adjacent the inner surface 102 of the cover layer 78 , It should be appreciated that each microchannel 80 may be connected to one or more of the outlets 92. It should also be appreciated that the outlets 92 may be oriented at any angle relative to the microchannels 80 and / or the chamber 94. In addition, it should be appreciated that the outlets 92 may have generally circular or oval cross sections, generally rectangular cross sections, generally triangular cross sections, or any other suitably shaped polygonal cross sections.
    The downstream end portion 72 and the cover layer 78 may each comprise a single material, such as e.g. a substrate or a coating, or each containing a number of materials, e.g. several substrates and coatings. In an exemplary embodiment, the downstream end portion 72 may be e.g. as shown in Fig. 8, a flame tube substrate 110 have. The substrate 110 may be e.g. a nickel, cobalt or iron base superalloy. The alloys may e.g. be poured or kneading superalloys. It should be appreciated that the flame tube substrate 110 according to the present disclosure is not limited to the above materials but could be any suitable material for any portion of a flame tube 40.
    As shown in FIG. 8, the cover layer 78 may further include a metal coating 112. According to an exemplary aspect of an embodiment, the metal coating 112 could be any metal or metal alloy based coating, such as a metal or metal alloy based coating. a coating based on nickel, cobalt, iron, zinc or copper.
    Alternatively, the cover layer 78 may include a tie layer 114. The tie layer 114 may be made of any suitable binder material. The tie layer 114 may be e.g. have the chemical composition MCrAl (X), where M is an element selected from the group consisting of Fe, Co and Ni, or a combination thereof, and (X) is an element selected from the group consisting of from gamma prime imagers, solid solution hardeners, eg of Ta, Re and reactive elements such as e.g. Y, Zr, Hf, Si, and grain boundary consolidators consisting of B, C and combinations thereof. The tie layer 114 may be applied to the downstream end portion 72, e.g. by a physical vapor deposition process such as electron beam evaporation, ion plasma arc evaporation or sputtering, or by another thermal spray process such as e.g. Air plasma spraying, high-speed oxyfuel or low-pressure plasma spraying are applied. Alternatively, tie layer 114 may comprise a diffusion aluminide bond coat, such as e.g. a coating having the chemical composition NiAl or PtAl, and the bonding layer 114 may e.g. be applied to the downstream end portion 72 by gas phase aluminization or chemical vapor deposition.
    Alternatively, the cover layer 78 may include a thermal barrier coating (TBC) 116. The TBC 116 may be made of any suitable thermal barrier material. For example, For example, the TBC 116 may be yttria-stabilized zirconia and may be applied to the downstream end portion 72 by a physical vapor deposition process or a thermal spray process. Alternatively, the TBC 116 may be a ceramic, such as a ceramic. a thin layer of zirconia oxidized by other refractory oxides, e.g. Oxides formed from elements of Groups IV, V and VI, or from oxides formed by elements of the lanthanide series, e.g. La, Nd, Gd, Yb and the like is modified.
    In other exemplary embodiments, the downstream end portion 72 and the cover layer 78 may each include a number of materials, such as described above, such as described above. a number of substrates and coatings. In one embodiment, as shown in FIG. 9, the downstream end portion 72 may include a flame tube substrate 110 and an end-portion bonding layer 114. The downstream end portion 72 may include the outer surface 76, and the end portion bonding layer 114 may include the inner surface 74. Thus, the plurality of microchannels 80 may be formed in the end-portion bonding layer 114. Further, the cover layer 78 may include an end portion TBC 116 as shown in FIG.
    In another embodiment, as shown in FIG. 10, the downstream end portion 72 may include a flame tube substrate 110, a tie layer 114, and a first TBC 116. The flame tube substrate 110 may include the outer surface 76, and the first TBC 116 may include the inner surface 74. Thus, the plurality of microchannels 80 may be formed in the first TBC 116. Furthermore, the cover layer 78 may include a second TBC 118 as shown in FIG.
    In addition, as shown in FIG. 8, the flame tube 40 may include an accessory TBC 116 disposed adjacent to the cover layer 78. Further, as shown in FIG. 8, the flame tube 40 may include an additive tie layer 114 disposed between the accessory TBC 116 and the cover layer 78. Alternatively, the cover layer 78 may include the metal coating 112, the bonding layer 114, and the TBC 116.
    In some embodiments, as shown in FIG. 4, the outer surface 76 of the downstream end portion 72 may include a number of channels 120. The channels 120 may be configured to pass a coolant 64 therethrough, which generally further cools the downstream end portion 72 and the flame tube 40. The channels 120 may be microchannels having any of the characteristics of the microchannels 80, or may be larger than the microchannels 80 and e.g. using any suitable technique, e.g. Milling, casting, molding or laser etching / cutting, be formed.
    The channels 120 may be connected in fluid communication with the microchannels 80. At least a portion of the passages 90 may be e.g. be in fluid communication with at least a portion of the channels 120. As shown in FIG. 4, various of the passages 90 may be formed in the channels 120. Thus, the coolant 64 flowing through the channels 120 may be received by the passages 90 and flow through the passages 90 to the microchannels 80.
    The combustor 14 according to the present disclosure may further include a seal ring 130 as shown in FIGS. 1-3. The seal ring 130 may seal between the flame tube 40, such as the downstream end portion 72, and the transition member 56.
    In exemplary embodiments, as shown in FIG. 5, seal ring 130 may further include a number of supply channels 132. The feed channels 132 may be configured to pass the coolant 64 therethrough. The coolant 64 flowing to the downstream end portion 72 may be e.g. at least partially flow over the sealing ring 130, and at least a portion of this coolant 64 can be received by the supply channels 132.
    Furthermore, at least a portion of the passages 90 formed in the downstream end portion 72 may be configured to receive a coolant 64 from the plurality of supply passages 132. Various of the passages 90 may e.g. may be formed in the downstream end portion 72 such that these passages 90 are generally covered by the seal ring 130 when the seal ring 130 is disposed adjacent to the downstream end portion 72. Thereby, the coolant 64, which flows through the supply channels 132 through the sealing ring 130, are taken up by these passages 90 and generally supplied to the microchannels 80. It should be appreciated, however, that further passages 90 could be formed in the downstream end portion 72 outside of the seal ring 130, and these passages 90 could accommodate still more coolant 64 than the coolant 64 supplied through the supply passages 132.
    In further exemplary embodiments, as shown in FIG. 4, the combustor may further include an annular shell 140. The annular sheath 140 may be connected between the flame tube 40, such as e.g. the downstream end portion 72, and the seal ring 130 may be arranged. The annular shell 140 may form a number of supply channels 142. The feed channels 142 may be configured to pass the coolant 64 therethrough. The coolant 64 flowing to the downstream end portion 72 may be e.g. at least partially over the annular sheath 140, and at least a portion of this coolant 64 may be received by the supply channels 142. In some embodiments, a seal plate 144 may be disposed at or adjacent the downstream end of the annular sheath 140. The seal plate 144 may prevent coolant 64 from flowing past the annular shell 140 and may promote the flow of coolant 64 to the supply channels 142.
    Furthermore, at least a portion of the passages 90 formed in the downstream end portion 72 may be configured to receive coolant 64 from the plurality of supply passages 142. For example, For example, various of the passages 90 may be formed in the downstream end portion 72 such that these passages 90 are generally covered by the annular shell 140 when the annular shell 140 is disposed adjacent to the downstream end portion 72. Thus, the coolant 64 that flows through the supply channels 142 through the annular shell 140 may then be received by these passages 90 and routed generally to the microchannels 80. It should be appreciated, however, that further passages 90 could be formed in the downstream end portion 72 outside the annular shell 140, and that these passages 90 could accommodate still more coolant 64 than the coolant 64 routed through the supply passages 142.
    Using microchannels 80 and passages 90 as described herein, cooling of the flame tube 40 is effected with a relatively high heat transfer rate and a relatively uniform temperature profile. As a result, the life of the fire tube 40 may be increased, and the flame tube 40 may further allow the use of higher temperature hot gas streams 26, thereby increasing the performance and efficiency of the system 10. Furthermore, the amount of coolant 64 needed for cooling can be reduced through the use of microchannels 80 and passages 90, thereby reducing the amount of oxidizing medium 24 diverted for cooling. Advantageously, this reduction can reduce NOx emissions and reduce cold traces adjacent to the flame tube 40 and transition member 56 further reducing CO values at part load operation.
    LIST OF REFERENCE NUMBERS
    [0051]<Tb> 10 <September> Gas Turbine System<Tb> 12 <September> compressor<Tb> 14 <September> combustion chamber<Tb> 16 <September> Turbine<Tb> 18 <September> wave<Tb> 20 <September> fuel<tb> 22 <SEP> Fuel supplied<tb> 24 <SEP> Oxidizing medium<Tb> 26 <September> hot gas flow<Tb> 28 <September> hot gas path<Tb> 30 <September> diffuser<Tb> 32 <September> exit chamber<Tb> 34 <September> cover plate<Tb> 40 <September> flame tube<Tb> 42 <September> flow sleeve<Tb> 44 <September> flow path<Tb> 46 <September> inlet<Tb> 48 <September> combustion chamber<Tb> 50 <September> impingement sleeve<Tb> 52 <September> mounting flange<Tb> 54 <September> fastener<Tb> 56 <September> transition element<Tb> 58 <September> flow path<Tb> 60 <September> inlet<Tb> 62 <September> transition element cavity<Tb> 64 <September> Coolant<Tb> 66 <September> turbine nozzle<tb> 70 <SEP> Upstream section<tb> 72 <SEP> Downstream End Section<Tb> 73 <September> longitudinal axis<tb> 74 <SEP> Inner surface<tb> 76 <SEP> Outer surface<Tb> 78 <September> topcoat<Tb> 80 <September> microchannel<Tb> 82 <September> Depth<Tb> 84 <September> Width<Tb> 86 <September> Length<Tb> 90 <September> passage<Tb> 92 <September> outlet<Tb> 94 <September> Chamber<tb> 102 <SEP> Inner surface<tb> 104 <SEP> Outer surface<Tb> 110 <September> liner substrate<Tb> 112 <September> metal coating<Tb> 114 <September> bonding layer<Tb> 116 <September> thermal barrier coating<tb> 118 <SEP> Second thermal barrier coating<Tb> 120 <September> Channel<Tb> 130 <September> sealing ring<Tb> 132 <September> supply channel<tb> 140 <SEP> Ring-shaped case<Tb> 142 <September> supply channel<Tb> 144 <September> seal plate
    权利要求:
    Claims (14)
    [1]
    A combustor flame tube (40) for the combustor (14) of a gas turbine, comprising:a portion (70) upstream of the combustion chamber (14) with respect to a hot gas path (28);a downstream end portion (72) extending in the combustion chamber (14) from the upstream portion (70) along a general longitudinal axis (73) of the combustion chamber (14) when the combustor flame tube (40) is installed, the downstream end portion (72 ), an inner surface (74) and an outer surface (76), wherein the inner surface (74) has a number of microchannels (80), and the downstream end portion (72) further comprises a number of passages (90) extending between the inner surface (74) and the outer surface (76), the plurality of microchannels (80) being in fluid communication with the plurality of passages (90); anda cover layer (78) connected to the inner surface (74) of the downstream end portion (72),wherein the plurality of microchannels (80) are configured to pass a coolant (64) therethrough that cools the fire tube (40).
    [2]
    A combustor flame tube (40) according to claim 1, wherein the cover layer (78) is a metal coating (112), a bonding layer (114) or a thermal barrier coating (116).
    [3]
    The combustor flame tube (40) of any of claims 1 or 2, further comprising an auxiliary thermal barrier coating (116) disposed adjacent to the cover layer (78).
    [4]
    A combustor flame tube (40) according to any one of claims 1 or 2, further comprising an additive bond layer (114) and an auxiliary thermal barrier coating (116) adjacent to the cover layer (78), the additive bond layer (114) interposed between Additional heat barrier coating (116) and the cover layer (78) is arranged.
    [5]
    A combustor flame tube (40) according to any one of claims 1 to 4, wherein the downstream end portion (72) comprises a lining combustor flame tube substrate (110).
    [6]
    A combustor flame tube (40) according to any one of claims 1 to 4, wherein the downstream end portion (72) comprises a lining combustor flame tube substrate (110) coated with an end portion bonding layer (114), the plurality of microchannels (80) in the end-portion bonding layer (140) are formed.
    [7]
    A combustor flame tube (40) according to any one of claims 1 to 4, wherein the downstream end portion (72) comprises a lining combustor flame tube substrate (110) coated with an end-portion bonding layer (114) and an end-portion thermal barrier coating (116). wherein the plurality of microchannels (80) are formed in the end-portion thermal barrier coating (116).
    [8]
    8. combustor flame tube (40) according to any one of claims 1 to 7, wherein the plurality of microchannels (80) with respect to the longitudinal axis (73) of the combustion chamber (14) extend in a straight line.
    [9]
    9. combustor flame tube (40) according to any one of claims 1 to 7, wherein the plurality of microchannels extend helically relative to the longitudinal axis (73) of the combustion chamber (14).
    [10]
    A combustor flame tube (40) according to any one of claims 1 to 9, wherein the outer surface (76) of the downstream end portion (72) has a number of channels (120), each of the plurality of channels (120) being configured to Passing coolant (64) therethrough which cools the combustor flame tube (40), and wherein at least a portion of the plurality of passages (90) is further connected in fluid communication with at least one of the channels (120).
    [11]
    The combustor flame tube (40) of any one of claims 1 to 10, wherein the plurality of microchannels (80) are formed such that the coolant (64) can flow directly into the hot gas path (28) from the microchannels.
    [12]
    The combustor flame tube (40) of any one of claims 1 to 11, wherein the cover layer (78) forms a plurality of outlets (92), each of the plurality of outlets (92) being in fluid communication with one of the plurality of microchannels (80) and configured to receive coolant (64) from the microchannel (80) and to deliver coolant (64) adjacent to the cover layer (78).
    [13]
    13. The combustor flame tube (40) of any one of claims 1 to 12, wherein the inner surface (74) of the downstream end portion (72) further includes a chamber (94) configured to receive coolant (64) from the plurality of microchannels (94). 80).
    [14]
    A combustor flame tube (40) according to claim 13, wherein the cover layer (78) forms the plurality of outlets (92), each of the plurality of outlets (92) being in fluid communication with the chamber (94) and adapted to be removed from Chamber (94) to receive coolant and to the cover layer (78) adjacent dispensing coolant (64).
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    同族专利:
    公开号 | 公开日
    JP2012041918A|2012-03-01|
    US8499566B2|2013-08-06|
    CN102374537A|2012-03-14|
    DE102011050757A1|2012-02-16|
    US20120036858A1|2012-02-16|
    CN102374537B|2016-03-16|
    JP5860616B2|2016-02-16|
    CH703549A2|2012-02-15|
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2022-01-31| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US12/855,156|US8499566B2|2010-08-12|2010-08-12|Combustor liner cooling system|
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