EP2980483B1 - Gas turbine combustor - Google Patents

Gas turbine combustor Download PDF

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Publication number
EP2980483B1
EP2980483B1 EP15179363.5A EP15179363A EP2980483B1 EP 2980483 B1 EP2980483 B1 EP 2980483B1 EP 15179363 A EP15179363 A EP 15179363A EP 2980483 B1 EP2980483 B1 EP 2980483B1
Authority
EP
European Patent Office
Prior art keywords
fuel nozzle
fuel
gas turbine
receiving hole
turbine combustor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP15179363.5A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2980483A1 (en
Inventor
Satoshi Kumagai
Yoshihide Wadayama
Mitsuhiro Karishuku
Satoshi Dodo
Nobuo Yagi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Power Ltd
Original Assignee
Mitsubishi Hitachi Power Systems Ltd
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Publication date
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Publication of EP2980483A1 publication Critical patent/EP2980483A1/en
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Publication of EP2980483B1 publication Critical patent/EP2980483B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts

Definitions

  • the present invention relates to a gas turbine combustor and to a method for building it and, more particularly, to a gas turbine combustor having a fuel nozzle to inject a fuel.
  • a plurality of fuel nozzles are respectively arranged in the circumferential and radial directions of a swirler of the gas turbine combustor to improve the fuel dispersibility.
  • a premixing pilot burner is provided at the head of a combustion sleeve which forms a combustion chamber, and a premixing main burner is provided on its outer periphery to sufficiently premix air and a fuel and thereby keep NOx low.
  • JP2009014297 discloses a gas turbine combustor in which a fuel nozzle is mounted in a mounting hole of a mounting structure.
  • DE 102012216080 A1 discloses a burner in which fuel nozzles are mounted on a body and pierce through an insulation shield.
  • US 2010/0071377 A1 discloses a combustor apparatus comprising a liner, a fow sleeve and an injector system comprising plural fuel injectors.
  • Patent Literature 1 The technique of gas turbine combustor described in Patent Literature 1 has the following problem. That is, as the number of fuel nozzles is increased to improve the fuel dispersibility, the distance between individual fuel nozzles or that between a set of fuel nozzles and a neighboring wall reduces.
  • An object of the present invention is to provide a gas turbine combustor and a manufacturing method thereof rendering an increased structural reliability by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
  • the fuel nozzle plate is provided with at least one fuel nozzle receiving hole to receive one of the fuel nozzles, and the fuel nozzle plate and the fuel nozzle inserted in the fuel nozzle receiving hole are connected to each other from an upstream side of the fuel nozzle plate by welding.
  • a method for building a gas turbine combustor comprising a burner comprises the steps of providing a plurality of fuel nozzles to supply fuel; providing a fuel nozzle plate to support end portions of the fuel nozzles structurally and being configured to distribute the fuel flowing from an upstream side to the fuel nozzles; providing in the fuel nozzle plate one or more fuel nozzle receiving holes, and inserting one or more of the fuel nozzles into one or more of the fuel nozzle receiving holes and connecting them to each other from an upstream side of the fuel nozzle plate by welding.
  • the present invention realizes a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
  • a gas turbine which constitutes a gas turbine plant 1 includes a compressor 3 which takes in air 2 from atmosphere and compresses it, a gas turbine combustor 7 which burns compressed air 4 compressed by the compressor 3 and a fuel 5 to generate a high-temperature and highpressure combustor exit gas 6, a gas turbine 8 which is driven by the combustor exit gas 6 generated by the gas turbine combustor 7 and extracts energy from the combustor exit gas 6 as rotational power, and an electric generator 9 which generates electric power using the rotational power of the gas turbine 8.
  • the gas turbine combustor 7 includes an end cover 10 which is provided at the end portion of the gas turbine combustor 7, a cylindrical front outer sleeve 11 which is attached to the end cover 10, and an elongated cylindrical rear outer sleeve 12 which is attached to the rear portion of the front outer sleeve 11.
  • a disk-shaped swirler 13 having a plurality of air holes 21 is provided inside the front outer sleeve 11 and the rear outer sleeve 12.
  • a fuel nozzle plate 14 having a plurality of fuel nozzles 15 to inject a fuel toward air holes 21 formed in the swirler 13 is provided upstream of the swirler 13.
  • An elongated cylindrical liner 16 to constitute a combustion chamber 23 in which air and a fuel are mixed and burned is provided downstream of the swirler 13.
  • the compressed air 4 compressed by the compressor 3 passes through an annular passage 17 formed between the rear outer sleeve 12 and the liner 16, and flows into a burner 18 formed in the gas turbine combustor 7.
  • the burner 18 includes a plurality of fuel nozzles 15 to inject a fuel, a fuel nozzle plate 14 to supports the end portions of the fuel nozzles 15 structurally and serves to distribute the fuel flowing into it from the upstream side to the fuel nozzles 15, and the swirler 13 having a plurality of air holes 21 to be supplied with combustion air, are formed downstream of the fuel nozzle plate 14 including the plurality of fuel nozzles 15.
  • the compressed air 4 partially flows into the liner 16 from multiple cooling holes, formed in the liner 16, to serve as cooling air 19 for cooling the liner 16.
  • the fuel 5 supplied to the gas turbine combustor 7 flows into the fuel nozzle plate 14 through a fuel supply pipe 20 provided in the end cover 10, passes through the fuel nozzles 15 from the fuel nozzle plate 14, and is injected toward the plurality of air holes 21 formed in the swirler 13.
  • the fuel 5 injected by the fuel nozzle 15 and the compressed air 4 supplied through the annular passage 17 formed between the rear outer sleeve 12 and the liner 16 are mixed into an air-fuel mixture 22, which is injected toward the combustion chamber 23 and burned to form a high-temperature flame 24.
  • the gas turbine combustor 7 according to Embodiment 1 can use not only natural gas but also, for example, a coke oven gas, a refinery off-gas, or a coal gasification gas as the fuel 5.
  • FIG. 2 shows the arrangement of the burner 18 of the gas turbine combustor 7 according to Embodiment 1.
  • the burner 18 in the gas turbine combustor 7 according to Embodiment 1 includes the swirler 13, the fuel nozzle plate 14, and the fuel nozzles 15.
  • An upstream end portion 40 of the fuel nozzle 15 that injects a fuel is connected to the fuel nozzle plate 14 in a connecting portion, the connecting portion of which is sealed to prevent leakage of the fuel 5.
  • the upstream end portion 40 of the fuel nozzle 15 is connected to the fuel nozzle plate 14 generally by, for example, bolting, welding, or brazing.
  • FIG. 3 illustrates a method of connecting together by welding the fuel nozzle 15 and the fuel nozzle plate 14 which form the burner 18 of the gas turbine combustor 7 according to Embodiment 1.
  • a fuel nozzle receiving hole 44 to receive the fuel nozzle 15 is formed to extend through the fuel nozzle plate 14, and a connecting portion 45 is formed at an upstream end portion 40 of the fuel nozzle 15, inserted in the fuel nozzle receiving hole 44 and an upstream end portion 41 of the fuel nozzle plate 14 by welding them together from the upstream side of the fuel nozzle plate 14 to connect the upstream end portion 40 of the fuel nozzle 15 to the upstream end portion 41 of the fuel nozzle plate 14.
  • FIG. 4 shows a method of connecting to each other the fuel nozzle 15 and the fuel nozzle plate 14 which form the burner 18 of the gas turbine combustor 7 according to conventional Example.
  • a side surface 40b of the fuel nozzle 15 on the upstream side and a downstream end portion 41b of the fuel nozzle plate 14 are connected to each other by forming a connecting portion 42 on them from the downstream side of the fuel nozzle plate 14.
  • the method of connecting the fuel nozzle 15 and the fuel nozzle plate 14 to each other according to conventional example shown in FIG. 4 poses the following problem. That is, when multiple fuel nozzles 15 are densely arranged downstream of the fuel nozzle plate 14 and a space 43 surrounding the fuel nozzle 15 is narrow, an operation space which is wide enough to connect the fuel nozzle 15 and the fuel nozzle plate 14 to each other cannot be ensured on the downstream side of the fuel nozzle plate 14.
  • the fuel nozzle receiving hole 44 to receive the fuel nozzle 15 is formed to extend through the fuel nozzle plate 14, and the fuel nozzle 15 inserted in the fuel nozzle receiving hole 44 projects to the downstream side of the fuel nozzle plate 14.
  • a connecting portion 45 is formed at the upstream end portion 40 of the fuel nozzle 15, inserted in the fuel nozzle receiving hole 44, and the upstream end portion 41 of the fuel nozzle plate 14 by welding them together from the upstream side of the fuel nozzle plate 14 to connect the upstream end portion 40 of the fuel nozzle 15 to the upstream end portion 41 of the fuel nozzle plate 14.
  • the gas turbine combustor 7 of Embodiment 1 since the gas turbine combustor 7 of Embodiment 1 has the fuel nozzle 15 that does not extend to the upstream side of the fuel nozzle plate 14, an operation space wide enough to connect the fuel nozzle 15 and the fuel nozzle plate 14 to each other is ensured on the upstream side of the fuel nozzle plate 14. This improves both the accuracy of connecting the fuel nozzle 15 and the fuel nozzle plate 14 to each other and, with the improvement in connecting accuracy, the structural reliability of the connecting portion between the fuel nozzle 15 and the fuel nozzle plate 14 is heightened.
  • forming a small space between the side surface of the fuel nozzle 15 and the inner surface of the fuel nozzle receiving hole 44 of the fuel nozzle plate 14 makes it possible to generate a frictional force between the side surface of the fuel nozzle 15 and the inner surface of the fuel nozzle receiving hole 44 of the fuel nozzle plate 14 upon their contact.
  • the obtained frictional force can produce an effect of damping oscillation acting on the fuel nozzle 15.
  • Present Embodiment 1 realizes a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
  • a method of connecting to each other a fuel nozzle 15 and a fuel nozzle plate 14 which form a burner 18 of a gas turbine combustor 7 according to Embodiment 2 of the present invention will be described below with reference to a partial enlarged view shown in FIG. 5 .
  • FIG. 5 illustrates details of the structure of the burner 18 in the gas turbine combustor 7 according to Embodiment 2. Since the basic arrangement and the method of connecting to each other the fuel nozzle 15 and the fuel nozzle plate 14 which form the burner 18 of the gas turbine combustor 7 according to Embodiment 2 are similar to those according to the above-mentioned Embodiment 1 of the present invention, parts common to both embodiments will not be described and only different parts will be described below.
  • FIG. 5 shows the fuel nozzle 15 connected to an upstream end portion 41 of the fuel nozzle plate 14 at an upstream end portion 40 of the fuel nozzle 15, in the burner 18 of the gas turbine combustor 7 according to Embodiment 2.
  • the burner 18 of the gas turbine combustor 7 according to Embodiment 2 shown in FIG. 5 includes stepped portions 51 and 50.
  • the stepped portion 51 is formed upstream of the fuel nozzle receiving hole 44 formed to extend through the fuel nozzle plate 14 and has a diameter larger than that of the downstream portion of the fuel nozzle receiving hole 44.
  • the stepped portion 50 is formed at the upstream end portion 40 of the fuel nozzle 15 inserted in the fuel nozzle receiving hole 44 and has a diameter larger than that of the downstream portion of the fuel nozzle 15.
  • the stepped portion 50 formed at the upstream end portion 40 of the fuel nozzle 15 abuts against the stepped portion 51 formed upstream of the fuel nozzle receiving hole 44.
  • a connecting portion 45 is formed at the upstream end portion 40 of the large-diameter stepped portion 50, formed on the fuel nozzle 15, and the upstream end portion 41 of the fuel nozzle plate 14, facing the upstream portion of the large-diameter stepped portion 51 formed in the fuel nozzle receiving hole 44, by welding them together from the upstream side of the fuel nozzle plate 14 to connect the upstream end portion 40 of the fuel nozzle 15 to the upstream end portion 41 of the fuel nozzle plate 14.
  • the stepped portion 50 formed at the upstream end portion 40 of the fuel nozzle 15 has an outer diameter larger than that of the downstream portion of the fuel nozzle 15, and the stepped portion 51 formed in the upstream portion of the fuel nozzle receiving hole 44 of the fuel nozzle plate 14 has an inner diameter larger than that of the downstream portion of the fuel nozzle receiving hole 44.
  • This structure allows the lower surface of the large-diameter stepped portion 50 formed on the fuel nozzle 15 to abut against the lower surface of the large-diameter stepped portion 51 formed in the fuel nozzle receiving hole 44 to prevent the fuel nozzle 15 from falling off the fuel nozzle receiving hole 44 to the downstream side.
  • the use of the stepped portions 50 and 51 allows the fuel nozzle 15 to be positioned in its axial direction 52.
  • Present Embodiment 2 realizes a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
  • a method of connecting to each other a fuel nozzle 15 and a fuel nozzle plate 14 which form a burner 18 of a gas turbine combustor 7 according to Embodiment 3 will be described below with reference to a partial enlarged view shown in FIG. 6 .
  • FIG. 6 illustrates details of the structure of the burner 18 in the gas turbine combustor 7 according to Embodiment 3. Since the basic arrangement and the method of connecting to each other upstream end portion 40 of the fuel nozzle 15 and upstream end portion 41 of the fuel nozzle plate 14, respectively, which form the burner 18 of the gas turbine combustor 7 according to Embodiment 3 are similar to those according to the above-mentioned Embodiment 1 of the present invention, parts common to both embodiments will not be described and only different parts will be described below.
  • FIG. 6 shows details of the structure of the burner 18 in the gas turbine combustor 7 according to Embodiment 3.
  • a connecting portion 45 is formed at the upstream end portion 40 of the fuel nozzle 15, inserted in a fuel nozzle receiving hole 44 formed to extend through the fuel nozzle plate 14, and the upstream end portion 41 of the fuel nozzle plate 14 by welding them together from the upstream side of the fuel nozzle plate 14 to connect the upstream end portion 40 of the fuel nozzle 15 to the upstream end portion 41 of the fuel nozzle plate 14.
  • the fuel nozzle 15 has a tapered outer shape portion 60 in which a portion of the fuel nozzle 15 projecting to the downstream side from the fuel nozzle receiving hole 44 formed to extend through the fuel nozzle plate 14 has its outer diameter being gradually smaller from its basal portion toward a downstream end portion 30.
  • the fuel nozzle 15 has the tapered outer shape portion 60 in which a portion of the fuel nozzle 15 projecting to the downstream side from the fuel nozzle receiving hole 44 has its outer diameter being gradually smaller toward the downstream end portion 30.
  • This allows the fuel nozzle 15 to be relatively lightweight by the weight of the portion gradually smaller in outer diameter of the fuel nozzle 15. It is, therefore, possible to reduce the load acting upon combustion oscillation on the connecting portion 45 that connects the upstream end portion 40 of the fuel nozzle 15 to the upstream end portion 41 of the fuel nozzle plate 14.
  • Present Embodiment 3 realizes a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
  • FIG. 7 illustrates details of the structure of the burner 18 in the gas turbine combustor 7 according to Embodiment 4. Since the basic arrangement and the method of connecting to each other upstream end portion 40 of the fuel nozzle 15 and upstream end portion 41 of the fuel nozzle plate 14, respectively, which form the burner 18 of the gas turbine combustor 7 according to Embodiment 4 are similar to those according to the above-mentioned Embodiment 2, parts common to both embodiments will not be described and only different parts will be described below.
  • a stepped portion 50 formed at the upstream end portion of the fuel nozzle 15 has an outer diameter larger than that of the downstream portion of the fuel nozzle 15, and a stepped portion 51 formed in the upstream portion of the fuel nozzle receiving hole 44 of the fuel nozzle plate 14 has an inner diameter larger than that of the downstream portion of the fuel nozzle receiving hole 44.
  • This structure allows the lower surface of the large-diameter stepped portion 50 formed on the fuel nozzle 15 to abut against the lower surface of the large-diameter stepped portion 51, formed in the fuel nozzle receiving hole 44, to prevent the fuel nozzle 15 from falling off the fuel nozzle receiving hole 44 to the downstream side.
  • the fuel nozzle 15 has a tapered outer shape portion 60 in which a portion of the fuel nozzle 15 projecting to the downstream side from the fuel nozzle receiving hole 44 formed to extend through the fuel nozzle plate 14 has its outer diameter being gradually smaller from its basal portion toward a downstream end portion 30, as in the shape of the fuel nozzle 15 described in Embodiment 3.
  • the fuel nozzle 15 has the tapered outer shape portion 60 in which a portion of the fuel nozzle 15 projecting to the downstream side from the fuel nozzle receiving hole 44 formed in the fuel nozzle plate 14 has its outer diameter being gradually smaller toward the downstream end portion 30.
  • This allows the fuel nozzle 15 to be relatively lightweight by the weight of the portion gradually smaller in outer diameter of the fuel nozzle 15. It is, therefore, possible to reduce the load acting upon combustion oscillation on the connecting portion 45 that connects the upstream end portion 40 of the fuel nozzle 15 to the upstream end portion 41 of the fuel nozzle plate 14.
  • the fuel nozzle 15 is relatively lightweight while keeping a sufficient strength. It is, therefore, possible to reduce the load acting upon combustion oscillation on the connecting portion 45 that connects the fuel nozzle 15 to the fuel nozzle plate 14.
  • Present Embodiment 4 realizes a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
  • a method of connecting to each other a fuel nozzle 15 and a fuel nozzle plate 14 which form a burner 18 of a gas turbine combustor 7 according to Embodiment 5 will be described below with reference to a partial enlarged view shown in FIG. 8 .
  • FIG. 8 illustrates details of the structure of the burner 18 in the gas turbine combustor 7 according to Embodiment 5. Since the basic arrangement and the method of connecting to each other upstream end portion 40 of the fuel nozzle 15 and upstream end portion 41 of the fuel nozzle plate 14, respectively, which form the burner 18 of the gas turbine combustor 7 according to Embodiment 5 are similar to those according to the above-mentioned Embodiment 1 of the present invention, parts common to both embodiments will not be described and only different parts will be described below.
  • a fuel nozzle receiving hole 44 formed to extend through the fuel nozzle plate 14 has an inner wall surface defining a tapered portion 70 in which the fuel nozzle receiving hole 44 has its outer diameter being gradually larger from its intermediate portion to the upstream side.
  • the fuel nozzle 15 inserted in the fuel nozzle receiving hole 44 has an outer wall surface defining a tapered portion 72 in which the fuel nozzle 15 has its outer diameter being gradually larger from its intermediate portion to the upstream side, in correspondence with the shape of the inner wall surface defining the tapered portion 70 of the fuel nozzle receiving hole 44.
  • a connecting portion 45 is formed on the inner wall surface defining the tapered portion 70, formed near an upstream end portion 41 of the fuel nozzle plate 14, and the outer wall surface defining the tapered portion 72, formed near an upstream end portion 40 of the fuel nozzle 15 inserted in the fuel nozzle receiving hole 44, by welding them together from the upstream side of the fuel nozzle plate 14 to connect the fuel nozzle 15 to the fuel nozzle plate 14.
  • the fuel nozzle 15 has an outer wall surface defining the tapered portion 72 in which a portion of the fuel nozzle 15 formed near the upstream end portion 40 has an outer diameter larger than that of the downstream portion of the fuel nozzle 15.
  • the fuel nozzle receiving hole 44 has an inner wall surface defining the tapered portion 70 in which a portion of the fuel nozzle receiving hole 44 formed near the upstream end portion 41 of the fuel nozzle plate 14 has an inner diameter larger than that of the downstream portion of the fuel nozzle receiving hole 44.
  • This structure allows the outer wall surface defining the tapered portion 72 of the fuel nozzle 15 to abut against the inner wall surface defining the tapered portion 70 of the fuel nozzle receiving hole 44 to prevent the fuel nozzle 15 from falling off the fuel nozzle receiving hole 44 to the downstream side.
  • the use of the tapered portion 72 formed on the fuel nozzle 15 allows the fuel nozzle 15 to be positioned in its axial direction 52 and radial direction 71 with respect to the tapered portion 70 of the fuel nozzle receiving hole 44 formed on the fuel nozzle plate 14.
  • Present Embodiment 5 realizes a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
  • FIG. 9 illustrates details of the structure of the burner 18 in the gas turbine combustor 7 according to Embodiment 6. Since the basic arrangement and the method of connecting to each other the fuel nozzle 15 and the fuel nozzle plate 14 which form the burner 18 of the gas turbine combustor 7 according to Embodiment 6 are similar to those according to the above-mentioned Embodiment 1 of the present invention, parts common to both embodiments will not be described and only different parts will be described below.
  • the burner 18 in the gas turbine combustor 7 according to Embodiment 6 shown in FIG. 9 includes flanged portions 80.
  • the flanged portion 80 is formed at an upstream end portion 40 of the fuel nozzle 15 inserted in a fuel nozzle receiving hole 44 formed to extend through the fuel nozzle plate 14, and has a diameter larger than the outer diameter of the downstream portion of the fuel nozzle 15.
  • a connecting portion 45 is formed on an upstream end portion 41 of the fuel nozzle plate 14 and the large-diameter flanged portion 80, formed at the upstream end portion 40 of the fuel nozzle 15, by welding them together from the upstream side of the fuel nozzle plate 14 to connect the lower surface of the upstream end portion 40 of the fuel nozzle 15 to the upstream end portion 41 of the fuel nozzle plate 14.
  • the flanged portion 80 formed at the upstream end portion 40 of the fuel nozzle 15 has an outer diameter larger than the inner diameter of the fuel nozzle receiving hole 44 of the fuel nozzle plate 14.
  • the fuel nozzle 15 can be positioned in its axial direction 52 in a contact portion 81 where the lower surface of the upstream end portion 40 defining the flanged portion 80 of the fuel nozzle 15 comes into contact with the upstream end portion 41 of the fuel nozzle plate 14.
  • Present Embodiment 6 realizes a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
  • a method of connecting to each other a fuel nozzle 15 and a fuel nozzle plate 14 which form a burner 18 of a gas turbine combustor 7 according to Embodiment 7 will be described below with reference to a partial enlarged view shown in FIG. 10 .
  • FIG. 10 illustrates details of the structure of the burner 18 in the gas turbine combustor 7 according to Embodiment 7. Since the basic arrangement and the method of connecting to each other upstream end portion 40 of the fuel nozzle 15 and upstream end portion 41 of the fuel nozzle plate 14, respectively, which form the burner 18 of the gas turbine combustor 7 according to Embodiment 7 are similar to those according to the above-mentioned Embodiment 2 of the present invention, parts common to both embodiments will not be described and only different parts will be described below.
  • the burner 18 in the gas turbine combustor 7 according to Embodiment 7 shown in FIG. 10 includes an orifice portion 90 formed in the intermediate portion of the fuel passage of the fuel nozzle 15.
  • a connecting portion 45 is formed at an upstream end portion 40 of a large-diameter stepped portion 50 of the fuel nozzle 15 and an upstream end portion 41 of the fuel nozzle plate 14, provided upstream of a large-diameter stepped portion 51 of a fuel nozzle receiving hole 44 formed in the fuel nozzle plate 14, by welding them together from the upstream side of the fuel nozzle plate 14 to connect the upstream end portion 40 of the fuel nozzle 15 to the upstream end portion 41 of the fuel nozzle plate 14.
  • thermal deformation occurs due to factors associated with welding and the inner diameter of the orifice portion 90 formed in the intermediate portion of the fuel passage of the fuel nozzle 15 changes.
  • the direction of thermal deformation caused by welding is not a radial direction 71 of the fuel nozzle 15 but an axial direction 52 of the fuel nozzle 15. This keeps deformation, occurring in the orifice portion 90 of any fuel nozzle 15, small to accurately control the fuel flow rate.
  • Present Embodiment 7 realizes a gas turbine combustor with its structural reliability increased by facilitating connection between a fuel nozzle and a fuel nozzle plate, even when the space surrounding the fuel nozzle is narrow, to improve the accuracy of connecting the fuel nozzle and the fuel nozzle plate to each other.
  • a gap may be formed between an inner surface of the fuel nozzle receiving hole 44 formed in the fuel nozzle plate 14 to receive the fuel nozzle 15 and an outer surface of the fuel nozzle 15 inserted in the fuel nozzle receiving hole 44.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
EP15179363.5A 2014-08-01 2015-07-31 Gas turbine combustor Active EP2980483B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2014157350A JP6301774B2 (ja) 2014-08-01 2014-08-01 ガスタービン燃焼器

Publications (2)

Publication Number Publication Date
EP2980483A1 EP2980483A1 (en) 2016-02-03
EP2980483B1 true EP2980483B1 (en) 2018-09-19

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US (1) US20160033136A1 (zh)
EP (1) EP2980483B1 (zh)
JP (1) JP6301774B2 (zh)
CN (1) CN105318355B (zh)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111237087B (zh) * 2020-01-19 2024-03-22 西北工业大学 一种航天动力用微孔板主被动复合冷却结构及冷却方法

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6423760B2 (ja) * 2015-06-24 2018-11-14 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器の燃料ノズル構造
JP6633982B2 (ja) * 2016-07-01 2020-01-22 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器、ガスタービン燃焼器の燃料ノズルの製造方法
FR3059047B1 (fr) * 2016-11-21 2020-08-28 Safran Helicopter Engines Injecteur de chambre de combustion pour une turbomachine et son procede de fabrication
JP6863718B2 (ja) 2016-11-21 2021-04-21 三菱パワー株式会社 ガスタービン燃焼器
US10920673B2 (en) * 2017-03-16 2021-02-16 General Electric Company Gas turbine with extraction-air conditioner
CN107023830B (zh) * 2017-05-26 2023-11-07 泉州市明燃厨房设备有限公司 一种燃烧器喷嘴底座
CN107477611B (zh) * 2017-07-20 2019-08-09 中国科学院工程热物理研究所 燃烧器
KR102049042B1 (ko) * 2017-10-27 2019-11-26 두산중공업 주식회사 연료 노즐 조립체, 이를 포함하는 연소기 및 가스 터빈
JP7287811B2 (ja) * 2019-03-25 2023-06-06 三菱重工業株式会社 燃焼器及びガスタービン
JP7257350B2 (ja) * 2020-03-16 2023-04-13 三菱重工業株式会社 ガスタービン燃焼器
JP2021162184A (ja) * 2020-03-31 2021-10-11 三菱パワー株式会社 ガスタービン燃焼器、燃料ノズルの製造方法
JP2023131352A (ja) * 2022-03-09 2023-09-22 三菱重工業株式会社 燃焼器及びガスタービン

Family Cites Families (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3975141A (en) * 1974-06-25 1976-08-17 The United States Of America As Represented By The Secretary Of The Army Combustion liner swirler
JPS5469537A (en) * 1977-11-15 1979-06-04 Hitachi Zosen Corp Joining method for tube and tube plate in heat exchanger or the like
JPS5496537A (en) * 1978-01-17 1979-07-31 Nissan Motor Co Ltd Coating method
JPS5671595A (en) * 1979-11-19 1981-06-15 Toshiba Corp Welding method for tube and tube plate in heat exchanger
US5575153A (en) * 1993-04-07 1996-11-19 Hitachi, Ltd. Stabilizer for gas turbine combustors and gas turbine combustor equipped with the stabilizer
JP3970244B2 (ja) * 2001-07-10 2007-09-05 三菱重工業株式会社 予混合ノズルおよび燃焼器並びにガスタービン
US6813889B2 (en) * 2001-08-29 2004-11-09 Hitachi, Ltd. Gas turbine combustor and operating method thereof
US6857271B2 (en) * 2002-12-16 2005-02-22 Power Systems Mfg., Llc Secondary fuel nozzle with readily customizable pilot fuel flow rate
US8122721B2 (en) * 2006-01-04 2012-02-28 General Electric Company Combustion turbine engine and methods of assembly
JP2009014297A (ja) * 2007-07-06 2009-01-22 Hitachi Ltd ガスタービン燃焼器
JP4906689B2 (ja) * 2007-11-29 2012-03-28 株式会社日立製作所 バーナ，燃焼装置及び燃焼装置の改造方法
US8061142B2 (en) * 2008-04-11 2011-11-22 General Electric Company Mixer for a combustor
US8230687B2 (en) * 2008-09-02 2012-07-31 General Electric Company Multi-tube arrangement for combustor and method of making the multi-tube arrangement
US20100071377A1 (en) * 2008-09-19 2010-03-25 Fox Timothy A Combustor Apparatus for Use in a Gas Turbine Engine
EP2189720A1 (de) * 2008-11-21 2010-05-26 Siemens Aktiengesellschaft Brenneranordnung
JP2011058775A (ja) * 2009-09-14 2011-03-24 Hitachi Ltd ガスタービン燃焼器
JP5470662B2 (ja) * 2011-01-27 2014-04-16 株式会社日立製作所 ガスタービン燃焼器
JP5393745B2 (ja) * 2011-09-05 2014-01-22 川崎重工業株式会社 ガスタービン燃焼器
JP5630424B2 (ja) * 2011-11-21 2014-11-26 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器
US9296038B2 (en) * 2011-12-29 2016-03-29 Solar Turbines Incorporated Method and apparatus for swaged liquid injector spoke
US9267690B2 (en) * 2012-05-29 2016-02-23 General Electric Company Turbomachine combustor nozzle including a monolithic nozzle component and method of forming the same
JP5926635B2 (ja) * 2012-07-04 2016-05-25 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器
JP5908361B2 (ja) * 2012-07-24 2016-04-26 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器
DE102012216080A1 (de) * 2012-08-17 2014-02-20 Dürr Systems GmbH Brenner

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111237087B (zh) * 2020-01-19 2024-03-22 西北工业大学 一种航天动力用微孔板主被动复合冷却结构及冷却方法

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US20160033136A1 (en) 2016-02-04
JP6301774B2 (ja) 2018-03-28
CN105318355B (zh) 2018-03-16

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