US20170370235A1 - Transition piece, combustor provided with same, and gas turbine provided with combustor - Google Patents

Transition piece, combustor provided with same, and gas turbine provided with combustor Download PDF

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Publication number
US20170370235A1
US20170370235A1 US15/544,384 US201615544384A US2017370235A1 US 20170370235 A1 US20170370235 A1 US 20170370235A1 US 201615544384 A US201615544384 A US 201615544384A US 2017370235 A1 US2017370235 A1 US 2017370235A1
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United States
Prior art keywords
passage
passages
region
axial direction
transition piece
Prior art date
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Abandoned
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US15/544,384
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English (en)
Inventor
Tetsu Konishi
Hiroaki KISHIDA
Kentaro Tokuyama
Hiroki Shibata
Akihiro Murakami
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Mitsubishi Power Ltd
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Mitsubishi Hitachi Power Systems Ltd
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Filing date
Publication date
Application filed by Mitsubishi Hitachi Power Systems Ltd filed Critical Mitsubishi Hitachi Power Systems Ltd
Assigned to MITSUBISHI HITACHI POWER SYSTEMS, LTD. reassignment MITSUBISHI HITACHI POWER SYSTEMS, LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KISHIDA, HIROAKI, KONISHI, TETSU, MURAKAMI, AKIHIRO, SHIBATA, HIROKI, TOKUYAMA, Kentaro
Publication of US20170370235A1 publication Critical patent/US20170370235A1/en
Assigned to MITSUBISHI POWER, LTD. reassignment MITSUBISHI POWER, LTD. CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
Abandoned legal-status Critical Current

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    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/005—Combined with pressure or heat exchangers
    • 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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • 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
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • 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
    • F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow

Definitions

  • the present invention relates to a transition piece demarcating a flow path where combustion gas flows, a combustor provided with the same, and a gas turbine provided with a combustor.
  • Patent Document 1 Japanese Unexamined Patent Application Publication No. 2010-261318A
  • the transition piece must be maintained at a fixed temperature or lower from the perspective of durability and the like. Therefore, if a large number of cooling passages with a large cross-sectional area are formed in the transition piece and a cooling medium is supplied in the cooling passages, the entire transition piece can be maintained at a fixed temperature or lower. On the other hand, the flow rate of the cooling medium supplied to the transition piece is preferably minimized from the perspective of operational cost and the like.
  • an object of the present invention is to provide: a transition piece that can suppress the flow rate of a cooling medium while maintaining durability; a combustor provided with the same; and a gas turbine provided with the combustor.
  • a transition piece of first aspect of the invention for achieving the aforementioned object is a transition piece demarcating a periphery of a combustion gas flow path where combustion gas flows from an upstream side to a downstream side in an axial direction in which an axis extends, wherein: a plurality of cooling passages which extend in the axial direction and inside which a cooling medium flows are formed so as to be aligned in the axial direction and a circumferential direction with regard to the axis; one or more downstream side passages which are a portion of the plurality of cooling passages are formed in a downstream side region on the downstream side within at least one circumferential region in the circumferential direction, and one or more upstream side passages which are another portion of the plurality of cooling passages are formed in an upstream side region on the upstream side with regard to the downstream side region within the circumferential region; and a total cross-sectional area per unit circumferential length of the one or more downstream side passages in the downstream side region is greater than a total cross-section
  • the total cross-sectional area per unit circumferential length of the one or more downstream side passages in the downstream side region within one circumferential region in the circumferential direction is larger than the total cross-sectional area per unit circumferential length of the one or more upstream side passages in the upstream side region within the same circumferential region. Therefore, in this transition piece, cooling performance by a cooling medium in the downstream side region can be enhanced. Furthermore, in this transition piece, the flow rate of the cooling medium flowing through the upstream side passage can be suppressed.
  • a transition piece of a second aspect of the invention for achieving the aforementioned object is the transition piece of the first aspect, wherein the number of the downstream side passages in the downstream side region may be greater than the number of the upstream side passages in the upstream side region.
  • a transition piece according to a third aspect of the invention for achieving the aforementioned object is a transition piece demarcating a periphery of a combustion gas flow path where combustion gas flows from an upstream side to a downstream side in an axial direction in which an axis extends, wherein: a plurality of cooling passages which extend in the axial direction and inside which a cooling medium flows are formed so as to be aligned in the axial direction and a circumferential direction with regard to the axis; one or more downstream side passages which are a portion of the plurality of cooling passages are formed in a downstream side region on the downstream side within at least one circumferential region in the circumferential direction, and one or more upstream side passages which are another portion of the plurality of cooling passages are farmed in an upstream side region on the upstream side with regard to the downstream side region within the circumferential region; and a ratio of a cross-sectional area of the downstream side passage to a length in the axial direction of the downstream side passage is larger than
  • the transition piece is more prone to heating on the downstream side than the upstream side.
  • the ratio of the cross-sectional area of the downstream side passage to the length in the axial direction of the downstream side passage in the downstream side region within one circumferential region in the circumferential direction is larger than the ratio of the cross-sectional area of the upstream side passage to the length in the axial direction of the upstream side passage in the upstream side region within the same circumferential region. Therefore, in this transition piece, cooling performance by a cooling medium in the downstream side region can be enhanced. Furthermore, in this transition piece, the flow rate of the cooling medium flowing through the upstream side passage can be suppressed.
  • a transition piece of a fourth aspect of the invention for achieving the aforementioned object is the transition piece of the third aspect, wherein the length in the axial direction of the downstream side passage may be shorter than the length in the axial direction of the upstream side passage.
  • a transition piece of a fifth aspect of the invention for achieving the aforementioned object is the transition piece of any one of the first to fourth aspects, wherein a cross-sectional area of the downstream side passage may be larger than a cross-sectional area of the upstream side passage.
  • a transition piece of a sixth aspect of the invention for achieving the aforementioned object is the transition piece of any one of the first to fifth aspects, including a body portion that demarcates a portion of the combustion gas flow path, is formed by bonding ends of one or more plate materials together, and has a bonded portion that is a portion where the ends of the one or more plate materials are bonded together and extends in the axial direction, wherein the upstream side passage and the downstream side passage may be formed in the body portion.
  • a transition piece of a seventh aspect of the invention for achieving the aforementioned object is the transition piece of any one of the first to sixth aspects, provided in a gas turbine casing that covers a gas turbine rotor, wherein: one or more rotor side passages which are a portion of the plurality of cooling passages may be formed in a rotor side region opposing the gas turbine rotor within at least one axial region in the axial direction, and one or more casing side passages which are another portion of the plurality of cooling passages may be formed in a casing side region opposing an inner circumferential surface of the gas turbine casing within the axial region; and a total cross-sectional area per unit circumferential length of the one or more casing side passages in the casing side region may be larger than a total cross-sectional area per unit circumferential length of the one or more rotor side passages in the rotor side region.
  • the total cross-sectional area per unit circumferential length of the one or more casing side passages in the casing side region within at least one axial region in the axial direction is larger than the total cross-sectional area per unit circumferential length of the one or more rotor side passages in the rotor side region within the same axial region. Therefore, in this transition piece, cooling performance by a cooling medium in the casing side region can be enhanced. Furthermore, in this transition piece, the flow rate of the cooling medium flowing through the cooling passage in the rotor side region can be suppressed.
  • a transition piece of an eighth aspect of the invention for achieving the aforementioned object is a transition piece provided in a gas turbine casing that covers a gas turbine rotor and demarcating a periphery of a combustion gas flow path where combustion gas flows from an upstream side to a downstream side in an axial direction in which an axis extends, wherein: a plurality of cooling passages which extend in the axial direction and inside which a cooling medium flows are formed so as to be aligned in a circumferential direction with regard to the axis; one or more rotor side passages which are a portion of the plurality of cooling passages are formed in a rotor side region opposing the gas turbine rotor within at least one axial region in the axial direction, and one or more casing side passages which are another portion of the plurality of cooling passages are formed in a casing side region opposing an inner circumferential surface of the gas turbine casing within the axial region; and a total cross-sectional area per unit circumferential length of
  • the cooling effect on the transition piece exerted by the compressed air that is present on the outer circumferential side of the transition piece is higher in the rotor side region and lower in the casing side region, of the regions in the circumferential direction in the transition piece.
  • the total cross-sectional area per unit circumferential length of the one or more casing side passages in the casing side region within at least one axial region in the axial direction is larger than the total cross-sectional area per unit circumferential length of the one or more rotor side passages in the rotor side region within the same axial region. Therefore, in this transition piece, too, cooling performance by a cooling medium in the casing side region can be enhanced. Furthermore, in this transition piece, the flow rate of the cooling medium flowing through the cooling passage in the rotor side region can be suppressed.
  • a transition piece of a ninth aspect of the invention for achieving the aforementioned object is the transition piece of the seventh or eighth aspect, wherein the number of the casing side passages in the casing side region may be higher than the number of the rotor side passages in the rotor side region.
  • a transition piece of a tenth aspect of the invention for achieving the aforementioned object is a transition piece provided in a gas turbine casing that covers a gas turbine rotor and demarcating a periphery of a combustion gas flow path where combustion gas flows from an upstream side to a downstream side in an axial direction in which an axis extends, wherein: a plurality of cooling passages which extend in the axial direction and inside which a cooling medium flows are formed so as to be aligned in a circumferential direction with regard to the axis; one or more rotor side passages which are a portion of the plurality of cooling passages are formed in a rotor side region opposing the gas turbine rotor within at least one axial region in the axial direction, and one or more casing side passages which are another portion of the plurality of cooling passages are formed in a casing side region opposing an inner circumferential surface of the gas turbine casing within the axial region; and a ratio of a cross-sectional area of
  • the cooling effect on the transition piece exerted by the compressed air that is present on the outer circumferential side of the transition piece is higher in the rotor side region and lower in the casing side region, of the regions in the circumferential direction in the transition piece.
  • the ratio of the cross-sectional area of the casing side passage to the length in the axial direction of the casing side passage in the casing side region within at least one axial region in the axial direction is larger than the ratio of the cross-sectional area of the rotor side passage to the length in the axial direction of the rotor side passage in the rotor side region within the same axial region. Therefore, in this transition piece, too, cooling performance by a cooling medium in the casing side region can be enhanced. Furthermore, in this transition piece, the flow rate of the cooling medium flowing through the cooling passage in the rotor side region can be suppressed.
  • a transition piece of an eleventh aspect of the invention for achieving the aforementioned object is the transition piece of the tenth aspect, wherein the length in the axial direction of the casing side passage may be shorter than the length in the axial direction of the rotor side passage.
  • a transition piece of a twelfth aspect of the invention for achieving the aforementioned object is the transition piece of any one of the seventh to eleventh aspects, wherein the cross-sectional area of the casing side passage may be larger than the cross-sectional area of the rotor side passage.
  • a transition piece of a thirteenth aspect of the invention for achieving the aforementioned object is the transition piece of any one of the seventh to twelfth aspects, including a body portion that demarcates a portion of the combustion gas flow path, is formed by bonding ends of one or more plate materials together, and has a bonded portion that is a portion where the ends of the one or more plate materials are bonded together and extends in the axial direction, wherein the rotor side passage and the casing side passage may be formed in the body portion.
  • a transition piece of a fourteenth aspect of the invention for achieving the aforementioned object is the transition piece of the sixth or thirteenth aspect, wherein a length in the axial direction of a bond side passage of the plurality of cooling passages that is nearest to the bonded portion in the circumferential direction may be shorter than a length in the axial direction of an adjacent passage of the plurality of cooling passages that is adjacent to the bond side passage in the circumferential direction.
  • an interval between a pair of cooling passages with the bonded portion provided between the two cooling passages is wider than an interval between other pairs of cooling passages. Therefore, the cooling performance by a cooling medium per unit circumferential length is lower between the pair of cooling passages with the bonded portion provided therebetween.
  • a transition piece of a fifteenth aspect of the invention for achieving the aforementioned object is a transition piece demarcating a periphery of a combustion gas flow path where combustion gas flows from an upstream side to a downstream side in an axial direction in which an axis extends, the transition piece including a body portion that demarcates a portion of the combustion gas flow path, is formed by bonding ends of one or more plate materials together, and has a bonded portion that is a portion where the ends of the one or more plate materials are bonded together and extends in the axial direction, wherein: a plurality of cooling passages which extend in the axial direction and inside which a cooling medium flows are formed in the body portion so as to be aligned in the axial direction and a circumferential direction with regard to the axis; and a length in the axial direction of a bond side passage of the plurality of cooling passages that is nearest to the bonded portion in the circumferential direction is shorter than a length in the axial direction of an adjacent passage of the pluralit
  • the length in the axial direction of the bond side passage which is a cooling passage nearest to the bonded portion in the circumferential direction is shorter than the length in the axial direction of another cooling passage adjacent to this bond side passage in the circumferential direction. Therefore, in this transition piece, too, the cooling performance of the bond side passage can be enhanced, and an area between a pair of cooling passages between which the bonded portion is provided can be cooled as equally well as areas between other pairs of cooling passages.
  • a transition piece of a sixteenth aspect of the invention for achieving the aforementioned object is the transition piece of the fourteenth or fifteenth aspect, wherein a cross-sectional area of the bond side passage may be larger than a cross-sectional area of the adjacent passage.
  • a transition piece of a seventeenth aspect of the invention for achieving the aforementioned object is the transition piece of any one of the first to sixteenth aspects, wherein, in at least some cooling passages of the plurality of cooling passages, an inlet into which the cooling medium flows may be formed at a downstream side end portion, and an outlet out of which the cooling medium flows may be formed at an upstream side end portion.
  • the cooling medium flows from the downstream side to the upstream side in the axial direction in at least some cooling passages. Therefore, in this transition piece, the downstream side of at least some cooling passages can be effectively cooled.
  • a transition piece of an eighteenth aspect of the invention for achieving the aforementioned object is the transition piece of any one of the first to sixteenth aspects, wherein the plurality of cooling passages may each have the same cross-sectional area at any position in the axial direction.
  • a combustor of an eighteenth aspect of the invention for achieving the aforementioned object includes: any of the above-described transition pieces; and a fuel supply unit supplying fuel and air into the combustion gas flow path.
  • a gas turbine of a nineteenth aspect of the invention for achieving the aforementioned object includes: the combustor; a compressor that compresses air and supplies the compressed air to the combustor; and a turbine that is driven by the combustion gas from the combustor.
  • FIG. 1 is a schematic view illustrating a configuration of a gas turbine according to an embodiment of the present invention.
  • FIG. 2 is a cross-sectional view of the vicinity of a combustor in the gas turbine according to the embodiment of the present invention.
  • FIG. 3 is a perspective view of a transition piece according to a first embodiment of the present invention.
  • FIG. 5 is a cross-sectional view taken along a line V-V in FIG. 4 .
  • FIG. 6 is a cross-sectional view taken along a line VI-VI in FIG. 4 .
  • FIG. 7 is a cross-sectional view taken along a line VII-VII in FIG. 4 .
  • FIG. 8 is a schematic developed view of a transition piece according to a second embodiment of the present invention.
  • FIG. 9 is a cross-sectional view taken along a line IX-IX in FIG. 8 .
  • FIG. 10 is a cross-sectional view taken along a line X-X in FIG. 8 .
  • FIG. 11 is a schematic developed view of a transition piece according to a third embodiment of the present invention.
  • FIG. 12 is a schematic developed view of a transition piece according to a fourth embodiment of the present invention.
  • FIG. 13 is a schematic developed view of a transition piece according to a fifth embodiment of the present invention.
  • FIG. 14 is a cross-sectional view taken along a line XIV-XIV in FIG. 13 .
  • FIG. 15 is a cross-sectional view taken along a line XV-XV in FIG. 13 .
  • FIG. 16 is a cross-sectional view taking along a line XVI-XVI in FIG. 13 .
  • FIG. 17 is a cross-sectional view taking along a line XVII-XVII in FIG. 13 .
  • FIG. 18 is a schematic developed view of a transition piece according to a sixth embodiment of the present invention.
  • a gas turbine includes a compressor 1 that generates compressed air A by compressing outside air Ao, a plurality of combustors 4 that generate combustion gas G by combusting fuel F in the compressed air A, and a turbine 5 driven by the combustion gas G.
  • the compressor 1 has a compressor rotor 2 that rotates around a rotational axis Ar and a compressor casing 3 that covers the compressor rotor 2 such that the compressor rotor can rotate.
  • the turbine 5 has a turbine rotor 6 that rotates around a rotational axis Ar and a turbine casing 7 that covers the turbine rotor 6 such that the turbine rotor can rotate.
  • the rotational axis Ar of the compressor rotor 2 and the rotational axis Ar of the turbine rotor 6 are located on the same straight line.
  • the compressor rotor 2 and the turbine rotor 6 are mutually connected to form a gas turbine rotor 8 .
  • the compressor casing 3 and the turbine casing 7 are mutually connected to form a gas turbine casing 9 .
  • a rotor of a generator GEN is connected to the gas turbine rotor 8 , for example.
  • the plurality of combustors 4 are aligned in a circumferential direction around the rotational axis Ar, and fixed to the gas turbine casing 9 .
  • the combustor 4 has a transition piece 20 and a fuel supply unit 10 that sends the fuel F and air A into the transition piece 20 .
  • the fuel F from the fuel supply unit 10 is combusted in the air A from the fuel supply unit 10 .
  • the combustion gas G is generated as a result of the combustion.
  • the transition piece 20 sends the combustion gas G to a combustion gas flow path of the turbine 5 .
  • the combustors 4 are provided inside the gas turbine casing 9 , in a space where the compressed air A compressed by the compressor 1 drifts.
  • the fuel supply unit 10 includes a plurality of burners 11 that discharge fuel and air, and a burner retaining cylinder 12 that retains the plurality of burners 11 .
  • the plurality of burners 11 are all supported by the burner retaining cylinder 12 parallel to a combustor axis Ac. Furthermore, the plurality of burners 11 all discharge the fuel F from a first side to a second side in the axial direction Da in which the combustor axis Ac extends.
  • the transition piece 20 forms a cylindrical shape extending in the axial direction Da and demarcates a periphery of a combustion gas flow path 21 in which the combustion gas G flows.
  • the transition piece 20 is formed around the combustor axis Ac.
  • the combustion gas flow path 21 gradually narrows from a first side towards a second side in the axial direction Da. Therefore, the cross-sectional area of a cross section orthogonal to the combustor axis Ac of the transition piece 20 gradually decreases from the first side towards the second side in the axial direction Da.
  • the first side in the axial direction Da is referred to as an upstream side Su
  • the second side in the axial direction Da is referred to as a downstream side Sd.
  • a circumferential direction of the combustion gas flow path 21 in other words, a circumferential direction with regard to the combustor axis Ac is simply referred to as a circumferential direction Dc.
  • the combustor 4 is provided inside the as turbine casing 9 , in a space where the compressed air A compressed by the compressor 1 drifts. Therefore, one region in the circumferential direction Dc of the transition piece 20 forms a rotor side region Rcr opposite from the gas turbine rotor 8 , and another region in the circumferential direction Dc of the transition piece 20 forms a casing side region Rcc opposite from an inner circumferential surface of the gas turbine casing 9 .
  • a first embodiment of a transition piece is described while referring to FIG. 3 to FIG. 7 .
  • the transition piece 20 of the present embodiment has a body portion 30 and an outlet flange portion 50 bonded to the downstream side Sd of the body portion 30 .
  • the flange portion 50 has a cylinder 51 forming a cylindrical shape and demarcating a portion of the combustion gas flow path 21 , and a flange 53 formed on a downstream end of the cylinder 51 . As illustrated in FIG. 2 , the flange 53 connects the transition piece 20 to a first stage vane 5 s 1 of the turbine 5 .
  • the cylinder 51 and flange 53 are integrally molded by casting or the like to form the outlet flange portion 50 .
  • a thermal barrier coating (TBC) layer not illustrated in the drawings is formed on an inner circumferential surface of the cylinder 51 .
  • a plurality of cooling passages 55 extending in the axial direction Da are formed in the outlet flange portion 50 .
  • An inlet of the cooling passage 55 is formed in an outer circumferential surface of the cylinder 51
  • an outlet of the cooling passage 55 is formed in a flange end surface of the flange 53 .
  • the body portion 30 is formed into a cylindrical shape by bending a plurality of laminate plates 31 , aligning the plurality of bent laminate plates 31 in the circumferential direction Dc, and then mutually bonding ends of the laminate plates 31 in the circumferential direction Dc by welding.
  • two sheets of the laminate plate 31 are aligned in the circumferential direction Dc, but three or more sheets, for example, four sheets of the laminate plates 31 may be aligned in the circumferential direction Dc.
  • one sheet of the laminate plate 31 may be bent into a cylindrical shape, and ends of the one sheet of laminate plate 31 may be mutually bonded by welding.
  • the laminate plate 31 has an outer plate 32 and an inner plate 34 .
  • a first surface forms an outer circumferential surface 32 o and a second surface forms a bond surface 32 c.
  • a first surface forms a bond surface 34 c and a second surface forms an inner circumferential surface 34 i.
  • a plurality of long grooves 33 recessed towards the outer circumferential surface 32 o and extending in a constant direction are formed.
  • the bond surfaces 32 c, 34 c of the outer plate 32 and the inner plate 34 are bonded together by brazing or the like to form the laminate plate 31 .
  • By bonding the outer plate 32 and inner plate 34 openings of the long grooves 33 formed in the outer plate 32 are blocked by the inner plate 34 , and thus the inside of each long groove 33 becomes a cooling passage 35 .
  • the plurality of laminate plates 31 are each disposed such that the inner circumferential surface 34 i of the inner plate 34 faces an inner circumferential side of the transition piece 20 , the outer circumferential surface 32 o of the outer plate 32 faces an outer circumferential side of the transition piece 20 , and an extending direction of the cooling passage 35 matches the axial direction Da of the transition piece 20 , and the ends in the circumferential direction Dc are mutually bonded as described above.
  • a cylinder is formed by bonding the plurality of laminate plates 31 .
  • a thermal barrier coating layer 36 is formed on the inner circumferential surface of the cylinder, in other words, the inner circumferential surface 34 i of the inner plate 34 .
  • An inlet 35 i connected to the cooling passage 35 from the outer circumferential surface 32 o of the outer plate 32 is formed in the laminate plate 31 . Furthermore, an outlet 35 o connected to the cooling passage 35 from a surface of the thermal harder coating layer 36 is formed in the laminate plate 31 .
  • the combustor 4 is provided inside the gas turbine casing 9 , in a space where the compressed air A compressed by the compressor 1 drifts. Therefore, the compressed air A in the gas turbine casing 9 flows as a cooling medium into the cooling passage 35 of the body portion 30 from the inlet 35 i formed in the outer circumferential surface 32 o of the body portion 30 in the transition piece 20 .
  • the compressed air A flows out from the cooling passage 35 to the combustion gas flow path 21 formed on an inner circumferential side of the body portion 30 through the outlet 35 o formed in the inner circumferential surface 34 i of the body portion 30 .
  • the compressed air A flows into the cooling passage 55 of the outlet flange portion 50 from the inlet formed in an outer circumferential surface of the outlet flange portion 50 in the transition piece 20 .
  • the compressed air A flows out from the cooling passage 55 to the outside through the outlet formed in the flange end surface of the outlet flange portion 50 .
  • FIG. 4 is a schematic developed view in which the cylindrical transition piece 20 is developed on a plane and viewed from the inner circumferential surface 34 i side of the transition piece 20 .
  • the plurality of cooling passages 35 , 55 extending in the axial direction Da are formed in the transition piece 20 .
  • the plurality of cooling passages 35 , 55 include a plurality of first upstream side passages 41 , a plurality of second upstream side passages 42 , a plurality of first downstream side passages 43 , a plurality of second downstream side passages 44 , a plurality of first through fifth bond side passages 45 through 49 , and a plurality of outlet flange passages 55 .
  • the plurality of outlet flange passages 55 are formed in the outlet flange portion 50 of the transition piece 20 . Therefore, the outlet flange passage 55 forms the cooling passage 55 of the outlet flange portion 50 .
  • the other passages 41 through 49 excluding the outlet flange passage 55 are all formed in the body portion 30 of the transition piece 20 . Therefore, the other passages 41 to 49 form the cooling passages 35 of the body portion 30 .
  • a cross-sectional area of each of the plurality of cooling passages 35 , 55 is the same at any position in the axial direction Da. However, the cross-sectional areas of the plurality of cooling passages 35 may be different from one another as described later. Similarly, the cross-sectional areas of the plurality of cooling passages 55 also may be different from one another.
  • the plurality of first upstream side passages 41 are formed so as to be aligned in the circumferential direction Dc in a first upstream side region Ru 1 that is most upstream in the body portion 30 in the axial direction Da.
  • the plurality of second upstream side passages 42 are formed so as to be aligned in the circumferential direction Dc in a second upstream side region Ru 2 that is on the downstream side Sd with regard to the first upstream side region Ru 1 .
  • An upstream side portion of the second upstream side region Ru 2 overlaps with a downstream side portion of the first upstream side region Ru 1 in the axial direction Da. Therefore, an upstream side portion of the second upstream side passage 42 overlaps with a downstream side portion of the first upstream side passage 41 in the axial direction Da, and is shifted therefrom in the circumferential direction Dc.
  • the plurality of first downstream side passages 43 are formed so as to be aligned in the circumferential direction Dc in a first downstream side region Rd 1 that is on the downstream side Sd with regard to the second upstream side region Ru 2 .
  • An upstream side portion of the first downstream side region Rd 1 overlaps with a downstream side portion of the second upstream side region Ru 2 in the axial direction Da. Therefore, an upstream side portion of the first downstream side passage 43 overlaps with a downstream side portion of the second upstream side passage 42 in the axial direction Da, and is shifted therefrom in the circumferential direction Dc.
  • the plurality of second downstream side passages 44 are formed so as to be aligned in the circumferential direction Dc in a second downstream side region Rd 2 that is on the downstream side Sd with regard to the first downstream side region Rd 1 .
  • the second downstream side region Rd 2 is a region that is located farthest on the downstream side Sd in the body portion 30 .
  • An upstream side portion of the second downstream side region Rd 2 overlaps with a downstream side portion of the first downstream side region Rd 1 the axial direction Da. Therefore, an upstream side portion of the second downstream side passage 44 overlaps with a downstream side portion of the first downstream side passage 43 in the axial direction Da, and is shifted therefrom in the circumferential direction Dc.
  • a bonded portion 38 extending in the axial direction Da is formed in the body portion 30 .
  • the bonded portion 38 is formed by mutually bonding the ends of the plurality of laminate plates 31 in the circumferential direction Dc, as described above using FIG. 3 .
  • the first to fifth bond side passages 45 to 49 are all provided along the bonded portion 38 .
  • the first to fifth bond side passages 45 to 49 are all nearer to the bonded portion 38 than the other passages 41 to 44 in the circumferential direction Dc.
  • the first bond side passage 45 , second bond side passage 46 , third bond side passage 47 , fourth bond side passage 48 , and fifth bond side passage 49 are provided in this order so as to be aligned from the upstream side Su to the downstream side Sd of the body portion 30 .
  • the length of the first upstream side passage 41 in the axial direction Da and the length of the second upstream side passage 42 in the axial direction Da are both L 1 .
  • the length of a passage in the axial direction Da is referred to as a passage length.
  • the passage length of the first downstream side passage 43 and the passage length of the second downstream side passage 44 are both L 2 .
  • the passage length L 1 and the passage length L 2 are the same. Therefore, the passage length of the first upstream side passage 41 , the passage length of the second upstream side passage 42 , the passage length of the first downstream side passage 43 , and the passage length of the second downstream side passage 44 are mutually the same passage lengths.
  • the passage lengths of the first bond side passage 45 , second bond side passage 46 , and third bond side passage 47 are all L 3 .
  • the passage lengths of the fourth bond side passage 48 and fifth bond side passage 49 provided farther on the downstream side Sd than the bond side passages 45 to 47 are both L 4 .
  • the passage length L 3 is shorter than the passage lengths L 1 , L 2 .
  • the passage length L 4 is even shorter than the passage length L 3 . Therefore, the passage lengths L 3 , L 4 of the bond side passages 45 to 49 are both shorter than the passage lengths of the passages 41 to 44 adjacent to the bond side passages 45 to 49 in the circumferential direction Dc.
  • the cooling passages 35 formed in the body portion 30 each have the inlet 35 i formed at a downstream end portion of the cooling passage 35 , and the outlet 35 o formed at an upstream end portion of the cooling passage 35 . Therefore, the compressed air A flows from the downstream side Sd to the upstream side Su of the combustor 4 in the cooling passages 35 formed in the body portion 30 . Therefore, the air in the cooling passages 35 flows in a reverse direction from the combustion gas G flowing through the combustion gas flow path 21 .
  • the areas of cross sections orthogonal to the axial direction Da of the first upstream side passage 41 and second upstream side passage 42 are both S 1 as illustrated in FIG. 5 .
  • the area of a cross section orthogonal to the axial direction Da of a passage is referred to as the passage cross-sectional area.
  • the number of the first upstream side passages 41 and the number of the second upstream side passages 42 provided in a circumferential region of a unit circumferential length Lc are the same.
  • the passage cross-sectional areas of the first downstream side passage 43 and second downstream side passage 44 are both S 2 as illustrated in FIG. 6 .
  • the passage area S 2 is larger than the passage area S 1 .
  • the number of the first downstream side passages 43 and the number of the second downstream side passages 44 provided in a circumferential region of the unit circumferential length Lc are the same.
  • the total cross-sectional area per unit circumferential length Lc of the plurality of first downstream side passages 43 provided in the first downstream side region Rd 1 within one circumferential region Rc is larger than the total cross-sectional area per unit circumferential length Lc of the plurality of first upstream side passages 41 provided in the first upstream side region Ru 1 within the same circumferential region Rc.
  • the total cross-sectional area per unit circumferential length Lc of the plurality offing downstream side passages 43 provided in the first downstream side region Rd 1 within the same circumferential region Rc is larger than the total cross-sectional area per unit circumferential length Lc of the plurality of second upstream side passages 42 provided in the second upstream side region Ru 2 within the same circumferential region Rc.
  • the total cross-sectional area per unit circumferential length Lc of the plurality of second downstream side passages 44 provided in the second downstream side region Rd 2 within the same circumferential region Rc is larger than the total cross-sectional area per unit circumferential length Lc of the plurality of first upstream side passages 41 provided in the first upstream side region Ru 1 within the same circumferential region Rc.
  • the total cross-sectional area per unit circumferential length Lc of the plurality of second downstream side passages 44 provided in the second downstream side region Rd 2 within the same circumferential region Rc is larger than the total cross-sectional area per unit circumferential length Lc of the plurality of second upstream side passages 42 provided in the second upstream side region Ru 2 within the same circumferential region Rc.
  • the passage cross-sectional areas of the first to fifth bond side passages 45 to 49 are all S 3 .
  • the passage cross-sectional area S 3 is larger than the passage cross-sectional areas S 1 , S 2 .
  • heights of the passages are constant, and the passage cross-sectional areas of the passages are varied from one another by varying the widths of the passages.
  • the widths of the passages may be constant, and the heights of the passages may be varied in order to vary the passage cross-sectional areas of the passages from one another.
  • the cooling passages 55 formed in the outlet flange portion 50 each have an inlet 55 i formed at an upstream end of the outlet flange passage 55 , and an outlet 55 o formed at a downstream end of the outlet flange passage 55 .
  • the outlet 55 o is opened in the downstream end surface of the flange 53 as described above. Therefore, as with the combustion gas G, air inside the outlet flange passages 55 formed in the outlet flange portion 50 flows from the upstream side Su to the downstream side Sd of the combustor 4 , and flows to the outside from the downstream end surface of the flange 53 .
  • the fuel F and compressed air A are injected from the plurality of burners 11 of the fuel supply unit into the transition piece 20 .
  • the fuel F is combusted in the compressed air A.
  • the high-temperature combustion gas G is generated by combusting the fuel F.
  • the combustion gas G flows to the downstream side Sd through the inside of the transition piece 20 , and flows into the combustion gas flow path of the turbine 5 .
  • the downstream side Sd reaches a higher temperature than the upstream side Su in the combustion gas flow path 21 in the transition piece 20 . Therefore, the downstream side Sd of the transition piece 20 is more exposed to high-temperature gas than the upstream side Su. Furthermore, as described above, the combustion gas flow path 21 in the transition piece 20 gradually narrows from the upstream side Su towards the downstream side Sd. Therefore, in the combustion gas flow path 21 , the gas flow velocity is higher on the downstream side Sd than the upstream side Su. Therefore, the heat transfer coefficient with gas is higher on the downstream side Sd of the transition piece 20 than the upstream side Su.
  • the downstream side Sd is more exposed to high-temperature gas than the upstream side Su, and the downstream side Sd has a higher heat transfer coefficient with gas than the upstream side Su, and therefore, the downstream side Sd is more prone to heating than the upstream side Su.
  • air is passed from the downstream side Sd of the combustor 4 to the upstream side Su through the plurality of cooling passages 35 of the body portion 30 , and thus portions on the downstream side Sd of the cooling passages 35 are efficiently cooled.
  • the total cross-sectional area per unit circumferential length Lc of the plurality of downstream side passages 43 , 44 provided in the downstream side region Rd within the one circumferential region Rc is larger than the total cross-sectional area per unit circumferential length Lc of the plurality of upstream side passages 41 , 42 provided in the upstream side region Ru within the same circumferential region Rc. Therefore, in the present embodiment, the flow rate of air flowing through the downstream side passages 43 , 44 is higher than the flow rate of air flowing through the upstream side passages 41 , 42 , and the cooling performance in the downstream side region Rd is higher than the cooling performance in the upstream side region Ru. On the other hand, in the present embodiment, the flow rate of air flowing through the upstream side passages 41 , 42 in the upstream side region Ru that is heated less than the downstream side region Rd is reduced to suppress the cooling performance in the upstream side region Ru.
  • an interval between a pair of cooling passages 35 with the bonded portion 38 provided between the two cooling passages 35 is wider than an interval between other pairs of cooling passages 35 . Therefore, the cooling performance by air per unit circumferential length Lc is lower between the pair of cooling passages 35 between which the bonded portion 38 is provided.
  • the passage cross-sectional area S 3 of the bond side passages 45 through 49 which are the cooling passages 35 nearest to the bonded portion 38 in the circumferential direction Dc is larger than the passage cross-sectional area S 1 or S 2 of the other cooling passages 41 to 44 adjacent to the bond side passages 45 to 49 in the circumferential direction Dc. Furthermore, in the present embodiment, as illustrated in FIG. 4 , the passage lengths L 3 and L 4 of the bond side passages 45 through 49 which are the cooling passages 35 nearest to the bonded portion 38 in the circumferential direction Dc are shorter than the passage lengths L 1 and L 2 of the other cooling passages 41 to 44 adjacent to the bond side passages 45 to 49 in the circumferential direction Dc.
  • the heating amount of the cooling medium in a process of flowing through the passage is smaller as compared to when the passage length is long. Therefore, the temperature of the cooling medium is lower, and thus the cooling performance thereof is higher, in a cooling passage with a short passage length where the heating amount of the cooling medium is smaller, than in a cooling passage with a long passage length. Therefore, in the present embodiment, the cooling performance of the bond side passage 45 to 49 can be enhanced, and an area between pairs of cooling passages 45 to 49 between which the bonded portion 38 is provided can be cooled as equally well as areas between other pairs of cooling passages 41 to 44 .
  • the entire transition piece 20 can be at a fixed temperature or lower, a uniform temperature can be achieved, and the durability of the transition piece 20 can be ensured. Furthermore, in the present embodiment, while the flow rate of the cooling medium flowing through the cooling passage 35 in a region where the heating amount is large is increased, the flow rate Of the cooling medium flowing through the cooling passage 35 in a region where the heating amount is small is reduced, and therefore, the flow rate of the cooling medium can be suppressed overall.
  • the passage cross-sectional area of the first upstream side passage 41 and the passage cross-sectional area of the second upstream side passage 42 are the same.
  • the passage cross-sectional area of the second upstream side passage 42 may be larger than the passage cross-sectional area of the first upstream side passage 41 .
  • the passage cross-sectional area of the first downstream side passage 43 and the passage cross-sectional area of the second downstream side passage 44 are the same.
  • the passage cross-sectional area of the second downstream side passage 44 may be larger than the passage cross-sectional area of the first downstream side passage 43 .
  • the upstream side portion of the second upstream side passage 42 overlaps with the downstream side portion of the first upstream side passage 41 in the axial direction Da.
  • the upstream side portion of the first downstream side passage 43 overlaps with the downstream side portion of the second upstream side passage 42 in the axial direction Da.
  • the upstream side portion of the second downstream side passage 44 overlaps with the downstream side portion of the first downstream side passage 43 in the axial direction Da.
  • the cooling passages 41 to 44 may not overlap in the axial direction Da.
  • a second embodiment of the transition piece is described while referring to FIG. 8 to FIG. 10 .
  • the passage cross-sectional area of the downstream side passages 43 , 44 is larger than the passage cross-sectional area of the upstream side passages 41 , 42 .
  • the passage cross-sectional area of downstream side passages 43 a, 44 a and the passage cross-sectional area of upstream side passages 41 a, 42 a are the same, but the number of the downstream side passages 43 a, 44 a per unit circumferential length Lc is higher than the number of the upstream side passages 41 a , 42 a per unit circumferential length Lc.
  • the transition piece 20 a of the present embodiment is different from the first embodiment on this point, but the configuration is otherwise the same as that of the first embodiment.
  • a plurality of first upstream side passages 41 a, a plurality of second upstream side passages 42 a, a plurality of first downstream side passages 43 a, a plurality of second downstream side passages 44 a, a plurality of first through fifth bond side passages 45 through 49 , and a plurality of outlet flange passages 55 are also formed in the transition piece 20 a of the present embodiment, similarly to the transition piece 20 of the first embodiment.
  • a passage length of the first upstream side passage 41 a and a passage length of the second upstream side passage 42 a are both L 1 a .
  • a passage length of the first downstream side passage 43 a and a passage length of the second downstream side passage 44 a are both L 2 a.
  • the passage length L 1 a and the passage length L 2 a are the same.
  • Passage cress-sectional areas of the first upstream side passage 41 a and second upstream side passage 42 a are both S 1 as illustrated in FIG. 9 .
  • passage cross-sectional areas of the first downstream side passage 43 a and second downstream side passage 44 a are S 1 , which is the same as the passage cross-sectional areas of the first upstream side passage 41 a and second upstream side passage 42 a, as illustrated in FIG. 10 .
  • the number of the first downstream side passages 43 a and second downstream side passages 44 a per unit circumferential length Lc is higher than the number of the first upstream side passages 41 a and second upstream side passages 42 a per unit circumferential length Lc.
  • the total cross-sectional area per unit circumferential length Lc of the plurality of first downstream side passages 43 a provided in a first downstream side region Rd 1 a within one circumferential region Rc is lamer than the total cross-sectional area per unit circumferential length Lc of the plurality of first upstream side passages 41 a provided in a first upstream side region Ru 1 a within the same circumferential region Rc, similarly to the first embodiment.
  • the total cross-sectional area per unit circumferential length Lc of the plurality of first downstream side passages 43 a provided in the first downstream side region Rd 1 a within the same circumferential region Rc is larger than the total cross-sectional area per unit circumferential length Lc of the plurality of second upstream side passages 42 a provided in a second upstream side region Ru 2 a within the same circumferential region Rc.
  • the total cross-sectional area per unit circumferential length Lc of the plurality of second downstream side passages 44 a provided in a second downstream side region Rd 2 a within the same circumferential region Rc is larger than the total cross-sectional area per unit circumferential length Lc of the plurality of first upstream side passages 41 a provided in the first upstream side region Ru 1 a within the same circumferential region Rc.
  • the total cross-sectional area per unit circumferential length Lc of the plurality of second downstream side passages 44 a provided in the second downstream side region Rd 2 a within the same circumferential region Rc is larger than the total cross-sectional area per unit circumferential length Lc of the plurality of second upstream side passages 42 a provided in the second upstream side region Ru 2 a within the same circumferential region Rc.
  • the downstream side Sd is more exposed to high temperature gas than the upstream side Su, and the downstream side Sd has a higher heat transfer coefficient with gas than the upstream side Su, and therefore, the downstream side Sd is more prone to heating than the upstream side Su.
  • the number of the downstream side passages 43 a, 44 a per unit circumferential length Lc is increased to make the total cross-sectional area per unit circumferential length Lc of the plurality of downstream side passages 43 a, 44 a provided in the downstream side region Rda within the one circumferential region Rc larger than the total cross-sectional area per unit circumferential length Lc of the plurality of upstream side passages 41 a, 42 a provided in the upstream side region Rua within the same circumferential region Rc.
  • the total flow rate of air flowing through the downstream side passages 43 a, 41 a in the downstream side region Rda is higher than the total flow rate of air flowing through the upstream side passages 41 a, 42 a in the upstream side region Rua, and thus the cooling performance in the downstream side region Rda is higher than the cooling performance in the upstream side region Rua.
  • the total flow rate of air flowing through the upstream side passages 41 a, 42 a in the upstream side region Rua that is heated less than the downstream side region Rda is reduced to suppress the cooling performance in the upstream side region Ru.
  • the durability of the transition piece 20 a can be ensured, and the flow rate of the cooling medium can be suppressed.
  • the number of the first upstream side passages 41 a and the number of the second upstream side passages 42 a per unit circumferential length Lc are the same.
  • the number of the second upstream side passages 42 a per unit circumferential length Lc may be higher than the number of the first upstream side passages 41 a.
  • the number of the first downstream side passages 43 a and the number of the second downstream side passages 44 a per unit circumferential length Lc are the same.
  • the number of the second downstream side passages 44 a per unit circumferential length Lc may be higher than the number of the first downstream side passages 43 a.
  • the passage cross-sectional area of the first downstream side passage 43 a and second downstream side passage 44 a may be larger than the passage cross-sectional area of the first upstream side passage 41 a and second upstream side passage 42 a, similarly to the first embodiment.
  • a third embodiment of the transition piece is described while referring to FIG. 11 .
  • the passage cross-sectional area of the downstream side passages 43 , 44 is larger than the passage cross-sectional area of the upstream side passages 41 , 42 .
  • a passage cross-sectional area of downstream side passages 43 b , 44 b and a passage cross-sectional area of upstream side passages 41 b , 42 b are the same, but a passage length of the downstream side passages 43 b, 44 b is shorter than a passage length of the upstream side passages 41 b , 42 b.
  • the transition piece 20 b of the present embodiment is different from the first embodiment on this point, but the configuration is otherwise the same as that of the first embodiment.
  • a plurality of first upstream side passages 41 b, a plurality of second upstream side passages 42 b , a plurality of first downstream side passages 43 b , a plurality of second downstream side passages 44 b, a plurality of first through if bond side passages 45 through 49 , and a plurality of outlet flange passages 55 are also formed in the transition piece 20 b of the present embodiment, similarly to the transition piece 20 of the first embodiment.
  • the passage length of the first upstream side passage 41 b and the passage length of the second upstream side passage 42 b are both L 1 b .
  • the passage length of the first downstream side passage 43 b and the passage length of the second downstream side passage 44 b are both L 2 b .
  • the passage length L 2 b is shorter than the passage length L 1 b.
  • the passage lengths of the first bond side passage 45 , second bond side passage 46 , and third bond side passage 47 are all L 3 .
  • the passage lengths of the fourth bond side passage 48 and fifth bond side passage 49 provided farther on the downstream side Sd than the bond side passages 45 to 47 are both L 4 .
  • the passage length L 3 is shorter than passage lengths L 1 b .
  • the passage length L 4 is shorter than the passage length L 3 and the passage length L 2 b. Therefore, the passage lengths of the bond side passages 45 to 49 are both shorter than the passage lengths of all the passages adjacent to the bond side passages 45 to 49 in the circumferential direction Dc. Note that so long as the passage length L 3 is shorter than the passage length L 1 b , the passage length L 3 may be longer than the passage length L 2 b or shorter than the passage length L 2 b.
  • the passage cross-sectional areas of the first upstream side passage 41 b , second upstream side passage 42 b, first downstream side passage 43 b, and second downstream side passage 44 b are all S 1 . Furthermore, the number of the first downstream side passages 43 b, number of the second downstream side passages 44 b , number of the first upstream side passages 41 b , and number of the second upstream side passages 42 b per unit circumferential length Lc are mutually the same, similarly to the first embodiment.
  • a ratio (S 1 /L 2 b ) of the passage cross-sectional area S 1 to the passage length L 2 b of the downstream side passages 43 b, 44 b provided in downstream side regions Rd 1 b , Rd 2 b within one circumferential region Rc is larger than a ratio (S 1 /L 1 b ) of the passage cross-sectional area S 1 to the passage length L 1 b of the upstream side passages 41 b , 42 b provided in upstream side regions Ru 1 b , Ru 2 b within the same circumferential region Rc.
  • the downstream side Sd is more exposed to high-temperature gas than the upstream side Su, and the downstream side Sd has a higher heat transfer coefficient with gas than the upstream side Su, and therefore, the downstream side Sd is more prone to heating than the upstream side Su.
  • the cooling performance of a cooling passage with a short passage length is higher than that of a cooling passage with a long passage length. Therefore, in the present embodiment, the passage length L 2 b of the downstream side passages 43 b, 44 b is shorter than the passage length L 1 b of the upstream side passages 41 b, 42 b.
  • the durability of the transition piece 20 b can be ensured, and the flow rate of the cooling medium can be suppressed.
  • a method of making the passage length L 2 b of the downstream side passages 43 b , 44 b shorter than the passage length L 1 b of the upstream side passages 41 b, 42 b is used as a method of increasing the ratio (S 1 /L 2 b ) of the passage cross-sectional area S 1 to the passage length L 2 b of the downstream side passages 43 b , 44 b provided in the downstream side regions Rd 1 b , Rd 2 b within the one circumferential region Rc.
  • the ratio of the passage cross-sectional area to the passage length of the downstream side passages 43 b, 44 b provided in the downstream side regions Rd 1 b , Rd 2 b within the one circumferential region Rc can be increased.
  • the first embodiment can be said to have a ratio (S 2 /L 2 ) of the passage cross-sectional area S 2 to the passage length L 2 of the downstream side passages 43 , 44 provided in the downstream side region Rd within the one circumferential region Rc that is larger than a ratio (S 1 /L 1 ) of the passage cross-sectional area S 1 to the passage length L 1 of the upstream side passages 41 , 42 provided in the upstream side region Ru within the same circumferential region Rc.
  • the passage length of the first upstream side passage 41 b and the passage length of the second upstream side passage 42 b are the same.
  • the passage length of the second upstream side passage 42 b may be shorter than the passage length of the first upstream side passage 41 b.
  • the passage length of the first downstream side passage 43 b and the passage length of the second downstream side passage 44 b are the same.
  • the passage length of the second downstream side passage 44 b may be shorter than the passage length of the first downstream side passage 43 b.
  • the passage cross-sectional area of the first downstream side passage 43 b and second downstream side passage 44 b may be larger than the passage cross-sectional area of the first upstream side passage 41 b and second upstream side passage 42 b, similarly to the first embodiment.
  • the number of the first downstream side passages 43 b and second downstream side passages 44 b may be higher than the number of the first upstream side passages 41 b and second upstream side passages 42 b, similarly to the second embodiment.
  • a fourth embodiment of the transition piece is described while referring to FIG. 12 .
  • the rotor side region Rcr opposite from the gas turbine rotor 8 and the casing side region Rcc opposite from the inner circumferential surface of the gas turbine casing 9 are provided in the transition piece 20 .
  • a discharge opening 1 o of the compressor 1 is present on an inner side in a radial direction of the transition piece 20 , in a radial direction based on the rotational axis Ar of the gas turbine. Therefore, the compressed air A at a high flow velocity immediately after flowing out from the compressor 1 is directly blown onto the rotor side region Rcr of the transition piece 20 .
  • the compressed air A is stagnant on an outer side in the radial direction of the transition piece 20 , and therefore, the flow velocity of the compressed air A is low. Therefore, the heat transfer coefficient between the transition piece 20 and the compressed air A that is present on an outer circumferential side of the transition piece 20 is higher in the rotor side region Rcr and lower in the casing side region Rcc, of the regions in the circumferential direction Dc in the transition piece 20 .
  • the cooling effect on the transition piece 20 exerted by the compressed air A that is present on the outer circumferential side of the transition piece 20 is higher in the rotor side region Rcr and lower in the casing side region Rcc, of the regions in the circumferential direction Dc in the transition piece 20 .
  • a plurality of first upstream side passages 41 , 41 c, a plurality of second upstream side passages 42 , 42 c, a plurality of first downstream side passages 43 , 43 c , a plurality of second downstream side passages 44 , 44 c, a plurality of first through Milt bond side passages 45 to 49 , and a plurality of outlet flange passages 55 are also formed in the transition piece 20 c of the present embodiment, similarly to the transition piece 20 of the first embodiment.
  • the first upstream side passages 41 , 41 c include a first upstream casing side passage 41 c present in the casing side region Rcc, and a first upstream rotor side passage 41 present in a region including the rotor side region Rcr but excluding the casing side region Rcc.
  • the second upstream side passages 42 , 42 c include a second upstream casing side passage 42 c present in the casing side region Rcc, and a second upstream rotor side passage 42 present in a region including the rotor side region Rcr but excluding the casing side region Rcc.
  • first downstream side passages 43 , 43 c include a first downstream casing side passage 43 c present in the casing side region Rcc, and a first downstream rotor side passage 43 present in a region including the rotor side region Rcr but excluding the casing side region Rcc.
  • second downstream side passages 44 , 44 c include a second downstream casing side passage 44 c present in the casing side region Rcc, and a second downstream rotor side passage 44 present in a region including the rotor side region Rcr but excluding the casing side region Rcc.
  • a passage length of the first upstream casing side passage 41 c, passage length of the first upstream rotor side passage 41 , passage length of the second upstream casing side passage 42 c, and passage length of the second upstream rotor side passage 42 are all L 1 , similarly to the first embodiment. Furthermore, a passage length of the first downstream casing side passage 43 c, passage length of the first downstream rotor side passage 43 , passage length of the second downstream casing side passage 44 c , and passage length of the second downstream rotor side passage 44 are all L 2 . In the present embodiment, too, the passage length L 1 and the passage length L 2 are the same.
  • a passage cross-sectional area of the first upstream rotor side passage 41 and second upstream rotor side passage 42 is S 1 , which is the same as the passage cross-sectional area of the first upstream side passage 41 and second upstream side passage 42 of the first embodiment.
  • a passage cross-sectional area of the first downstream rotor side passage 43 and second downstream rotor side passage 44 is S 2 , which is the same as the passage cross-sectional area of the first downstream side passage 43 and second downstream side passage 44 of the first embodiment. Therefore, the passage cross-sectional area S 2 of the first downstream rotor side passage 43 and second downstream rotor side passage 44 is larger than the passage cross-sectional area S 1 of the first upstream rotor side passage 41 and second upstream rotor side passage 42 .
  • the passage cross-sectional area of the first upstream casing side passage 41 c and second upstream casing side passage 42 c is S 1 a , which is larger than the passage cross-sectional area S 1 of the first upstream rotor side passage 41 and second upstream rotor side passage 42 .
  • the passage cross-sectional area of the first downstream casing side passage 43 c and second downstream casing side passage 44 c is S 2 a, which is larger than the passage cross-sectional area S 2 of the first downstream rotor side passage 43 and second downstream rotor side passage 44 .
  • the passage cross-sectional area S 2 a of the first downstream casing side passage 43 c and second downstream casing side passage 44 c is larger than the passage cross-sectional area S 1 a of the first upstream casing side passage 41 c and second upstream casing side passage 42 c.
  • the cross-sectional area S 1 a of the first upstream casing side passage 41 c and second upstream casing side passage 42 c is larger than the passage cross-sectional area S 1 of the first upstream rotor side passage 41 and second upstream rotor side passage 42 and smaller than the passage cross-sectional area S 2 a of the first downstream casing side passage 43 c and second downstream casing side passage 44 e
  • the cross-sectional area S 1 a may be larger or smaller than the passage cross-sectional area S 2 of the first downstream rotor side passage 43 and second downstream rotor side passage 44 .
  • the total cross-sectional area per unit circumferential length Lc of the plurality of second downstream casing side passages 44 c provided in the casing side region Rcc within the second downstream side region Rd 2 which is one region in the axial direction Da is larger than the total cross-sectional area per unit circumferential length Lc of the plurality of second downstream rotor side passages 44 provided in the rotor side region Rcr within the second downstream side region Rd 2 .
  • the total cross-sectional area per unit circumferential length Lc of the plurality of first upstream casing side passages 41 c provided in the casing side region Rcc within the first upstream side region Ru 1 which is one region in the axial direction Da is larger than the total cross-sectional area per unit circumferential length Lc of the plurality of first upstream rotor side passages 41 provided in the rotor side region Rcr within the first upstream side region Ru 1 .
  • the total cross-sectional area per unit circumferential length Lc of the plurality of second upstream casing side passages 42 c provided in the casing side region Rcc within the second upstream side region Ru 2 which is one region in the axial direction Da is larger than the total cross-sectional area per unit circumferential length Lc of the plurality of second upstream rotor side passages 42 provided in the rotor side region Rcr within the second upstream side region Ru 2 .
  • the flow rate of air flowing through the cooling passage 35 in the casing side region Rcc is higher than the flow rate of air flowing through the cooling passage 35 in the rotor side region Rcr, and the cooling performance in the casing side region Rcc is higher than the cooling performance in the rotor side region Rcr. Therefore, in the present embodiment, the durability of the transition piece 20 c can be further improved, and the flow rate of the cooling medium can be further suppressed, as compared to the first embodiment.
  • a passage length of the first upstream casing side passage 41 d , passage length of the first upstream rotor side passage 41 a, passage length of the second upstream casing side passage 42 d, and passage length of the second upstream rotor side passage 42 a are all L 1 a, similarly to the second embodiment. Furthermore, a passage length of the first downstream casing side passage 43 d, passage length of the first downstream rotor side passage 43 a, passage length of the second downstream casing side passage 44 d , and passage length of the second downstream rotor side passage 44 a are all L 2 a, similarly to the second embodiment. In the present embodiment, too, the passage length L 1 a and the passage length L 2 a are the same, similarly to the second embodiment.
  • a passage cross-sectional area of the first upstream casing side passage 41 d , passage cross-sectional area of the first upstream rotor side passage 41 a , passage cross-sectional area of the second upstream casing side passage 42 d, passage cross-sectional area of the second upstream rotor side passage 42 a, passage cross-sectional area of the first downstream casing side passage 43 d, passage cross-sectional area of the first downstream rotor side passage 43 a, passage cross-sectional area of the second downstream casing side passage 44 d, and passage cross-sectional area of the second downstream rotor side passage 44 a are all S 1 as illustrated in in FIG. 14 to FIG. 17 .
  • the number of the first downstream rotor side passages 43 a and second downstream rotor side passages 44 a per unit circumferential length Lc 2 is higher than the number of the first upstream rotor side passages 41 a and second upstream rotor side passage 42 a per unit circumferential length Lc 2 (refer to FIG. 14 and FIG. 16 ), similarly to the second embodiment. Furthermore, the number of the first downstream casing side passages 43 d and second downstream casing side passages 44 d per unit circumferential length Lc 2 is higher than the number of the first upstream casing side passages 41 d and second upstream casing side passages 42 d per unit circumferential length Lc (refer to FIG. 15 and FIG. 17 ).
  • the total cross-sectional area per unit circumferential length Lc 2 of the plurality of first downstream casing side passages 43 d provided in the casing side region Rcc within the first downstream side region Rd 1 a is larger than the total cross-sectional area per unit circumferential length Lc 2 of the plurality of first downstream rotor side passages 43 a provided in the rotor side region Rcr within the first downstream side region Rd 1 a , similarly to the fourth embodiment.
  • the total cross-sectional area per unit circumferential length Lc 2 of the plurality of second downstream casing side passages 44 d provided in the casing side region Rcc within the second downstream side region Rd 2 a is larger than the total cross-sectional area per unit circumferential length Lc 2 of the plurality of second downstream rotor side passages 44 a provided in the rotor side region Rcr within the second downstream side region Rd 2 a.
  • the total cross-sectional area per unit circumferential length Lc 2 of the plurality of first upstream casing side passages 41 d provided in the casing side region Rcc within the first upstream side region Ru 1 a is larger than the total cross-sectional area per unit circumferential length Lc 2 of the plurality of first upstream rotor side passages 41 a provided in the rotor side region Rcr within the first upstream side region Ru 1 a .
  • the total cross-sectional area per unit circumferential length Lc 2 of the plurality of second upstream casing side passages 42 d provided in the casing side region Rcc within the second upstream side region Ru 2 a is larger than the total cross-sectional area per unit circumferential length Lc of the plurality of second upstream rotor side passages 42 a provided in the rotor side region Rcr within the second upstream side region Ru 2 a.
  • the flow rate of air flowing through the cooling passage 35 in the casing side region Rcr is higher than the flow rate of air flowing through the cooling passage 35 in the rotor side region Rcr, and the cooling performance in the casing side region Rcc can be made higher than the cooling performance in the rotor side region Rcr, similarly to the fourth embodiment.
  • a sixth embodiment of the transition piece is described while referring to FIG. 18 .
  • a plurality of first upstream casing side passages 41 e, plurality of first upstream rotor side passages 41 b, plurality of second upstream casing side passages 42 e, plurality of second upstream rotor side passages 42 b, plurality of first downstream casing side passages 43 e, plurality of first downstream rotor side passages 43 b, plurality of second downstream casing side passages 44 e, plurality of second downstream rotor side passages 44 b, plurality of first through fifth bond side passages 45 through 49 , and plurality of outlet flange passages 55 are also formed in the transition piece 20 e of the present embodiment, similarly to the transition piece 20 c of the fourth embodiment.
  • a plurality of third downstream casing side passages 45 e are further formed in the transition piece 20 e of the present embodiment.
  • the third downstream casing side passage 45 e is provided in the second downstream casing side passage 44 e.
  • a passage length of the first upstream rotor side passage 41 b and a passage length of the second upstream rotor side passage 42 b are both L 1 b , similarly to the third embodiment.
  • a passage length of the first downstream rotor side passage 43 b and a passage length of the second downstream rotor side passage 44 b are both L 2 b .
  • the passage length L 2 b is shorter than the passage length L 1 b .
  • a passage length of the first upstream casing side passage 41 e and a passage length of the second upstream casing side passage 42 e are both L 1 c .
  • a passage length of the first downstream casing side passage 43 e , passage length of the second downstream casing side passage 44 e, and passage length of the third downstream casing side passage 45 e are all L 2 c.
  • the passage length L 2 c is shorter than the passage length L 1 c .
  • the passage length L 1 c is shorter than the passage length L 1 b .
  • the passage length L 2 c is shorter than the passage length L 2 b. Note that so long as the passage length L 1 c is shorter than the passage length L 1 b , the passage length L 1 c may be longer or shorter than the passage length L 2 b.
  • a passage cross-sectional area of the first upstream rotor side passage 41 b , passage cross-sectional area of the second upstream rotor side passage 42 b, passage cross-sectional area of the first upstream casing side passage 41 e, passage cross-sectional area of the second upstream casing side passage 42 e, passage cross-sectional area of the first downstream rotor side passage 43 b, passage cross-sectional area of the second downstream rotor side passage 44 b, passage cross-sectional area of the first downstream casing side passage 43 e, passage cross-sectional area of the second downstream easing side passage 44 e, and passage, cross-sectional area of the third downstream casing side passage 45 e are all S 1 (refer to FIG. 5 , FIG.
  • the number of the first upstream rotor side passages 41 b, number of the second upstream rotor side passages 42 b, number of the first upstream casing side passages 41 e, number of the second upstream casing side passages 42 e, number of the first downstream rotor side passages 43 b, number of the second downstream rotor side passages 44 b, number of the first downstream casing side passages 43 e, number of the second downstream casing side passages 44 e , and number of the third downstream casing side passages 45 e are mutually the same, similarly to the third embodiment.
  • a (S 1 /L 2 b ) of the passage cross-sectional area S 1 to the passage length L 2 b of the downstream rotor side passages 43 b, 44 b provided in the downstream side region Rdb within the rotor side region Rcr which is one circumferential region is larger than a ratio (S 1 /L 1 b ) of the passage cross-sectional area S 1 to the passage length L 1 b of the upstream rotor side passages 41 b, 42 b provided in the upstream side region Rub within the rotor side region Rcr.
  • the ratio (S 1 /L 1 c ) of the passage cross-sectional area S 1 to the passage length L 1 c of the upstream casing side passages 41 e, 42 e provided in the casing side region Rcc within the upstream side region Rub which is one axial region is larger than the ratio (S 1 /L 1 b ) of the passage cross-sectional area S 1 to the passage length L 1 b of the upstream rotor side passages 41 b, 42 b provided in the rotor side region Rcr within the upstream side region Rub.
  • the ratio (S 1 /L 2 c ) of the passage cross-sectional area S 1 to the passage length L 2 c of the downstream casing side passages 43 e, 44 e, 45 e provided in the casing side region Rcc within the downstream side region Rdb which is one axial region is larger than the ratio (S 1 /L 2 b ) of the passage cross-sectional area S 1 to the passage length L 2 b of the downstream rotor side passages 43 b, 44 b provided in the rotor side region Rcr within the downstream side region Rd.
  • the cooling performance of the compressed air A in the downstream side region Rd can be increased, similarly to the third embodiment. Furthermore, in the present embodiment, the cooling preformance of the compressed air A in the casing side region Rcc can be increased, similarly to the fourth and fifth embodiments.
  • a method of making the passage length L 1 c of the cooling passage 35 in the casing side region Rcc shorter than the passage length L 1 b of the cooling passage 35 in the rotor side region Rcr is used as a method of increasing the ratio of the passage cross-sectional area to the passage length of the cooling passage 35 provided in the casing side region Rcc within one axial region.
  • the fourth embodiment can be said to have a ratio of the passage cross-sectional area to the passage length of the cooling passage 35 provided in the casing side region Rcc within one axial region that is larger than a ratio of the cross-sectional area to the passage length of the cooling passage 35 provided in the rotor side region Rcr within the same axial region.
  • the first upstream casing side passage 41 d, second upstream casing side passage 42 d, first downstream casing side passage 43 d, and second downstream casing side passage 44 d of the fifth embodiment may be used as the first upstream casing side passage 41 c, second upstream casing side passage 42 c, first downstream casing side passage 43 c, and second downstream casing side passage 44 c in the fourth embodiment.
  • first upstream casing side passage 41 c, second upstream casing side passage 42 c, first downstream casing side passage 43 c, and second downstream casing side passage 44 c of the fourth embodiment may be used as the first upstream casing side passage 41 d, second upstream casing side passage 42 d, first downstream casing side passage 43 d, and second downstream casing side passage 44 d in the fifth embodiment.
  • first upstream casing side passage 41 e, second upstream casing side passage 42 e, first downstream casing side passage 43 e, second downstream casing side passage 44 e, and third downstream casing side passage 45 e of the sixth embodiment may be used as the first upstream casing side passage 41 d , second upstream casing side passage 42 d, first downstream casing side passage 43 d , and second downstream casing side passage 44 d in the fifth embodiment.
  • first upstream casing side passage 41 c, second upstream casing side passage 42 c, first downstream casing side passage 43 c, and second downstream casing side passage 44 c of the fourth embodiment may be used as the first upstream casing side passage 41 e, second upstream casing side passage 42 e, first downstream casing side passage 43 e, second downstream casing side passage 44 e, and third downstream casing side passage 45 e in the sixth embodiment
  • first upstream casing side passage 41 d, second upstream casing side passage 42 d, first downstream casing side passage 43 d, and second downstream casing side passage 44 d of the fifth embodiment may be used as the first upstream casing side passage 41 e , second upstream casing side passage 42 e, first downstream casing side passage 43 e , second downstream casing side passage 44 e, and third downstream casing side passage 45 e in the sixth embodiment.
  • all of the cooling passages 35 of the body portion 30 have the inlet 35 i formed at the downstream end portion of the cooling passage 35 , and the outlet 35 o formed at the upstream end portion of the cooling passage 35 .
  • some of the cooling passages 35 of the body portion 30 may have an inlet formed at an upstream end portion of the cooling passages 35 , and an outlet formed at a downstream end portion of the cooling passages 35 , depending on the shape of the body portion 30 , accessories provided in the vicinity of the body portion 30 , and the like.
  • each of the cooling passages 35 , 55 has the same cross-sectional area at any position in the axial direction Da.
  • the cross-sectional area of any of the cooling passages may be changed in accordance with positional change in the axial direction Da.
  • the body portion 30 is formed by the laminate plate 31 having the outer plate 32 and inner plate 34 .
  • the body portion 30 does not necessarily have to be formed by the laminate plate 31 , and may be formed by a single plate.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US15/544,384 2015-01-30 2016-01-25 Transition piece, combustor provided with same, and gas turbine provided with combustor Abandoned US20170370235A1 (en)

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JP2015-017840 2015-01-30
JP2015017840A JP6476516B2 (ja) 2015-01-30 2015-01-30 トランジションピース、これを備える燃焼器、及び燃焼器を備えるガスタービン
PCT/JP2016/052021 WO2016121694A1 (ja) 2015-01-30 2016-01-25 トランジションピース、これを備える燃焼器、及び燃焼器を備えるガスタービン

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US10352244B2 (en) * 2014-04-25 2019-07-16 Mitsubishi Hitachi Power Systems, Ltd. Combustor cooling structure
US20200173294A1 (en) * 2018-11-29 2020-06-04 Doosan Heavy Industries & Construction Co., Ltd. Fin-pin flow guide for efficient transition piece cooling
US11149949B2 (en) * 2016-07-25 2021-10-19 Siemens Energy Global GmbH & Co. KG Converging duct with elongated and hexagonal cooling features
US20230167747A1 (en) * 2021-09-30 2023-06-01 Mitsubishi Heavy Industries, Ltd. Transition piece, combustor, and gas turbine engine
US12018840B2 (en) * 2021-11-04 2024-06-25 Rolls-Royce Plc Combustor arrangement

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JP6564872B2 (ja) 2015-11-05 2019-08-21 三菱日立パワーシステムズ株式会社 燃焼用筒、ガスタービン燃焼器及びガスタービン
JP7370364B2 (ja) 2021-09-30 2023-10-27 三菱重工業株式会社 トランジションピース、燃焼器及びガスタービンエンジン
JP2023166152A (ja) * 2022-05-09 2023-11-21 三菱重工業株式会社 燃焼器用筒、燃焼器、及びガスタービン

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EP3252287A1 (de) 2017-12-06
EP3252287A4 (de) 2018-04-11
EP3252287B1 (de) 2019-07-17
TW201641893A (zh) 2016-12-01
KR102001746B1 (ko) 2019-07-18
JP6476516B2 (ja) 2019-03-06
TWI619909B (zh) 2018-04-01
CN107208555B (zh) 2019-05-31
CN107208555A (zh) 2017-09-26
JP2016142163A (ja) 2016-08-08
US20210123351A1 (en) 2021-04-29
US11525364B2 (en) 2022-12-13
KR20170095346A (ko) 2017-08-22
WO2016121694A1 (ja) 2016-08-04

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