WO2011070806A1 - 燃焼器とタービン部との連通構造、および、ガスタービン - Google Patents

燃焼器とタービン部との連通構造、および、ガスタービン Download PDF

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Publication number
WO2011070806A1
WO2011070806A1 PCT/JP2010/058171 JP2010058171W WO2011070806A1 WO 2011070806 A1 WO2011070806 A1 WO 2011070806A1 JP 2010058171 W JP2010058171 W JP 2010058171W WO 2011070806 A1 WO2011070806 A1 WO 2011070806A1
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WO
WIPO (PCT)
Prior art keywords
turbine
side wall
stationary blade
stage stationary
combustor
Prior art date
Application number
PCT/JP2010/058171
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
ロシック バドミール
康朗 坂元
澄生 内田
栄作 伊藤
剛 北村
哲 羽田
聡介 中村
Original Assignee
三菱重工業株式会社
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 三菱重工業株式会社 filed Critical 三菱重工業株式会社
Priority to KR1020137019998A priority Critical patent/KR101415478B1/ko
Priority to US13/500,009 priority patent/US9395085B2/en
Priority to CN201080044670.3A priority patent/CN102686949B/zh
Priority to EP10835729.4A priority patent/EP2511612B1/en
Priority to KR1020127008290A priority patent/KR101377772B1/ko
Publication of WO2011070806A1 publication Critical patent/WO2011070806A1/ja

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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
    • F23R3/42—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
    • 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
    • F23R3/60—Support structures; Attaching or mounting means
    • 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
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • 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
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion

Definitions

  • the present invention relates to a communication structure between a combustor and a turbine section, and a gas turbine.
  • a gas turbine includes a compressor, a combustor, and a turbine section as main components, the compressor and the turbine are connected by a rotating shaft, and the combustor is disposed between the compressor and the turbine section.
  • air that is a working fluid is sucked and compressed by a compressor that is rotationally driven by a rotating shaft, and the compressed air is introduced into a combustor.
  • fuel is mixed with compressed air, and the air-fuel mixture is combusted to generate high-temperature and high-pressure combustion gas.
  • the combustion gas is discharged from the combustor to the turbine unit, and the turbine unit is driven to rotate.
  • the high-temperature working fluid containing the combustion gas discharged from the combustor flows between the turbine first stage stationary blades of the turbine section and then flows into the turbine first stage moving blades.
  • part of the energy of the working fluid is converted into rotational energy and transmitted to the rotating shaft as a rotational driving force.
  • the rear end of the transition piece of the combustor and the front edge of the turbine first stage stationary blade located at the uppermost stream of the turbine section are arranged with a space therebetween. Therefore, part of the high-temperature working fluid that flows from the combustor toward the turbine section flows into the gap between the rear end of the tail cylinder and the front edge of the turbine first stage stationary blade, and loss due to this flow occurs. There was a problem. In addition, there is a problem that the leading edge of the turbine first stage stationary blade is heated by the high-temperature working fluid flowing into the gap, and a large amount of cooling fluid is required.
  • Patent Document 1 As a technique for solving the above-described problem, a method of bringing a turbine first stage stationary blade closer to a combustor has been proposed (for example, see Patent Document 1).
  • a cooling fluid that wraps the leading edge of the turbine first stage stationary blade at the rear end of the combustor and cools the turbine first stage stationary blade from the tail cylinder through a slit formed in the front edge is supplied. ing.
  • the high temperature working fluid did not collide with the front edge of the turbine 1st stage stationary blade, and the cooling fluid used for cooling the front edge became unnecessary.
  • Patent Document 1 describes that the combustor and the turbine first stage stationary blade are integrated, the shape of the inner wall of the combustor in which the high-temperature working fluid flows is disclosed. It wasn't.
  • the present invention has been made in order to solve the above-described problem, and includes a combustor and a turbine unit that can suppress the generation of loss and reduce the flow rate of a cooling fluid used for cooling turbine blades. It is an object of the present invention to provide a communication structure and a gas turbine.
  • the communication structure between the combustor and the turbine section according to the first aspect of the present invention includes a compressed air supplied from a compressor and a fuel nozzle inside a plurality of cylinders arranged adjacent to each other around a rotating shaft.
  • a combustor that generates combustion gas by mixing and supplying the fuel supplied from the combustion chamber, and a plurality of the combustion gases that pass through a turbine stage including a plurality of turbine stationary blades and turbine blades arranged around the rotation shaft
  • a turbine part that generates a rotational driving force by causing at least a part of the turbine first stage stationary blade closest to the combustor to be adjacent to one cylinder and the other.
  • the distance from the front edge of the turbine first stage stationary blade disposed downstream of the side wall of the cylindrical body to the end on the turbine section side of the side wall is From the inner surface of the side wall of one cylinder body, there is a following distance to the inner surface of the side wall of the other of the cylindrical body.
  • the turbine first stage stationary blade located downstream of the side wall close to the end of the side wall on the turbine part side, Inflow of combustion gas between the side wall and the turbine first stage stationary blade is suppressed. Therefore, generation
  • the inner surface of the side wall may have a shape that smoothly connects to the outer surface of the turbine first stage stationary blade disposed downstream of the side wall. desirable.
  • the combustion gas generated inside the cylindrical body flows along the outer surface of the turbine first stage stationary blade connected smoothly after flowing along the inner surface of the side wall. Therefore, a step or the like is formed between the inner surface of the side wall and the outer surface of the turbine first stage stationary blade, and the flow of the combustion gas is less disturbed than in the case of discontinuity, and the generation of loss is suppressed. Furthermore, since the flow of combustion gas on the outer surface of the turbine first stage stationary blade is less likely to be disturbed, for example, in a method of cooling the turbine first stage stationary blade by flowing a cooling fluid on the outer surface of the turbine first stage stationary blade in the form of a film, Is suppressed.
  • the turbine first stage stationary blade disposed downstream of the side wall as compared with the turbine first stage stationary blade disposed other than the downstream side of the side wall includes: It is desirable that the number of cooling holes through which the cooling fluid used for cooling the turbine first stage stationary blade flows out around the turbine first stage stationary blade is small.
  • the turbine first stage stationary blade disposed downstream of the side wall is less likely to collide with the combustion gas at the leading edge than the turbine first stage stationary blade disposed elsewhere. Therefore, in comparison with a turbine first stage stationary blade arranged at a position other than the downstream side of the side wall, the cooling fluid flows out around the turbine first stage stationary blade in the turbine first stage stationary blade arranged at the downstream side of the sidewall, and the cooling fluid is formed in a film form along the outer surface. It is possible to reduce the number of cooling holes and shower head cooling holes that flow through. In other words, the flow rate of the cooling fluid used for cooling the turbine first stage stationary blade disposed downstream of the side wall can be reduced as compared with the turbine first stage stationary blade disposed other than downstream of the side wall.
  • the gap between the side wall in the one cylindrical body and the side wall in the other cylindrical body is cooled to cool the side wall. It is desirable that the cooling fluid after flowing the fluid and cooling the side wall flow from the downstream end of the side wall along the periphery of the turbine first stage stationary blade disposed downstream of the side wall.
  • the cooling fluid that flows between the side walls and cools the side walls is discharged from the outflow passage that is a slot-shaped gap formed between the downstream end of the side wall and the first stage stationary blade of the turbine.
  • the first stage stationary blade of the turbine disposed downstream of the side wall can be effectively cooled by the cooling fluid. Therefore, it is possible to reduce the flow rate of the cooling fluid that is supplied to the turbine first stage stationary blade disposed downstream of the side wall and cools the turbine first stage stationary blade.
  • the downstream end of the side wall is deflected in a direction in which the turbine first stage stationary blade deflects the combustion gas.
  • the flow of the combustion gas can be deflected by the downstream end of the side wall and the turbine first stage stationary blade. Furthermore, since the flow of combustion gas is deflected by the side wall and the turbine first stage stationary blade, the dimension in the axial direction related to the rotating shaft in the communication structure between the combustor and the turbine section can be reduced. On the other hand, when the deflection by the side wall can be increased, the deflection by the turbine first stage stationary blade can be reduced, and therefore the dimension in the axial direction can be further reduced.
  • the deflected portion of the side wall forms a blade shape together with the turbine first stage stationary blade disposed downstream of the side wall in a sectional view. It is desirable to do.
  • the cross-section of the deflected portion of the side wall has a shape that forms the blade shape together with the turbine first stage stationary blade, so that the combustion gas flow is effectively reduced compared to the case where the blade shape is not configured. Can be deflected.
  • a gas turbine mixes and combusts a compressor that compresses air, compressed air supplied from the compressor, and fuel supplied from a fuel nozzle, and generates combustion gas.
  • a combustor to be generated; a turbine unit that converts a part of energy of the combustion gas into a rotational driving force; and a rotary shaft that transmits the rotational driving force from the turbine unit to the compressor.
  • the gas turbine has a communication structure between the combustor of the present invention and the turbine section.
  • the gas turbine according to the second aspect of the present invention has a communication structure between the combustor of the present invention and the turbine section, so that the generation of loss is suppressed and the cooling fluid used for cooling the turbine blades is reduced. Since the flow rate can be reduced, the efficiency of the entire gas turbine can be improved.
  • the turbine first stage stationary blade located downstream of the side wall is disposed close to the end of the side wall on the turbine section side, thereby It is possible to suppress the generation of loss in the turbine and to reduce the flow rate of the cooling fluid used for cooling the turbine blades.
  • FIG. 2 is a partially enlarged view illustrating a communication structure between a combustor and a turbine unit in FIG. 1. It is the elements on larger scale explaining the communication structure of the combustor and turbine part in the gas turbine which concerns on the 2nd Embodiment of this invention. It is an enlarged view explaining the structure of the side wall of FIG. 4, and a turbine 1st stage stationary blade. It is the elements on larger scale explaining the communication structure of the combustor and turbine part in the gas turbine which concerns on the 3rd Embodiment of this invention.
  • FIG. 1 is a schematic diagram illustrating the configuration of the gas turbine of the present embodiment.
  • the gas turbine 1 of the present invention will be described as applied to one that drives a generator G.
  • the target driven by the gas turbine 1 is limited to the generator G. It is not intended to be limited, and other devices may be used without any particular limitation.
  • the gas turbine 1 is mainly provided with a compressor 2, a combustor 3, a turbine unit 4, and a rotating shaft 5.
  • the compressor 2 sucks and compresses atmospheric air, which is external air, and supplies the compressed air to the combustor 3.
  • the compressor 2 includes an inlet guide vane (not shown) that adjusts the flow rate of the air flowing into the compressor 2, a first stage moving blade (not shown) that compresses the air that flows in, and a first stage stationary blade (not shown). Etc.) are provided.
  • FIG. 2 is a schematic diagram illustrating the configuration of the compressor, the turbine unit, and the combustor of FIG.
  • the combustor 3 is a can-type combustor that mixes the air compressed by the compressor 2 and the fuel supplied from the outside and mixes the mixture. Is used to generate a high-temperature combustion gas.
  • the combustor 3 is mainly provided with an air inlet 31, a fuel nozzle 32, and a transition piece (tubular body) 33.
  • the air inlet 31 guides the air compressed by the compressor 2 to the inside of the tail cylinder 33, and is arranged in an annular shape around the fuel nozzle 32. Further, the air inlet 31 gives a flow velocity component in the swirl direction to the air flowing into the tail tube 33 and forms a circulation flow inside the tail tube 33.
  • the air inlet 31 may have a known shape and is not particularly limited.
  • the fuel nozzle 32 sprays fuel supplied from the outside toward the inside of the tail cylinder 33.
  • the fuel sprayed from the fuel nozzle 32 is agitated by the flow of air formed by the air inlet 31 and becomes a mixture of fuel and air.
  • the fuel nozzle 32 may have a known shape and is not particularly limited.
  • the tail cylinder 33 is a cylindrical member that forms a flow path extending from the air inlet 31 and the fuel nozzle 32 toward the inflow portion of the turbine section 4.
  • the transition piece 33 has a mixture of fuel and air and a combustion gas generated by the combustion of the mixture flowing in the inside thereof.
  • the cross-sectional shape in the vicinity of the fuel nozzle 32 in the tail cylinder 33 is substantially circular, and the cross-sectional shape in the vicinity of the turbine portion 4 is substantially rectangular. Therefore, the cross-sectional shape of the tail cylinder 33 continuously changes from a substantially circular shape to a substantially rectangular shape from the fuel nozzle 32 toward the turbine portion 4.
  • the turbine unit 4 receives a supply of high-temperature gas generated by the combustor 3 to generate a rotational driving force, and transmits the generated rotational driving force to the rotating shaft 5. is there.
  • FIG. 3 is a partially enlarged view for explaining a communication structure between the combustor and the turbine portion in FIG. 1.
  • the turbine section 4 is provided with a turbine first stage stationary blade (turbine stationary blade) 4SV and a turbine first stage stationary blade (turbine blade) 4RB.
  • the turbine first stage stationary blade 4SV constitutes a turbine stage together with the turbine first stage moving blade 4RB, and generates a rotational driving force from the high-temperature gas flowing into the turbine section 4 together with the turbine first stage moving blade 4RB.
  • the turbine first stage stationary blades 4SV are arranged at equal intervals around the rotary shaft 5 at positions facing the downstream end (lower end in FIG. 3) of the tail cylinder 33 in the combustion gas flow, and in the radial direction (see FIG. 3 is a plurality of wings arranged so as to extend along a direction perpendicular to the sheet of FIG. Further, the turbine first stage stationary blade 4SV deflects the combustion gas flowing from the combustor 3 into the row of turbine first stage stationary blades 4SV in the circumferential direction (left-right direction in FIG. 3).
  • the number of turbine first stage stationary blades 4SV is an integral multiple of the number of combustors 3, and at least a part of the turbine first stage stationary blades 4 SV is formed of the transition piece 33 in the combustor 3 as shown in FIG. 3. It is arranged downstream of the side wall 34.
  • the distance L from the front edge LE of the turbine first stage stationary blade 4SV to the end of the side wall 34 on the turbine unit 4 side is such that the side wall 34 of one tail cylinder 33, the side wall 34 of the other tail cylinder 33, and ,
  • the thickness T including the gap between the side walls 34, 34 in other words, the thickness from the inner surface of the side wall 34 of one tail tube 33 adjacent to each other to the inner surface of the side wall 34 of the other tail tube 33
  • the turbine first stage stationary blade 4SV is arranged so as to be equal to or less than T (hereinafter referred to as “thickness T related to the side wall 34”).
  • the turbine first stage stationary blade 4SV is provided with a cavity 41 supplied with cooling air (cooling fluid) that protects the turbine first stage stationary blade 4SV from the heat of the high-temperature gas flowing therearound, and the cooling air is supplied from the cavity 41 to the turbine first stage stationary blade 4SV.
  • cooling air cooling fluid
  • Many cooling holes 42 are arranged at the front edge LE of the turbine first stage stationary blade 4SV having a high heat load, and the front edge LE has a shower head shape.
  • the turbine first stage stationary blade 4SV arranged downstream of the side wall 34 and the other turbine first stage stationary blade 4SV is compared.
  • the number of cooling holes 42 formed in the front edge LE of 4SV is reduced.
  • the turbine first stage moving blade 4RB constitutes a turbine stage together with the turbine first stage stationary blade 4SV, and generates a rotational driving force based on the combustion gas deflected by the turbine first stage stationary blade 4SV.
  • the turbine first stage moving blades 4RB are arranged at equal intervals around the rotation axis at positions downstream of the turbine first stage stationary blades 4SV in the combustion gas flow (positions on the right side in FIG. 2) and in the radial direction (in FIG. 2). A plurality of wings arranged so as to extend in the vertical direction). Further, the turbine first stage moving blade 4RB receives the combustion gas deflected by the turbine first stage stationary blade 4SV and is driven to rotate around the rotation shaft 5. Further, cooling air for protecting the turbine first stage moving blade 4RB from the heat of the combustion gas flowing therearound is supplied to the turbine first stage moving blade 4RB.
  • the turbine section 4 may be provided with only the turbine first stage stationary blade 4SV and the turbine first stage stationary blade 4RB as described above, and further, the turbine second stage stationary blade and the turbine second stage stationary blade, and the turbine third stage stationary blade and A turbine three-stage rotor blade or the like may be provided and is not particularly limited.
  • the gas turbine 1 sucks air (air) when the compressor 2 is rotationally driven.
  • the sucked air is compressed by the compressor 2 and sent out toward the combustor 3.
  • the compressed air flowing into the combustor 3 is mixed with fuel supplied from the outside in the combustor 3.
  • the mixture of air and fuel is combusted in the combustor 3 to generate combustion gas.
  • the combustion gas generated in the combustor 3 is supplied from the combustor 3 to the turbine unit 4 downstream.
  • the combustion gas flows out from the transition piece 33 of the combustor 3 and flows into the cascade of the turbine first stage stationary blade 4SV in the turbine section 4.
  • the turbine first stage stationary blade 4SV is disposed close to the tail cylinder 33, the combustion gas flows between the turbine first stage stationary blade 4SV disposed downstream of the side wall 34 of the tail cylinder 33 and the tail cylinder 33. It is difficult to cause loss due to this flow.
  • the leading edge LE of the turbine first stage stationary blade 4SV arranged downstream of the side wall 34 is located in the wake (wake) of the side wall 34, the combustion gas does not easily collide with the leading edge LE.
  • the combustion gas that has flowed into the cascade of the first stage stationary blade 4SV of the turbine is deflected in the circumferential direction (leftward in FIG. 3) about the rotation shaft 5, and as shown in FIG. It flows into the 4RB cascade.
  • the turbine first stage moving blade 4RB is rotationally driven by the deflected combustion gas.
  • the rotating shaft 5 transmits the rotational driving force extracted in the turbine unit 4 to the compressor 2 and the generator G.
  • the turbine first stage stationary blade 4SV located downstream of the side wall 34 is disposed close to the end of the side wall 34 on the turbine section 4 side, so that the space between the side wall 34 and the turbine first stage stationary blade 4SV is disposed. Inflow of combustion gas is suppressed. Therefore, it is possible to suppress the occurrence of loss due to the combustion gas inflow between the side wall 34 and the turbine first stage stationary blade 4SV.
  • the leading edge LE of the turbine first stage stationary blade 4SV is disposed in a relatively cool wake (wake) of the side wall 34, and the turbine first stage stationary blade 4SV is arranged. It becomes difficult for high-temperature combustion gas to collide directly with the leading edge LE of 4SV. Therefore, the necessity of cooling the leading edge LE in the turbine first stage stationary blade 4SV is reduced, and the flow rate of the cooling air necessary for cooling can be reduced.
  • the turbine first stage stationary blade 4SV disposed downstream of the side wall 34 is less likely to collide with the combustion gas at the leading edge LE than the turbine first stage stationary blade 4SV disposed elsewhere. Therefore, compared with the turbine first stage stationary blade 4SV arranged at a position other than the downstream side of the side wall 34, the cooling air flows out around the turbine first stage stationary blade 4SV in the turbine first stage stationary blade 4SV arranged at the downstream side of the side wall 34 along the outer surface.
  • the number of cooling holes 42 through which the cooling air flows in a film can be reduced. In other words, the flow rate of the cooling air used for cooling the turbine first stage stationary blade 4SV disposed downstream of the side wall 34 can be reduced as compared with the turbine first stage stationary blade 4SV disposed other than the downstream side of the side wall 34.
  • FIG. 4 is a partially enlarged view illustrating a communication structure between the combustor and the turbine section in the gas turbine according to the present embodiment.
  • symbol is attached
  • the combustor 103 in the gas turbine 101 of the present embodiment has a shape of an end portion (lower end portion in FIG. 4) on the turbine portion 104 side in the side wall 134 of the tail tube (tubular body) 133. Is different from the first embodiment.
  • the transition tubes 133 of the adjacent combustors 103 extends along the direction in which the combustion gas flows (the vertical direction in FIG. 4), and a cooling fluid such as cooling air (for example, a cooling flow path 145 through which compressed air compressed by the compressor 2 flows is provided.
  • a cooling flow path 145 through which compressed air compressed by the compressor 2 flows is provided.
  • the end of the cooling channel 145 on the turbine section 104 side is open to the end of the side wall 134 of the tail tube 133 on the turbine section 104 side (the lower end of FIG. 4).
  • FIG. 5 is an enlarged view for explaining the configuration of the side wall of FIG. 4 and the turbine first stage stationary blade.
  • the inner surface of the side wall 134 is formed in a shape that smoothly connects with the outer surface of the turbine first stage stationary blade 104 SV adjacent to the side wall 134. Yes.
  • the side wall 134 is formed so that the width of the side wall 134 increases toward the turbine first stage stationary blade 104SV.
  • a turbine first stage stationary blade 4SV and a turbine first stage stationary blade (turbine stationary blade) 104SV are provided in the turbine section 104 of the gas turbine 101 of the present embodiment.
  • the turbine first stage stator blade 4SV and the turbine first stage stator blade 104SV constitute a turbine stage together with the turbine first stage rotor blade 4RB, and generate rotational driving force from the combustion gas flowing into the turbine section 104 together with the turbine first stage rotor blade 4RB. It is. Further, the turbine first stage stationary blade 4SV and the turbine first stage stationary blade 104SV are arranged at equal intervals on the same circumference around the rotation shaft 5 and extend along the radial direction (perpendicular to the paper surface of FIG. 4). Are a plurality of wings.
  • the turbine first stage stationary blade 4SV is a turbine stationary blade disposed between the side walls 134, in other words, a turbine stationary blade disposed between the turbine first stage stationary blades 104SV.
  • the turbine first stage stationary blade 104SV is disposed between the turbine stationary blades disposed in a position facing the downstream end (lower end in FIG. 4) of the tail tube 133 in the combustion gas flow, in other words, between the turbine first stage stationary blades 4SV.
  • Turbine vane Unlike the turbine first stage stationary blade 104SV, the turbine first stage stationary blade 104SV is not formed with a cavity 41 into which cooling air is supplied, or a cooling hole 42 through which the cooling air flows out of the cavity 41 around the turbine first stage stationary blade 104SV.
  • the cooling air after flowing through the cooling channel 145 is communicated with the cooling channel 145 of the side wall 134.
  • An outflow channel 146 is provided to flow out in the form of a film along the periphery of the turbine first stage stationary blade 104SV.
  • the outflow passage 146 is an elongated slot extending from the cooling passage 145 toward the outside of the side wall 134 in the downstream direction of the combustion gas flow (the right direction in FIG. 5).
  • the combustion gas flows out of the transition piece 133 of the combustor 103 and flows into the cascade of the turbine first stage stationary blade 4SV and the turbine first stage stationary blade 104SV in the turbine unit 104.
  • the combustion gas that flows along the inner surface of the side wall 134 in the tail tube 133 flows from the inner surface of the side wall 134 along the outer surface of the turbine first stage stationary blade 104SV and is deflected.
  • the cooling air flowing through the cooling flow path 145 and cooling the tail cylinder 133 flows out along the outer surface of the turbine first stage stationary blade 104SV via the outflow flow path 146.
  • the cooling air flows in the form of a film along the outer surface of the turbine first stage stationary blade 104SV, and cools the turbine first stage stationary blade 104SV.
  • the combustion gas flowing in the center of the transition piece 133 collides with the turbine first stage stationary blade 4SV and is deflected by flowing along the surface of the turbine first stage stationary blade 4SV, as in the first embodiment.
  • the combustion gas generated inside the tail tube 133 flows along the outer surface of the turbine first stage stationary blade 104SV that is smoothly connected after flowing along the inner surface of the side wall 134. Therefore, compared with the case where a step is formed between the inner surface of the side wall 134 and the outer surface of the turbine first stage stationary blade 104SV, the flow of the combustion gas is less likely to be disturbed, and the generation of loss is suppressed. .
  • the cooling air flowing out from the outflow passage 146 flows on the outer surface of the turbine first stage stationary blade 104SV in the form of a film to cool the turbine first stage stationary blade 104SV. In the method, it is possible to suppress a decrease in cooling efficiency of the turbine first stage stationary blade 104SV.
  • the turbine first stage stationary blade 104SV disposed downstream of the side wall 134 can be cooled by the cooling air. Therefore, in order to cool the turbine first stage stationary blade 104SV, the flow rate of the cooling air supplied to the turbine first stage stationary blade 104SV can be reduced.
  • FIG. 6 is a partially enlarged view for explaining the communication structure between the combustor and the turbine section in the gas turbine according to the present embodiment.
  • symbol is attached
  • the combustor 203 in the gas turbine 201 of the present embodiment has a shape of an end portion (lower end portion in FIG. 6) on the turbine portion 204 side in the side wall 234 of the tail tube (tubular body) 233. Is different from the first embodiment.
  • a deflecting portion deflected in a direction in which the turbine first stage stationary blade 4SV deflects the combustion gas flow (left direction in FIG. 6) is provided on the side wall 234 of the transition piece 233 in the combustor 203.
  • 235 is provided.
  • the deflection unit 235 is an end of the side wall 234 on the turbine unit 204 side, and is a portion adjacent to the turbine first stage stationary blade 204SV.
  • the deflecting portion 235 has the side wall 234 deflected as it is, the size in the thickness direction of the deflecting portion 235 and the size in the thickness direction of the side wall 234 other than the deflecting portion 235 are the same.
  • the transition piece 233 and the side wall 234 are provided with cooling passages 145 that extend along the direction in which combustion gas flows (the vertical direction in FIG. 6) and into which cooling fluid such as cooling air flows. ing.
  • the cooling flow path 145 further extends along the deflection unit 235 in the deflection unit 235 in the side wall 234.
  • the end of the cooling channel 145 on the turbine unit 204 side is open to the end of the deflecting unit 235 of the side wall 234 on the turbine unit 204 side (the lower end of FIG. 6).
  • a turbine first stage stationary blade 4SV and a turbine first stage stationary blade (turbine stationary blade) 204SV are provided in the turbine section 204 of the gas turbine 201 of the present embodiment.
  • the turbine first stage stator blade 4SV and the turbine first stage stator blade 204SV constitute a turbine stage together with the turbine first stage rotor blade 4RB, and generate rotational driving force from the combustion gas flowing into the turbine section 204 together with the turbine first stage rotor blade 4RB. It is. Further, the turbine first stage stationary blade 4SV and the turbine first stage stationary blade 204SV are arranged at equal intervals on the same circumference around the rotation shaft 5, and extend along the radial direction (perpendicular to the paper surface of FIG. 6). Are a plurality of wings.
  • the turbine first stage stationary blade 4SV is a turbine stationary blade disposed between the side wall 234 and the deflecting unit 235, in other words, a turbine stationary blade disposed between the turbine first stage stationary blade 204SV.
  • the turbine first stage stationary blade 204SV is disposed between the turbine stationary blade 4SV and the turbine stationary blade 4SV disposed at a position facing the downstream end (lower end in FIG. 6) of the deflection unit 235 in the combustion gas flow. Turbine vane.
  • the turbine first stage stationary blade 204SV has a smaller cross-sectional area than the turbine first stage stationary blade 4SV, and is the same as the thickness direction dimension of the deflecting portion 235 where the dimension in the thickness direction of the turbine first stage stationary blade 204SV is the largest. Yes.
  • the turbine first stage stationary blade 204SV is not formed with a cavity 41 to which cooling air is supplied, or a cooling hole 42 through which the cooling air flows out from the cavity 41 around the turbine first stage stationary blade 204SV.
  • the turbine first stage stationary blade 204SV and the deflecting unit 235 communicates with the cooling channel 145 of the deflecting unit 235, and the cooling air after flowing through the cooling channel 145 is converted into the turbine.
  • An outflow passage 146 is provided to flow out around the first stage stationary blade 204SV.
  • the outflow channel 146 is a through-hole extending from the cooling channel 145 toward the outside of the deflection unit 235 in the downstream direction of the combustion gas flow (the lower left direction in FIG. 6).
  • the combustion gas flows out from the transition piece 233 of the combustor 203 and flows into the cascade of the turbine first stage stationary blade 4 SV and the turbine first stage stationary blade 204 SV in the turbine unit 204.
  • the combustion gas that has flowed along the inner surface of the side wall 234 in the tail cylinder 233 flows and is deflected along the inner surface of the deflecting portion 235 of the side wall 234 and the outer surface of the turbine first stage stationary blade 204SV.
  • the cooling air that has flowed through the cooling flow path 145 to cool the tail cylinder 233 and the deflecting unit 235 flows out along the outer surface of the turbine first stage stationary blade 204 SV via the outflow flow path 146.
  • the cooling air flows in the form of a film along the outer surface of the turbine first stage stationary blade 204SV to cool the turbine first stage stationary blade 204SV.
  • the combustion gas that has flowed inside the transition piece 233 collides with the turbine first stage stationary blade 4SV and is deflected by flowing along the outer surface of the turbine first stage stationary blade 4SV, as in the first embodiment.
  • the flow of the combustion gas can be deflected by the deflecting unit 235 that is the downstream end of the side wall 234 and the turbine first stage stationary blade 204SV. Further, since the flow of the combustion gas is deflected by the deflection unit 235 and the turbine first stage stationary blade 204SV, the dimension in the axial direction (vertical direction in FIG. 6) related to the rotating shaft 5 in the communication structure between the combustor 203 and the turbine unit 204 is reduced. can do. When the deflection by the side wall 234 can be further increased, the deflection by the turbine first stage stationary blade 204SV can be reduced, and thus the axial dimension of the rotating shaft 5 can be further reduced.
  • FIG. 7 is a partially enlarged view for explaining the communication structure between the combustor and the turbine section in the gas turbine according to the present embodiment.
  • symbol is attached
  • the turbine section 304 in the gas turbine 301 of the present embodiment is different from the first embodiment in the shape and arrangement of a turbine first stage stationary blade (turbine stationary blade) 304SV.
  • the turbine first stage stationary blade 304SV constitutes a turbine stage together with the turbine first stage moving blade 4RB, and generates a rotational driving force from the combustion gas flowing into the turbine section 304 together with the turbine first stage moving blade 4RB. Furthermore, the turbine first stage stationary blades 304SV are arranged on the same circumference around the rotating shaft 5 at equal intervals, and are arranged so as to extend along the radial direction (perpendicular to the plane of FIG. 7). The wings.
  • the turbine first stage stationary blade 304SV is disposed at a position facing the downstream end (lower end in FIG. 7) of the side wall 334 of the tail cylinder 333 in the combustion gas flow. That is, the same number of turbine first stage stationary blades 304SV as the combustors 303 are provided.
  • the turbine first stage stationary blade 304SV has a similar shape and a larger cross-sectional area than the turbine first stage stationary blade 4SV in the first embodiment or the like. Specifically, the leading edge LE of the turbine first stage stationary blade 304SV is disposed at a position equal to or less than the thickness T with respect to the sidewall 334 from the downstream end of the side wall 334, and the trailing edge TE of the turbine first stage stationary blade 304SV is conventional. The turbine is disposed at the same position as the trailing edge TE of the first-stage turbine vane.
  • the combustion gas flows out of the transition piece 333 of the combustor 303 and flows into the cascade of the turbine first stage stationary blades 304 SV in the turbine unit 304.
  • the combustion gas that flows along the inner surface of the side wall 334 in the tail cylinder 333 flows along the outer surface of the turbine first stage stationary blade 304SV and is deflected.
  • the cooling air that has flowed through the cooling flow path 145 to cool the tail cylinder 333 flows out from the downstream end of the side wall 334 along the outer surface of the turbine first stage stationary blade 304SV.
  • the cooling air flows in the form of a film along the outer surface of the turbine first stage stationary blade 304SV to cool the turbine first stage stationary blade 304SV.
  • the number of turbine first stage stationary blades 304SV can be reduced as compared with the first embodiment or the like. Therefore, it is possible to suppress a decrease in the flow velocity of the combustion gas due to friction or the like acting between the turbine first stage stationary blade 304SV and the combustion gas, and it is possible to suppress the occurrence of loss due to this.
  • FIG. 8 is a partially enlarged view for explaining the communication structure between the combustor and the turbine section in the gas turbine according to the present embodiment.
  • symbol is attached
  • the combustor 403 in the gas turbine 401 of the present embodiment has a shape of an end portion (lower end portion in FIG. 8) on the turbine portion 404 side in the side wall 434 of the tail tube (tubular body) 433. Is different from the first embodiment.
  • a deflection unit 435 that deflects the combustion gas flow in the left direction in FIG. 8 is provided on the side wall 434 of the tail cylinder 433 in the combustor 403.
  • the deflecting unit 435 is an end of the side wall 434 on the turbine unit 404 side and is adjacent to the turbine first stage stationary blade 404SV.
  • the deflecting portion 435 is formed such that its cross section forms a blade shape together with the turbine first stage stationary blade 404SV.
  • the upstream end portion (upper end portion in FIG. 8) of the deflection portion 435 in the combustion gas flow is set to a position equivalent to the front edge LE of the turbine first stage stationary blade 304SV of the fourth embodiment.
  • cooling flow path 145 As shown in FIG. 8, between the adjacent tail cylinders 433, it extends along the direction in which the combustion gas flows (the vertical direction in FIG. 8), and is cooled by a cooling fluid such as cooling air (for example, compressed by the compressor 2).
  • a cooling channel 145 through which (compressed air) flows is provided.
  • the cooling flow path 145 further extends along the deflection section 435 between the deflection sections 435 in the adjacent side walls 434.
  • An end portion of the cooling flow path 145 is opened to a downstream end portion (lower end portion in FIG. 8) of the deflecting portion 435 of the side wall 434.
  • a turbine first stage stationary blade (turbine stationary blade) 404SV is provided in the turbine section 404 of the gas turbine 401 of the present embodiment.
  • the turbine first stage stationary blade 404SV constitutes a turbine stage together with the turbine first stage moving blade 4RB, and generates a rotational driving force from the combustion gas flowing into the turbine section 404 together with the turbine first stage moving blade 4RB. Furthermore, the turbine first stage stationary blades 404SV are arranged at equal intervals on the same circumference around the rotation shaft 5 and are arranged so as to extend along the radial direction (perpendicular to the paper surface of FIG. 8). The wings.
  • the turbine first stage stationary blade 404SV is disposed at a position facing the downstream end portion (lower end portion in FIG. 8) of the deflecting portion 435 in the combustion gas flow.
  • the turbine first stage stationary blade 404SV has a smaller cross-sectional area than the turbine first stage stationary blade 4SV of the first embodiment, and forms a blade shape together with the deflecting portion 435.
  • the trailing edge TE of the turbine first stage stationary blade 404SV is disposed at the same position as the trailing edge TE of the turbine first stage stationary blade 4SV in the first embodiment or the like.
  • the turbine first stage stationary blade 404SV has a cavity 41 to which cooling air is supplied, and a cooling hole 42 through which the cooling air flows from the cavity 41 to the periphery of the turbine first stage stationary blade 404SV. Not formed.
  • the cooling flow path 145 communicates with the cooling air after flowing through the cooling flow path 145 to the turbine first stage stationary blade 404SV.
  • An outflow channel 146 is provided to flow out in the form of a film along the outer surface.
  • the outflow channel 146 is an elongated slot extending from the cooling channel 145 toward the outside of the deflecting unit 435 in the downstream direction of the combustion gas flow (the lower left direction in FIG. 8).
  • the combustion gas flows out from the transition piece 433 of the combustor 403 and flows into the cascade of the turbine first stage stationary blade 404 SV in the turbine unit 404.
  • the combustion gas flowing along the inner surface of the side wall 434 in the tail cylinder 433 flows along the inner surface of the deflecting portion 435 of the side wall 434 and the outer surface of the turbine first stage stationary blade 404SV and is deflected.
  • the cooling air that has flowed through the cooling flow path 145 and cooled the tail cylinder 433 and the deflecting unit 435 flows out along the outer surface of the turbine first stage stationary blade 404SV via the outflow flow path 146.
  • the cooling air flows in a film shape along the outer surface of the turbine first stage stationary blade 404SV, and cools the turbine first stage stationary blade 404SV.
  • the cross section of the deflecting portion 435 in the side wall 434 has a shape that forms the blade shape together with the turbine first stage stationary blade 404SV, the flow of the combustion gas is more effective than the case where the blade shape is not formed. Can be deflected.
  • FIG. 9 is a partially enlarged view illustrating a communication structure between the combustor and the turbine section in the gas turbine according to the present embodiment.
  • symbol is attached
  • the combustor 503 in the gas turbine 501 of the present embodiment has a shape of an end portion (lower end portion in FIG. 9) on the turbine portion 504 side in the side wall 534 of the tail tube (tubular body) 533. Is different from the first embodiment.
  • a deflection unit 535 that deflects the combustion gas flow in the left direction of FIG. 9 is provided on the side wall 534 of the tail cylinder 533 in the combustor 503.
  • the deflection unit 535 is an end of the side wall 534 on the turbine unit 504 side and is a portion adjacent to the turbine first stage stationary blade 504SV.
  • the deflecting portion 535 has the side wall 534 deflected as it is, the dimension in the thickness direction of the deflecting portion 535 and the dimension in the thickness direction of the side wall 534 other than the deflecting portion 535 are the same.
  • the upstream end portion (upper end portion in FIG. 9) of the deflection portion 535 in the combustion gas flow is set to a position equivalent to the front edge LE of the turbine first stage stationary blade 304SV of the fourth embodiment.
  • a cooling channel 145 that extends along the direction in which the combustion gas flows (the vertical direction in FIG. 9) and through which cooling fluid such as cooling air flows. It has been.
  • the cooling flow path 145 further extends along the deflection portion 535 between the deflection portions 535 in the side wall 534.
  • An end portion of the cooling channel 145 is opened to a downstream end portion (lower end portion in FIG. 9) of the deflecting portion 535 of the side wall 534.
  • a turbine first stage stationary blade (turbine stationary blade) 504SV is provided in the turbine section 504 of the gas turbine 501 of the present embodiment.
  • the turbine first stage stationary blade 504SV constitutes a turbine stage together with the turbine first stage moving blade 4RB, and generates a rotational driving force from the combustion gas flowing into the turbine section 504 together with the turbine first stage moving blade 4RB. Furthermore, the turbine first stage stationary blades 504SV are arranged at equal intervals on the same circumference around the rotation shaft 5 and are arranged so as to extend along the radial direction (perpendicular to the paper surface of FIG. 9). The wings.
  • the turbine first stage stationary blade 504SV is disposed at a position facing the downstream end (lower end in FIG. 9) of the deflecting portion 535 in the combustion gas flow.
  • the turbine first stage stationary blade 504SV has a smaller cross-sectional area than the turbine first stage stationary blade 4SV, and is the same as the thickness direction dimension of the deflecting portion 535 where the dimension in the thickness direction of the turbine first stage stationary blade 504SV is the largest. Yes.
  • the trailing edge TE of the turbine first stage stationary blade 504SV is arranged at the same position as the trailing edge TE of the turbine first stage stationary blade 4SV in the first embodiment or the like.
  • the turbine first stage stationary blade 504SV has a cavity 41 to which cooling air is supplied, and a cooling hole 42 through which the cooling air flows from the cavity 41 to the periphery of the turbine first stage stationary blade 504SV. Not formed.
  • the cooling air 145 communicates with the cooling channel 145 of the deflecting unit 535, and the cooling air after flowing through the cooling channel 145 is supplied to the turbine.
  • An outflow passage 146 is provided to flow out around the first stage stationary blade 504SV.
  • the outflow channel 146 is a through hole extending from the cooling channel 145 toward the outside of the deflecting portion 535 in the downstream direction of the combustion gas flow (the lower left direction in FIG. 9).
  • the combustion gas flows out from the transition piece 533 of the combustor 503 and flows into the cascade of the turbine first stage stationary blade 504 SV in the turbine unit 504.
  • the combustion gas that has flowed along the inner surface of the side wall 534 in the tail cylinder 533 flows and is deflected along the inner surface of the deflecting portion 535 of the side wall 534 and the outer surface of the turbine first stage stationary blade 504SV.
  • the cooling air that has flowed through the cooling flow path 145 to cool the tail cylinder 533 and the deflecting portion 535 flows out along the outer surface of the turbine first stage stationary blade 504SV via the outflow flow path 146.
  • the cooling air flows in a film shape along the outer surface of the turbine first stage stationary blade 504SV to cool the turbine first stage stationary blade 504SV.
  • the technical scope of the present invention is not limited to the above embodiment, and various modifications can be made without departing from the spirit of the present invention.
  • the present invention is not limited to those applied to the above-described embodiments, and may be applied to embodiments obtained by appropriately combining these embodiments, and is not particularly limited.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
PCT/JP2010/058171 2009-12-07 2010-05-14 燃焼器とタービン部との連通構造、および、ガスタービン WO2011070806A1 (ja)

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KR1020137019998A KR101415478B1 (ko) 2009-12-07 2010-05-14 연소기와 터빈부의 연통 구조 및 가스 터빈
US13/500,009 US9395085B2 (en) 2009-12-07 2010-05-14 Communicating structure between adjacent combustors and turbine portion and gas turbine
CN201080044670.3A CN102686949B (zh) 2009-12-07 2010-05-14 燃烧器与涡轮部的连通结构及燃气轮机
EP10835729.4A EP2511612B1 (en) 2009-12-07 2010-05-14 Gas turbine component assembly
KR1020127008290A KR101377772B1 (ko) 2009-12-07 2010-05-14 연소기와 터빈부의 연통 구조 및 가스 터빈

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KR20130087640A (ko) 2013-08-06
KR20120058600A (ko) 2012-06-07
KR101377772B1 (ko) 2014-03-25
JP2011117700A (ja) 2011-06-16
EP2511612A1 (en) 2012-10-17
EP2511612B1 (en) 2017-11-08
JP5479058B2 (ja) 2014-04-23
KR101415478B1 (ko) 2014-07-04
CN102686949A (zh) 2012-09-19
EP2511612A4 (en) 2016-05-11
US20120247125A1 (en) 2012-10-04
CN102686949B (zh) 2015-02-04

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