WO2019097905A1 - ガスタービンの環状シール及びガスタービン - Google Patents

ガスタービンの環状シール及びガスタービン Download PDF

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Publication number
WO2019097905A1
WO2019097905A1 PCT/JP2018/037642 JP2018037642W WO2019097905A1 WO 2019097905 A1 WO2019097905 A1 WO 2019097905A1 JP 2018037642 W JP2018037642 W JP 2018037642W WO 2019097905 A1 WO2019097905 A1 WO 2019097905A1
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WO
WIPO (PCT)
Prior art keywords
groove
notch
annular seal
gas turbine
radial
Prior art date
Application number
PCT/JP2018/037642
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English (en)
French (fr)
Japanese (ja)
Inventor
剣太郎 ▲徳▼山
佐藤　賢治
健太 谷口
彰浩 村上
敬介 松山
貴也 甲田
鳥井　俊介
哲也 新名
Original Assignee
三菱日立パワーシステムズ株式会社
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Application filed by 三菱日立パワーシステムズ株式会社 filed Critical 三菱日立パワーシステムズ株式会社
Publication of WO2019097905A1 publication Critical patent/WO2019097905A1/ja

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    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • 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
    • 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
    • F02C7/28—Arrangement of seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/02—Sealings between relatively-stationary surfaces
    • F16J15/04—Sealings between relatively-stationary surfaces without packing between the surfaces, e.g. with ground surfaces, with cutting edge

Definitions

  • the present disclosure relates to an annular seal of a gas turbine and a gas turbine.
  • annular seal member may be provided at the outlet of the combustor to prevent the compressed air outside the combustor from entering the combustion gas passage formed inside the combustor and the turbine.
  • Patent Literatures 1 and 2 have annular inner surfaces respectively located radially inward and outward so as to seal circumferentially between the outlet of the combustor and the inner shroud and the outer shroud of the first stage turbine vane.
  • a gas turbine combustor outlet seal structure is disclosed that includes a circumferential seal member and an outer circumferential seal member.
  • the inner circumferential seal member is formed with a circumferential groove opening inward in the radial direction and a circumferential groove opening in the axial downstream direction.
  • the flange provided in the rear end part of a combustor tail cylinder, and the axial direction protrusion part of the inner side shroud of a 1st-stage stator blade are each fitted by these circumferential direction grooves.
  • Patent Document 2 describes a configuration in which the front edge portion (front portion) of the first stage stationary blade located on the downstream side of the outlet wall of the combustion cylinder is extended on the upstream side to form a flat surface.
  • At least one embodiment of the present invention provides an annular seal of a gas turbine capable of sealing a combustor outlet while avoiding interference with a single-stage vane, and a gas turbine including the same. With the goal.
  • An annular seal of a gas turbine A first portion extending in a circumferential direction on one end side in the axial direction and having a first groove opened to the one end side in the axial direction; A second portion extending in the circumferential direction on the other end side in the axial direction and having a second groove opening in the radial direction;
  • the first portion is one of a pair of first groove wall portions facing each other in the radial direction to form the first groove, one of the first groove walls positioned downstream in the opening direction of the second groove
  • the portion has a first notch formed along the axial direction.
  • the first portion of the annular seal has the first groove opening on one end side in the axial direction, and one of the pair of first groove wall portions forming the first groove. It has a first notch formed along the axial direction.
  • the first notch is provided from the open end on the one end side of the one first groove wall portion to the first groove bottom portion of the first groove.
  • the first notch is provided from the open end on one end side of the first groove wall portion to the first groove bottom portion of the first groove, the protrusion amount of the convex portion Even if Y is large, the interference between the annular seal and the first stage vane can be reliably avoided.
  • the first notch is A first axial notch provided in the one first groove wall and extending along the axial direction; And a first radial notch provided at the first groove bottom and extending along the radial direction.
  • the first notch includes a first axial notch provided in one of the first groove wall portions and a first radial notch provided in the first groove bottom, Therefore, even when the amount of protrusion of the convex portion is large, the interference between the annular seal and the first stage vane can be reliably avoided.
  • the axial length of the first axial notch is longer than the radial length of the first radial notch.
  • the bottom of the first notch formed in the first groove bottom portion is, in a cross section along the axial direction, the opening direction of the second groove in the radial direction toward the one end side in the axial direction It has a tapered surface directed to the upstream side.
  • the second portion is one of a pair of second groove wall portions facing each other in the axial direction to form the second groove, from one second groove wall portion positioned on the other end side in the axial direction And a second notch provided across the second groove bottom of the second groove.
  • the second portion of the annular seal has the second groove opening in the radial direction, and the second groove is formed from one of the pair of second groove wall portions forming the second groove. And a second notch provided across the bottom of the second groove.
  • a member for example, a radial direction seal described later
  • a member is inserted into the space formed between the side walls of the plurality of combustion cylinders having the flanges fitted in the second circumferential direction via the second notch. can do.
  • the second notch is A second radial notch provided in the one second groove wall and extending along the radial direction; And a second axial notch provided at the second groove bottom and extending along the axial direction.
  • the second notch includes a second radial direction notch provided in one of the second groove walls and a second axial direction notch provided in the second groove bottom, And the member can be reliably inserted through the second notch.
  • the radial length of the second radial notch is longer than the axial length of the second axial notch.
  • the space formed between the side wall portions of the plurality of combustion cylinders having the flanges fitted in the second circumferential direction is a member (for example, When inserting a radial seal (described later), the fitting length in the radial direction between the outlet flange provided on the combustion cylinder and the second groove is sufficiently secured while avoiding interference between the member and the annular seal. it can.
  • the annular seal is The plurality of arc seal sections are arranged circumferentially to form the annular seal.
  • the annular seal is formed by the plurality of arc seal sections arranged in the circumferential direction, which facilitates the assembly of the gas turbine including the annular seal.
  • the dividing line between the pair of arc seal sections adjacent to each other in the circumferential direction is A first radial line passing through the first groove bottom of the first groove along the radial direction to reach the first notch; A circumferential line having one end connected to an end of the first radial line opposite to the first notch, the circumferential line extending along the circumferential direction; A second radial line connected to the other end of the circumferential line and extending along the radial direction to the second groove bottom of the second groove; including.
  • the dividing lines between the arc seal sections are the first radial line and the second radial line, and the first radial line and the second radial line, which have different circumferential positions. Since the circumferential line having both ends to be connected is included, the axial positioning of each arc seal section is easy and the seal of the combustor outlet can be made more reliable.
  • the first radial direction line, the circumferential direction line, and the second radial direction line overlap the formation range of the first notch in the circumferential direction.
  • the first groove is located on the downstream side of the opening direction of the second groove with respect to the second groove bottom of the second groove in the radial direction.
  • the outlet flange of the combustion cylinder protrudes radially in the direction away from the gas path (combustion gas passage), so that the inner wall surface of the combustion cylinder and the wall surface of the shroud of the first stage vane are smoothly connected.
  • the first groove in which the protrusion of the shroud of the first stage vane engages with the second groove in which the outlet flange of the combustion cylinder fits.
  • the first groove is provided downstream of the second groove bottom in the opening direction of the second groove in the radial direction, so the inner wall surface of the combustion cylinder and the first stage vane It can be connected smoothly with the wall surface of the shroud.
  • the second groove is located on the other end side with respect to the first groove bottom of the first groove in the axial direction.
  • the second groove is formed at a position shifted to the other end side in the axial direction with respect to the first groove bottom of the first groove, so the combustion cylinder to the second groove Interference with the first groove bottom and the outlet flange when fitting to the outlet flange can be avoided.
  • the first groove is configured to be engageable with a protrusion provided along the circumferential direction so as to project in the axial direction from an inner shroud or an outer shroud of a first stage vane of the gas turbine.
  • the second groove is configured to be engageable with an outlet flange of a combustion cylinder of the gas turbine.
  • the first groove can be fitted with a protrusion projecting axially from the inner shroud or the outer shroud of the first stage vane of the gas turbine, and the second groove can be used for combustion of the gas turbine Because the outlet flange of the barrel is engageable, the annular seal can seal the outlet of the combustor can (combustor).
  • the first notch is configured such that a convex portion provided on a front portion of the first stage stationary blade engages.
  • the first notch is configured to engage with the convex portion provided on the front portion of the first-stage vane, the above-mentioned protrusion of the first-stage vane fits in the first groove In the mated state, the convex portion of the first stage vane is engageable with the first notch. Therefore, the outlet of the combustion cylinder (combustor) can be sealed while avoiding the interference between the annular seal and the first stage vane.
  • a gas turbine according to at least one embodiment of the present invention, A plurality of circumferentially arranged combustion cylinders each having an outlet flange; A plurality of first stage vanes provided on the downstream side of the combustion cylinder in the axial direction; The annular seal according to any one of (1) to (16), which is provided between the outlet flange of the combustion cylinder and at least one of the outer shroud and the inner shroud of the first-stage vane. Equipped with
  • the first portion of the annular seal has the first groove opened at one end side in the axial direction, and at one of the pair of first groove wall portions forming the first groove. It has a first notch formed along the axial direction.
  • the second portion of the annular seal is one of a pair of second groove wall portions facing each other in the axial direction to form the second groove, one of the second groove portions positioned on the other end side in the axial direction And a second notch provided from the groove wall to the second groove bottom of the second groove,
  • a radial seal is provided in a seal accommodating space formed along the radial direction between side wall portions of the pair of combustion cylinders adjacent in the circumferential direction so as to overlap the second notch in the radial direction.
  • the second portion of the annular seal is provided from the one of the pair of second groove wall portions forming the second groove to the second groove bottom portion of the second groove
  • a radial seal is provided in a seal receiving space having a notch and formed to overlap the second notch in the radial direction. Therefore, it is possible to seal between the combustion gas passage formed in the combustion cylinder and the turbine and the external space by the radial seal inserted into the seal accommodation space via the second notch.
  • annular seal of a gas turbine capable of sealing a combustor outlet while avoiding interference with a single-stage vane, and a gas turbine provided with the same.
  • FIG. 2 is a schematic view showing a combustor and a turbine inlet portion of a gas turbine according to an embodiment. It is a figure which shows the structure of the exit part of the combustor of the gas turbine which concerns on one Embodiment, and the inlet part of a turbine. It is a figure which shows the structure of the exit part of the combustor of the gas turbine which concerns on one Embodiment, and the inlet part of a turbine.
  • FIG. 5 is a partial external view of the annular seal shown in FIG. 4; FIG. 5 is a partial exploded perspective view of the gas turbine shown in FIG. 4; FIG. 5 is a partial exploded perspective view of the gas turbine shown in FIG.
  • FIG. 1 is a schematic configuration view of a gas turbine according to an embodiment.
  • the gas turbine 1 is rotationally driven by the compressor 2 for generating compressed air, a combustor 4 for generating combustion gas using the compressed air and fuel, and the combustion gas.
  • a turbine 6 configured as described above.
  • a generator (not shown) is connected to the turbine 6.
  • the compressor 2 includes a plurality of stationary blades 16 fixed to the compressor casing 10 and a plurality of moving blades 18 implanted in the rotor 8 so as to be alternately arranged with respect to the stationary blades 16. .
  • the air taken in from the air intake 12 is sent to the compressor 2, and this air is compressed by passing through the plurality of stationary blades 16 and the plurality of moving blades 18. Become compressed air.
  • a fuel and compressed air generated by the compressor 2 are supplied to the combustor 4, and the fuel is burned in the combustor 4 to generate a combustion gas which is a working fluid of the turbine 6. Be done.
  • the gas turbine 1 has a plurality of combustors 4 arranged in a circumferential direction around a rotor 8 in a casing 20.
  • the turbine 6 has a combustion gas passage 28 formed by a turbine casing 22 and includes a plurality of vanes 24 and blades 26 provided in the combustion gas passage 28.
  • the stator vanes 24 are fixed to the turbine casing 22 side, and a plurality of stator vanes 24 arranged along the circumferential direction of the rotor 8 constitute a stator vane row.
  • the moving blades 26 are implanted in the rotor 8, and a plurality of moving blades 26 arranged along the circumferential direction of the rotor 8 constitute a moving blade row.
  • the stationary blade row and the moving blade row are alternately arranged in the axial direction of the rotor 8.
  • the stator blade 24 provided on the most upstream side (that is, the stator blade 24 provided at a position close to the combustor 4) is the first stage stator blade 23.
  • the combustion gas from the combustor 4 that has flowed into the combustion gas passage 28 passes through the plurality of stationary blades 24 and the plurality of moving blades 26 to rotationally drive the rotor 8, thereby being connected to the rotor 8.
  • the generator is driven to generate power.
  • the combustion gas after driving the turbine 6 is exhausted to the outside through the exhaust chamber 30.
  • FIG. 2 is a schematic view showing an inlet portion of the combustor 4 and the turbine 6 of the gas turbine 1 according to one embodiment.
  • each of the plurality of combustors 4 (refer to FIG. 1) annularly arranged around the rotor 8 is provided in a combustor casing 32 defined by the casing 20 (combustors And a plurality of second combustion burners 40 disposed to surround the first combustion burners 38 and the first combustion burners 38 disposed in the combustion cylinder 36, respectively. That is, in the gas turbine 1, a plurality of combustion cylinders 36 of the combustor 4 are arranged in the circumferential direction.
  • the combustor 4 may include other components such as a bypass pipe (not shown) for bypassing the combustion gas.
  • the combustion liner (combustor liner) 36 includes an inner cylinder 48 disposed around the first combustion burner 38 and the plurality of second combustion burners 40, and a transition piece 50 connected to the tip of the inner cylinder 48. Have.
  • the inner cylinder 48 and the transition piece 50 may constitute an integral combustion cylinder.
  • Each of the first combustion burner 38 and the second combustion burner 40 includes a fuel nozzle (not shown) for injecting a fuel and a burner cylinder (not shown) disposed so as to surround the fuel nozzle.
  • Each fuel nozzle is supplied with fuel via fuel ports 42 and 44, respectively.
  • compressed air generated by the compressor 2 see FIG.
  • the first combustion burner 38 may be a burner for generating a diffusion combustion flame
  • the second combustion burner 40 may be a burner for burning a premixed gas to generate a premixed combustion flame.
  • the fuel from the fuel port 44 and the compressed air are premixed, and the premixed air mainly forms a swirling flow by the swirler (not shown) and flows into the combustion cylinder 36.
  • the compressed air and the fuel injected from the first combustion burner 38 through the fuel port 42 are mixed in the combustion cylinder 36, ignited and burned by a not-shown seed fire, and a combustion gas is generated.
  • the combustion region may be formed, for example, in the inner cylinder 48 and not formed in the transition piece 50.
  • the combustion gas generated by the combustion of the fuel in the combustor 4 flows into the first stage vane 23 of the turbine 6 through the outlet 52 of the combustor 4 located at the downstream end of the transition piece 50.
  • FIGS. 3 and 4 are diagrams showing the configurations of the outlet 52 of the combustor 4 and the inlet of the turbine 6, respectively, according to one embodiment.
  • FIG. 3 is a cross-sectional view along the circumferential direction
  • FIG. 4 is a cross-sectional view along the radial direction.
  • a plurality of single-stage vanes are provided on the downstream side of the transition piece 50 (combustion cylinder) forming the outlet 52 of the combustor 4, a plurality of first-stage stationary blades 23 are provided.
  • each of the plurality of combustors 4 has an outlet 52 positioned at the downstream end of the transition piece 50 (combustion cylinder), and the outlet 52 of each combustor 4 It has side wall portions 54, 54 'extending along the radial direction (vertical direction in FIG. 3).
  • the sidewall portion 54 of one combustor 4 and the sidewall portion 54 ′ of the other combustor 4 are a pair of sidewall portions 54 facing each other. , 54 '(see FIG. 3).
  • the plurality of first-stage stationary blades 23 of the turbine 6 are circumferentially arranged at the downstream axial position of the pair of side wall portions 54, 54 ′.
  • the plurality of first stage vanes 23 include one stage vanes 23A provided on the downstream side of the pair of side wall portions 54, 54 'along the axial direction.
  • one-stage stator vanes 23A are provided on the downstream side of each of the pair of side wall portions 54, 54 ′ facing each other in the circumferential direction. Multiple are arranged in the direction.
  • the plurality of first-stage vanes 23 further include another one-stage vane 23B provided at a circumferential position between a pair of circumferentially adjacent one-stage vanes 23A and 23A. That is, in the embodiment shown in FIG. 3, the first-stage vanes 23A and the first-stage vanes 23B constituting the plurality of first-stage vanes 23 arranged along the circumferential direction are alternately disposed in the circumferential direction.
  • the plurality of one-stage vanes arranged along the circumferential direction may include only a plurality of one-stage vanes 23A provided on the downstream side of the pair of side wall portions 54, 54 '. .
  • the first stage vanes 23 ⁇ / b> A have an airfoil shape that extends radially between the inner shroud 60, the outer shroud 62 provided radially outward of the inner shroud 60, and the inner shroud 60 and the outer shroud 62. And 70.
  • the outer shroud 62 is supported by the turbine casing 22 (see FIG. 1), and the first stage vanes 23 are supported by the turbine casing 22 via the outer shroud 62.
  • the first stage stationary blade 23A includes a rear portion 66 including a trailing edge 65 and a front portion 64 located axially upstream of the rear portion 66.
  • the front portion 64 of the first stage stationary blade 23A has a special shape, and specifically, the front portion 64 of the first stage stationary blade 23A has a convex portion 68 having a shape projecting in the axial direction.
  • a convex portion receiving space 71 is formed at the downstream end of the pair of side wall portions 54, 54 ', and the convex portion 68 of the first stage stationary blade 23A is a convex portion receiving space. 71 is fitted.
  • the convex portion receiving space 71 extends radially at a position facing the other side wall portion at the downstream end 55 of the pair of side wall portions 54, 54 '.
  • the grooves 72, 72 are formed.
  • the convex portion receiving space 71 in which the convex portion 68 of the first stage stationary blade 23A is fitted may be formed in any one of the pair of side wall portions 54 and 54 '. .
  • annular seal 74 is provided between the outlet 52 of the combustor 4 and the first stage vane 23A.
  • the compressed air in the combustor casing 32 is formed in the combustor 4 and the turbine 6 (i.e., the combustion gas passage 28 formed in the internal space of the combustion cylinder 36 and the turbine 6). (See Figure 1))).
  • FIG. 5 is a partial external view of the annular seal 74 shown in FIG. 4 and is a view of the annular seal 74 constituting the gas turbine 1 viewed from the upstream side toward the downstream side in the axial direction.
  • the display of components of the gas turbine 1 other than the annular seal 74 is omitted.
  • the gas turbine 1 is provided with a circumferentially extending annular seal 74.
  • the gas turbine 1 is configured as the annular seal 74 by the inner annular seal 76 positioned inward in the circumferential direction and the outer side positioned circumferentially outward relative to the inner annular seal 76.
  • an annular seal 78 an annular seal 78.
  • the inner annular seal 76 and the outer annular seal 78 may be collectively referred to as an annular seal 74.
  • the annular seal 74 may be formed by a plurality of circumferentially arranged arcuate seal sections.
  • the inner annular seal 76 and the outer annular seal 78 shown in FIG. 5 are each formed by a plurality of arc seal sections 76a, 78a arranged circumferentially.
  • FIG. 6 is a view for explaining the engagement between the annular seal 74 and the first stage stationary blade 23A
  • FIG. 7 is a view for explaining the engagement between the annular seal 74 and the transition piece 50.
  • 6 and 7 show the outer annular seal 78 as an example of the annular seal 74, the following description of the outer annular seal 78 using FIGS. 6 and 7 is the inner annular seal 76. Is also applicable. 6 and 7, for convenience of explanation, a part of the annular seal 74 is cut out, and the cross section is shown by the hatched part in the drawings.
  • the inner annular seal 76 includes an inner outlet flange 80 (outlet flange) provided at the outlet of the transition piece 50 (combustion cylinder 36) (ie, the outlet 52 of the combustor 4) It is provided between the inner shroud 60 of 23A. Further, the outer annular seal 78 is provided between the outer outlet flange 82 (outlet flange) provided at the outlet of the transition piece 50 (combustion cylinder 36) and the outer shroud 62 of the first stage vane 23A (see FIG. See also 7).
  • the transition piece 50 has an inner side wall 51 and an outer side wall 53 that form radially inner and outer walls.
  • the inner outlet flange 80 (outlet flange) is formed to project radially inward from the inner side wall 51 at the outlet of the transition piece 50.
  • the outer outlet flange 82 (outlet flange) is formed so as to project radially outward from the outer wall portion 53 at the outlet portion of the transition piece 50. That is, the outlet flange is formed so as to protrude in the radial direction away from the internal space of the combustion cylinder 36 and the combustion gas passage formed inside the turbine 6.
  • the transition pieces 50 of the plurality of combustors 4 are arranged along the circumferential direction, the inner outlet flange 80 and the outer outlet flange 82 of the transition piece 50 are also aligned along the circumferential direction. .
  • the inner shroud 60 and the outer shroud 62 (see also FIG. 6) of the first stage vane 23 A project respectively in the axial direction toward the upstream side (that is, toward the combustor 4)
  • the projecting portions 61 and 63 are provided along the circumferential direction so that The protrusions 61 and 63 may be located opposite to the gas path (combustion gas passage) with respect to the inner shroud 60 and the outer shroud 62, respectively. That is, the protrusion 61 may be located radially inward of the connection between the inner shroud 60 and the airfoil 70.
  • the projecting portion 63 may be located radially outward of the connection portion between the outer shroud 62 and the airfoil portion 70.
  • the annular seal 74 (the inner annular seal 76 and the outer annular seal 78) has a first portion in which the first groove 86 is formed on the downstream side (one end side) in the axial direction. And a second portion 88 in which a second groove 90 is formed on the upstream side (the other end side) in the axial direction.
  • the first groove 86 of the first portion 84 includes a pair of first groove wall portions 92A and 92B opposed to each other in the radial direction and a pair of first groove wall portions 92A and 92B.
  • a first groove bottom portion 94 is provided to connect the first groove wall portions 92A and 92B therebetween.
  • the pair of first groove wall portions 92A and 92B one of the pair of first groove wall portions 92A and 92B located on the downstream side in the opening direction (radially inner side or outer side) of the second groove 90 described below is the first groove wall portion 92A.
  • One of the first groove wall portions 92 ⁇ / b> B is located on the upstream side in the opening direction of the second groove 90.
  • the first groove 86 extends in the circumferential direction and is open toward the downstream side (one end side), and the protrusions 61 and 63 of the first stage stationary blade 23A are engaged with each other. That is, in the illustrated embodiment, the opening direction of the first groove 86 is the downstream side in the axial direction.
  • the second groove 90 of the second portion 88 includes a pair of second groove wall portions 96A and 96B opposed to each other in the axial direction and a pair of second groove wall portions 96A, A second groove bottom 98 is provided to connect the second groove walls 96A and 96B between 96B.
  • the pair of second groove wall portions 96A and 96B one of the pair of second groove wall portions 96A and 96B located on one end side (that is, the downstream side in the axial direction) in the axial direction is the second groove wall portion 96B.
  • the second groove wall portion 96A is located on the upstream side in the axial direction).
  • the second groove 90 extends in the circumferential direction and opens in the radial direction, and the outlet flanges 80 and 82 provided at the outlet of the tail cylinder 50 are fitted.
  • the second groove 90 of the inner annular seal 76 is opened radially outward, and the inner outlet flange 80 provided so as to project radially inward at the outlet portion of the tail cylinder 50 is fitted It is united.
  • the second groove 90 of the outer annular seal 78 is opened radially inward, and the outer outlet flange 82 provided so as to project radially outward at the outlet portion of the tail cylinder 50 is fitted It is united. That is, in the illustrated embodiment, the opening direction of the second groove 90 of the inner annular seal 76 is radially outward, and the opening direction of the second groove 90 of the outer annular seal 78 is radially inner.
  • the second groove wall portion 96 ⁇ / b> B at one end side forming the second groove and the first groove bottom portion 94 have one direction ( In the illustrated example, it may be a continuous member extending continuously in the radial direction.
  • the first portion 84 of the annular seal 74 is a first groove wall located downstream of the pair of first groove wall portions 92A and 92B in the opening direction of the second groove 90.
  • the portion 92A has a first notch 102 formed along the axial direction.
  • the convex part 68 provided in the front part 64 of 1st-stage stationary blade 23A engages with the 1st notch 102. As shown in FIG.
  • the first portion 84 of the annular seal 74 has the first groove 86 opened on one end side (downstream side) in the axial direction, and in the first groove wall portion 92A in the axial direction It has a first notch 102 formed along it.
  • the first notch 102 is the first groove bottom of the first groove 86 from the open end of the one end side (ie, the downstream side) of the first groove wall 92A. It may be provided across 94.
  • the first notch 102 is provided in the first groove wall 92A and extends in the axial direction with a first axial notch 102a; And a first radial notch 102b provided in the groove bottom 94 and extending in the radial direction.
  • the first notch 102 is provided from the open end of the first groove wall 92A to the first groove bottom 94 of the first groove 86 from the open end on the one end side (that is, the downstream side) of the first groove wall 92A. Even in the case where the amount of protrusion of the convex portion 68 in the axial direction of the 23A is large, the interference between the annular seal 74 and the first stage stationary blade 23A can be reliably avoided.
  • the length L 1a in the axial direction of the first axial notch 102a of the above (see FIG. 6), the length L 1b in a radial direction of the first radial notch 102b above (FIG. 6) longer than.
  • the axial direction of the first groove 86 and the projections 61, 63 provided on the shroud (the inner shroud 60 or the outer shroud 62) of the first stage vane 23A can be sufficiently secured.
  • the bottom of the first notch 102 formed in the first groove bottom 94 extends in the axial direction.
  • the taper toward the opening side of the opening direction of the second groove 90 in the radial direction toward the one end side in the axial direction that is, the downstream side in the axial direction. It may have a face 104.
  • the bottom of the first notch 102 formed in the first groove bottom 94 (the first radial direction notch 102b) has the above-described tapered surface 104, so that the convex portion 68 of the first stage vane 23A and the annular seal It is easy to avoid interference with 74.
  • the protrusion 68 of the first stage vane 23A is welded to the airfoil 70, the inner shroud 60 and the outer shroud 62 by welding, for example, the upper surface of the protrusion 68 A weld 69 is formed between the lower end of the outer shroud 62 and the axial end face of the protrusion 63 of the outer shroud 62.
  • the weld 69 is accommodated in the space formed by the tapered surface 104, and interference between the weld 69 and the annular seal 74 is obtained. It can be avoided.
  • a fillet portion may be formed between the upper surface of the convex portion 68 and the axial end surface of the projecting portion 63 of the outer shroud 62.
  • the above-mentioned fillet portion is accommodated in the space formed by the tapered surface 104, and the fillet portion and the annular seal 74 Interference can be avoided.
  • the second portion 88 of the annular seal 74 is the other end in the axial direction of the pair of second groove wall portions 96A, 96B (ie, the upstream side). And a second notch 106 provided from the one second groove wall 96A located on the side) to the second groove bottom 98 of the second groove 90.
  • FIG. 7 it extends along the radial direction between the sidewall portions 54, 54 '(see FIG. 3) of the combustion cylinders 36 of the pair of combustors 4, 4 adjacent in the circumferential direction.
  • a seal accommodating space 117 is formed.
  • the seal accommodation space 117 is formed to overlap the second notch 106 of the annular seal 74 in the radial direction.
  • a radially extending radial seal 120 is inserted into the seal accommodating space 117.
  • the radial seal 120 has a pair of plate members 121A and 121B opposed in the axial direction, and a spring (not shown) provided between the plate members 121A and 121B for biasing in the axial direction. It may be done. Then, in a state where the radial direction seal 120 is inserted into the seal accommodation space 117, the plate members 121A and 121B are axially urged by the spring to make surface contact with the wall surface of the seal accommodation space 117. And a combustion gas passage formed in the turbine 6 and an external space (e.g., the combustor casing 32) may be sealed.
  • the second portion 88 of the annular seal 74 extends from the second groove wall portion 96A forming the second groove 90 to the second notch 106 provided from the second groove bottom portion 98 of the second groove 90.
  • the space for example, the seal accommodation space 117 described above
  • the second notch 106 is formed in the space (for example, the seal accommodation space 117 described above) formed between the side walls 54, 54 'of the plurality of combustion cylinders 36 having the outlet flanges fitted in the second groove 90.
  • the second notch 106 is formed in the space (for example, the seal accommodation space 117 described above) formed between the side walls 54, 54 'of the plurality of combustion cylinders 36 having the outlet flanges fitted in the second groove 90.
  • the notch 106 is formed in the space (for example, the seal accommodation space 117 described above) formed between the side walls 54, 54 'of the plurality of combustion cylinders 36 having the outlet flanges fitted in the second groove 90.
  • the notch 106 is formed
  • the second notch 106 is provided in the second groove wall 96A and extends in the radial direction with a second radial notch 106a and a second groove bottom 98 and may include a second axial notch 106b extending along the axial direction.
  • the second notch 106 includes the second radial notch 106a provided in the second groove wall 96A and the second axial notch 106b provided in the second groove bottom 98, A member (e.g., the radial seal 120 described above) can be reliably inserted through the second notch 106.
  • the length L 2a in the radial direction of the second radial notch 106a of the above is, (see FIG. 7) L 2b than the length in the axial direction of the second axial notch 106b may be longer.
  • the space (for example, the above-mentioned seal accommodation space 117) formed between the side walls 54, 54 'of the plurality of transition members 50 (combustion cylinder 36) having the outlet flanges fitted in the second groove 90 2)
  • a member for example, the radial direction seal 120 described later
  • the outlet flanges 80 and 82 provided on the combustion cylinder 36 while avoiding the interference between the member and the annular seal 74
  • the fitting length in the radial direction with the second groove 90 can be sufficiently secured.
  • the first notch 102 is an end opposite to the open end of the first groove wall 92A (ie, the downstream side) (ie, the first groove 102).
  • the groove bottom portion 94) has a rectangular shape (see FIG. 12A), but the shape of the opposite end of the first notch 102 is not limited to a rectangular shape.
  • FIGS. 12A to 12D are schematic views showing the first notch 102 according to one embodiment, respectively.
  • the shape of the opposite end of the first notch 102 has, for example, a shape including a curve such as a U-shape (see FIGS. 12B and 12C) or an acute angle such as a V-shape. It may have a shape including two sides (see FIG. 12D).
  • the first notch 102 is provided across the first groove bottom 94, the end opposite to the open end of the first notch 102 is formed in the first groove bottom 94 as illustrated.
  • the opposite end described above may be formed in the first groove wall 92A.
  • the shape of the second notch 106 is not limited to the rectangular shape (see FIG. 12A).
  • a shape including a curve such as a U shape (see FIGS. 12B and 12C) or a V shape It may have a shape including two sides forming an acute angle (see FIG. 12D).
  • the first groove 86 of the annular seal 74 is radially downstream of the opening direction of the second groove 90 with respect to the second groove bottom 98 of the second groove 90 (the outer annular seal 78 If located radially inward).
  • the positional relationship of the first groove 86 in which the projecting portions 61 and 63 of the shrouds 60 and 62 of the first stage vane 23A are engaged with the second groove 90 in which the outlet flanges 80 and 82 of the combustion cylinder 36 are engaged is It can be desirable from the viewpoint of connecting smoothly the inner wall surface of the cylinder 50 (combustion cylinder 36) and the wall surface of the shroud of the first stage stationary blade 23A.
  • the inner wall surface of the tail cylinder 50 (combustion cylinder 36) and the shroud of the first stage vane 23A It can be connected smoothly to the 60, 62 wall surfaces.
  • the second groove 90 is located on the other end side (that is, upstream in the axial direction) with respect to the first groove bottom 94 of the first groove 86 in the axial direction.
  • the combustion cylinder 36 to the second groove 90 is formed. Interference with the first groove bottom 94 and the outlet flanges 80, 82 at the time of fitting to the outlet flanges 80, 82 of the second embodiment.
  • the annular seal 74 may be formed by a plurality of circumferentially arranged arc seal sections (see FIG. 5).
  • FIGS. 8 to 11 are a perspective view of an end portion of the arc seal section shown in FIG. 5 in the circumferential direction.
  • FIG. 8 is a perspective view of one end 79a of the arc seal section 78a forming the outer annular seal 78 as viewed from the direction A.
  • FIG. 9 is the other end of the same arc seal section 78a (the one end 79a Is a perspective view of the opposite end portion 79b as viewed from the B direction.
  • FIG. 10 is a perspective view of one end 77a of the arc seal section 76a forming the inner annular seal 76 as viewed from the C direction
  • FIG. 11 is the other end (one end of the same arc seal section 76a). It is a perspective view at the time of seeing the end 77b opposite to 77a from the D direction.
  • the hatched portions in FIGS. 8 to 11 do not indicate cross sections, and in FIGS. 8 and 9 and FIGS. 10 and 11, it is shown that the same kind of hatched portions face each other. It is a thing.
  • a dividing line 110 is formed between a pair of arc seal sections 76a, 76a and 78a, 78a adjacent to each other in the circumferential direction, and each dividing line 110 is a first radial line 112. , A circumferential line 114 and a second radial line 116.
  • the first radial line 112 has an end face 120a, 124a of the first portion 84 at one end 79a, 77a of the arc seal section 76a, 78a, and an arc adjacent to the arc seal section. It is respectively formed by the end faces 120b and 124b of the first portion 84 at the other ends 79b and 77b of the seal sections 76a and 78a.
  • the end faces 120a and 124a and the end faces 120b and 124b are arranged to face each other in the circumferential direction.
  • the second radial line 116 is adjacent to the end faces 118a, 122a of the second portion 88 at the one end 79a, 77a of the arc seal sections 76a, 78a and the arc seal section.
  • the end faces 118b and 122b of the second portion 88 at the other ends 79b and 77b of the arc seal sections 76a and 78a, respectively.
  • the end faces 118a and 122a and the end faces 118b and 122b are arranged to face each other in the circumferential direction.
  • the circumferential line 114 connects the end face 118a, 122a and the end face 120a, 124a at the one end 79a, 77a of the arc seal section 76a, 78a
  • the end faces 118b and 122b are connected to the end faces 120b and 124b at the surfaces 119a and 123a respectively extending in the circumferential direction and the other ends 79b and 77b of the arc seal sections 76a and 78a adjacent to the arc seal section.
  • they are formed by the surfaces 119 b and 123 b extending in the circumferential direction, respectively.
  • the surfaces 119a and 123a and the surfaces 119b and 123b are arranged to face each other in the radial direction.
  • the first radial line 112 is formed to pass through the first groove bottom 94 of the first groove 86 in the radial direction and to reach the first notch 102.
  • the circumferential line 114 also has one end 126 connected to the end of the first radial line 112 opposite to the first notch 102 and extends along the circumferential direction.
  • the second radial line 116 is connected to the other end 128 of the circumferential line 114 and extends in the radial direction to the second groove bottom 98 of the second groove 90.
  • the dividing line 110 between the arc seal sections is connected to the first radial line 112 and the second radial line 116, which are different in circumferential position, and to the first radial line 112 and the second radial line 116.
  • a circumferential line 114 having opposite ends (one end 126 and the other end 128) to facilitate positioning of the arc seal sections 76a and 78a in the axial direction and sealing at the outlet 52 of the combustor 4 Can be assured.
  • the above-described parting line 110 overlaps the formation area of the first notch 102 in the circumferential direction.
  • the first radial line 112, the circumferential line 114 and the second radial line 116 form the range R 1 in which the first notch 102 is formed in the circumferential direction (see FIG. 5). It overlaps with).
  • a representation representing a relative or absolute arrangement such as “in a direction”, “along a direction”, “parallel”, “orthogonal”, “center”, “concentric” or “coaxial”
  • a representation representing a relative or absolute arrangement such as “in a direction”, “along a direction”, “parallel”, “orthogonal”, “center”, “concentric” or “coaxial”
  • expressions that indicate that things such as “identical”, “equal” and “homogeneous” are equal states not only represent strictly equal states, but also have tolerances or differences with which the same function can be obtained. It also represents the existing state.
  • expressions representing shapes such as a square shape and a cylindrical shape not only indicate shapes such as a square shape and a cylindrical shape in a geometrically strict sense, but also within the range where the same effect can be obtained. Also, the shape including the uneven portion, the chamfered portion, and the like shall be indicated. Moreover, in the present specification, the expressions “comprising”, “including” or “having” one component are not exclusive expressions excluding the presence of other components.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
PCT/JP2018/037642 2017-11-14 2018-10-10 ガスタービンの環状シール及びガスタービン WO2019097905A1 (ja)

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JP7154984B2 (ja) * 2018-12-11 2022-10-18 三菱重工業株式会社 タービン静翼及びガスタービン
JP7348784B2 (ja) * 2019-09-13 2023-09-21 三菱重工業株式会社 出口シール、出口シールセット、及びガスタービン
CN118815551B (zh) * 2024-09-18 2024-12-03 中国航发四川燃气涡轮研究院 一种轴向大尺寸涡轮静子叶片连接结构及其设计方法

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JP2000257862A (ja) * 1999-03-08 2000-09-22 Mitsubishi Heavy Ind Ltd 燃焼器の尾筒シール構造及びその構造を用いたガスタービン
JP2005030680A (ja) * 2003-07-14 2005-02-03 Mitsubishi Heavy Ind Ltd ガスタービン尾筒の冷却構造
JP2008031870A (ja) * 2006-07-26 2008-02-14 Mitsubishi Heavy Ind Ltd ガスタービンのシール構造
JP2016070081A (ja) * 2014-09-26 2016-05-09 三菱日立パワーシステムズ株式会社 シール構造
WO2017043415A1 (ja) * 2015-09-08 2017-03-16 三菱日立パワーシステムズ株式会社 シール部材の組付構造及び組付方法、シール部材、ガスタービン

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JP2001289003A (ja) * 2000-04-04 2001-10-19 Mitsubishi Heavy Ind Ltd ガスタービンの冷却構造
EP3124749B1 (en) * 2015-07-28 2018-12-19 Ansaldo Energia Switzerland AG First stage turbine vane arrangement

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Publication number Priority date Publication date Assignee Title
JP2000257862A (ja) * 1999-03-08 2000-09-22 Mitsubishi Heavy Ind Ltd 燃焼器の尾筒シール構造及びその構造を用いたガスタービン
JP2005030680A (ja) * 2003-07-14 2005-02-03 Mitsubishi Heavy Ind Ltd ガスタービン尾筒の冷却構造
JP2008031870A (ja) * 2006-07-26 2008-02-14 Mitsubishi Heavy Ind Ltd ガスタービンのシール構造
JP2016070081A (ja) * 2014-09-26 2016-05-09 三菱日立パワーシステムズ株式会社 シール構造
WO2017043415A1 (ja) * 2015-09-08 2017-03-16 三菱日立パワーシステムズ株式会社 シール部材の組付構造及び組付方法、シール部材、ガスタービン

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