EP3596315B1 - Deckbanddichtungsvorrichtung - Google Patents

Deckbanddichtungsvorrichtung Download PDF

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Publication number
EP3596315B1
EP3596315B1 EP18714568.5A EP18714568A EP3596315B1 EP 3596315 B1 EP3596315 B1 EP 3596315B1 EP 18714568 A EP18714568 A EP 18714568A EP 3596315 B1 EP3596315 B1 EP 3596315B1
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EP
European Patent Office
Prior art keywords
ring
radial
turbine
sector
annular
Prior art date
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Application number
EP18714568.5A
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English (en)
French (fr)
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EP3596315A1 (de
Inventor
Nicolas Paul Tableau
Sébastien Serge Francis Congratel
Clément Jean Pierre Duffau
Fabrice Marcel Noël GARIN
Lucien Henri Jacques Quennehen
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication date
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Publication of EP3596315A1 publication Critical patent/EP3596315A1/de
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Classifications

    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]

Definitions

  • the invention relates to a turbine ring assembly comprising a plurality of ring sectors of ceramic matrix composite material as well as a ring support structure.
  • the field of application of the invention is in particular that of gas turbine aeronautical engines.
  • the invention is however applicable to other turbomachines, for example industrial turbines.
  • CMC materials have good mechanical properties making them suitable for constituting structural elements and advantageously retain these properties at high temperatures.
  • the use of CMC materials has advantageously made it possible to reduce the cooling flow to be imposed during operation and therefore to increase the performance of the turbomachines.
  • the use of CMC materials advantageously makes it possible to reduce the mass of the turbomachines and to reduce the hot expansion effect encountered with the metal parts.
  • the invention aims to provide a turbine ring assembly making it possible to maintain each ring sector in a deterministic manner, that is to say so as to control its position and prevent it from vibrating. , on the one hand, while allowing the ring sector, and by extension to the ring, to deform under the effects of temperature rises and pressure variations, and this in particular independently of the metallic parts at the interface, and , on the other hand, while improving the seal between the non-vein sector and the vein sector and by simplifying the manipulations and reducing their number for mounting the ring assembly.
  • An object of the invention provides a turbine ring assembly comprising a plurality of ring sectors forming a turbine ring and a ring support structure, each ring sector having, according to a section plane defined by an axial direction and a radial direction of the turbine ring, an annular base portion with, in the radial direction of the turbine ring, an inner face defining the inner face of the turbine ring and an outer face to from which project a first and a second hooking lug, the ring support structure comprising a central ferrule from which project a first and a second radial flange between which are held the first and second hooking tabs of each ring sector.
  • the turbine ring assembly comprises an annular flange in one piece removably attached to the central ferrule, the annular flange having a first free end, a second end coupled to the central ferrule, a first portion extending from the first end, a second portion extending between the first portion and the second end, the first portion of the flange comprising a first and a second distinct lugs, the first lug resting against the first hooking lug and the second lug being distant from the first lug in the axial direction, the second lug being in upstream of the first tab with respect to the direction of an air flow intended to pass through the turbine ring assembly, and the second portion of the annular flange comprising a bearing shell extending downstream projecting in the axial direction, the bearing shell having a radial bearing in contact with the central shell of the ring support structure.
  • the ring sectors can be made of a ceramic matrix composite (CMC).
  • CMC ceramic matrix composite
  • the presence on the first portion of the annular flange of a second lug disposed upstream and separated from a first lug in contact with an upstream lug of the ring makes it possible to provide the turbine ring assembly an upstream tab of the annular flange dedicated to absorbing the force of the high pressure distributor (DHP).
  • the second leg upstream of the first leg of the turbine ring and free from any contact with the ring is configured to pass the maximum axial force induced by the DHP directly into the ring support structure without passing by the ring which presents, when it is in CMC, a low mechanical admissible.
  • the downstream bearing ring provides greater resistance to tilting induced by the DHP force.
  • the support ring takes up the significant tangential stresses caused by the DHP force on the upstream lug and thereby limits the tilting of the annular flange.
  • the radial bearing of the bearing ring makes it possible to limit the tilting of the annular flange when the DHP force passes through the flange.
  • annular flange allows axial access to the cavity of the turbine ring. This makes it possible to assemble the ring sectors together on the outside of the ring support structure and then to slide the assembly thus assembled axially into the cavity of the ring support structure until it comes into contact with it. bearing against the second radial flange, before fixing the annular flange on the central ferrule of the ring support structure.
  • the solution defined above for the ring assembly thus makes it possible to maintain each ring sector in a deterministic manner, that is to say to control its position and to prevent it from vibrating, while by improving the seal between the non-vein sector and the vein sector, by simplifying the manipulations and reducing their number for mounting the ring assembly, and by allowing the ring to deform under the effect of temperature and pressure, in particular independently of the metal parts at the interface.
  • the first annular radial flange forms a first protruding rib in the radial direction of the turbine ring towards the interior of the ring
  • the second end of the annular flange comprises an axial stop extending in the radial direction of the turbine ring towards the outside of the ring, the axial stop being disposed upstream of said first annular radial flange and coming to bear in the axial direction of the turbine ring against said first annular radial flange.
  • the axial stop makes it possible to press the annular flange against the first annular radial flange and thus to position the first tab of the annular flange axially with respect to the radial hooking lug upstream of the ring.
  • the central ferrule of the ring support structure may further include a second rib projecting in the radial direction of the turbine ring inwardly. 'ring and having a bearing surface on which the radial bearing of the bearing shell rests, the second rib being disposed between the first and the second radial flanges of the ring supporting structure.
  • the second rib is a radial fulcrum that allows the ring support structure to retain the rocker of the second leg of the ring flange when DHP stress is applied.
  • the large distance between the axial stop and the radial support of the support ring makes it possible to increase the lever arm and thus induce a less significant radial force on the housing at the level of the contact of the radial support with the second rib of the ring support structure.
  • the annular flange is fixed by means of two radial hoops, a first hoop between the radial support and the second rib, and a second hoop between the surface of the axial stop extending in a plane comprising the axial direction and the central ferrule.
  • the ring sector may have a section in the Greek letter pi ( ⁇ ) inverted according to the section plane defined by the axial direction and the radial direction, and the assembly may comprise, for each ring sector, at least three pins for radially holding the ring sector in position, the first and second hooking tabs of each ring sector each comprising a first end integral with the external face of the annular base, a second free end, at least three lugs for receiving said at least three pins, at least two lugs projecting from the second end of one of the first or second hooking lugs in the radial direction of the turbine ring and at least one lug s' projecting from the second end of the other hooking lug in the radial direction of the turbine ring, each receiving lug comprising an orifice for receiving one of the pins.
  • the ring sector may have a section having an elongated K-shape along the section plane defined by the axial direction and the radial direction, the first and a second legs. hook having an S-shape.
  • the ring sector may have, over at least one radial range of the ring sector, an O-shaped section according to the section plane defined by the axial direction and the radial direction, the first and second attachment tabs each having a first end integral with the outer face and a second free end, and each ring sector comprising a third and a fourth attachment tabs each extending, in the axial direction of the turbine ring, between a second end of the first attachment lug and a second end of the second attachment lug, each ring sector being fixed to the ring support structure by a fixing screw comprising a screw head bearing against the ring support structure and a thread cooperating with an internal thread formed in a fixing plate, the fixing plate cooperating with the third and fourth brackets hooking up.
  • Another object of the invention provides a turbomachine comprising a turbine ring assembly as defined above.
  • the figure 1 shows a high pressure turbine ring assembly comprising a turbine ring 1 of ceramic matrix composite (CMC) material and a ring support metal structure 3.
  • the turbine ring 1 surrounds a set of rotating blades (not shown).
  • the turbine ring 1 is formed from a plurality of ring sectors 10, the figure 1 being a view in radial section.
  • the arrow D A indicates the axial direction of the turbine ring 1 while the arrow D R indicates the radial direction of the turbine ring 1.
  • the figure 1 is a partial view of the turbine ring 1 which is actually a complete ring.
  • each ring sector 10 has, along a plane defined by the axial D A and radial D R directions , a section substantially shaped like the inverted Greek letter ⁇ .
  • the section in fact comprises an annular base 12 and upstream and downstream radial hooking tabs, respectively 14 and 16.
  • upstream and downstream are used here with reference to the direction of flow of the gas flow in the turbine. represented by the arrow F on the figure 1 .
  • the legs of the ring sector 10 could have another shape, the section of the ring sector having a shape other than ⁇ , such as for example a K or O shape.
  • the annular base 12 comprises, in the radial direction D R of the ring 1, an internal face 12a and an external face 12b opposite to each other.
  • the internal face 12a of the annular base 12 is coated with a layer 13 of abradable material forming a thermal and environmental barrier and defines a gas stream flow stream in the turbine.
  • the terms “internal” and “external” are used here with reference to the radial direction D R in the turbine.
  • the upstream and downstream radial hooking tabs 14 and 16 extend projecting, in the direction D R , from the outer face 12b of the annular base 12 at a distance from the upstream and downstream ends 121 and 122 of the annular base 12.
  • the upstream and downstream radial hooking tabs 14 and 16 extend over the entire width of the ring sector 10, that is to say over the entire arc of a circle described by the ring sector 10. , or over the entire circumferential length of ring sector 10.
  • the ring support structure 3 which is integral with a turbine housing comprises a central ferrule 31, extending in the axial direction D A , and having an axis of revolution coincident with the axis of revolution of the turbine ring 1 when they are fixed together, as well as a first annular radial flange 32 and a second annular radial flange 36, the first annular radial flange 32 being positioned upstream of the second annular radial flange 36 which is therefore located in downstream of the first annular radial flange 32.
  • the second annular radial flange 36 extends in the circumferential direction of the ring 1 and, in the radial direction D R , from the central ferrule 31 towards the center of the ring 1. It comprises a first free end 361 and a second end 362 integral with the central ferrule 31.
  • the second annular radial flange 36 comprises a first portion 363, a second portion 364, and a third portion 365 lying between the first portion 363 and the second portion 364.
  • the first portion 363 s' extends between the first end 361 and the third portion 365, and the second portion 364 extends between the third portion 365 and the second end 362.
  • the first portion 363 of the second annular radial flange 36 is in contact with the downstream radial hooking flange 16.
  • the second portion 364 is thinned with respect to the first portion 363 and the third portion 365 so as to give a certain flexibility to the second annular radial flange 36 and thus do not over-strain the turbine ring 1 in CMC.
  • the first annular radial flange 32 forms a first annular radial rib extending in the circumferential direction of the ring 1 as well as in the radial direction D R of the ring from the central ferrule 31 towards the center of the ring 1.
  • the turbine ring assembly 1 comprises a single removable annular flange 35 made in one piece and removably attached to the ring support structure 3
  • the removable flange 35 comprises a first free end 351 and a second end 352 shrunk radially to the central ferrule 31 of the annular support structure 3.
  • the removable flange 35 further comprises a first portion 353 extending from the first end 351 and a second portion 354 extending between the first portion 353 and the second end 352.
  • the first portion 353 comprises a first leg 33 and a second leg 34 separate from the first leg 33 and distant from the latter in the axial direction D A , the second leg 34 being upstream of the first leg 33 relative to the direction of flow. of air F intended to pass through the turbine ring assembly 1.
  • the first lug 33 of the removable flange 35 rests against the upstream radial hooking lug 14 of each ring sectors 10 making up the turbine ring 1.
  • the radial retention of the ring 1 is provided by the first tab 33 of the annular flange 35 which is pressed against the upstream radial hooking lug 14 and by the first portion 363 of the second annular radial flange 36 which is pressed against the flange radial downstream attachment 16.
  • the first tab 33 of the annular flange 35 seals between the vein cavity and the cavity outside the vein of the ring.
  • the second tab 34 of the removable annular flange 35 is dedicated to taking up the force of the high pressure distributor (DHP) on the removable annular flange 35, on the one hand, by deforming, and, on the other hand, by making transfer this force to the casing line which is more robust mechanically, that is to say towards the line of the ring support structure 3 as illustrated by the force arrows E shown on the figure 3 .
  • DHP high pressure distributor
  • the first tab 33 and the second tab 34 of the removable annular flange 35 meet at the level of the second portion 354 of the removable annular flange 35.
  • the annular flange 35 comprises an axial stop 355 extending in the radial direction D R from the second end 352 of the annular flange 35.
  • the axial stop 355 extends from the second end 352 in the direction of the central ferrule 31 of the ring support structure 3.
  • the axial stop 355 is fixed by hooping on the central ferrule 31.
  • the axial stop 355 is arranged upstream of the first radial rib formed by the first annular radial flange 32, the latter therefore being downstream of the axial stop 355.
  • the axial stop 355 has an upstream face 355a receiving the gas flow F and a downstream face 355b opposite the upstream face 355a and facing the first radial rib 312.
  • the first radial rib 32 that is to say the first annular radial flange, has an upstream face 32a facing the axial stop 355 of the annular flange 35 and a downstream face 32b opposite the upstream face 32a and facing the second annular radial flange 36.
  • the axial stop 355 has two uses. It allows, on the one hand, the axial position of the annular flange 35 which makes it possible to precisely adjust the axial position of the first lug 33 relative to the upstream radial hooking lug 14 of the ring, to ensure contact. axial controlled between the two parts.
  • the axial stop 355 makes it possible, on the other hand, to limit the tilting of the second lug 34 and to cause the DHP force to pass axially on the central ferrule 31 of the ring support structure 3.
  • the second end 352 of the annular flange 35 comprises a bearing ring 356 projecting downstream in the axial direction D A.
  • the annular flange 35 has an upstream face 35a receiving the gas flow F and a downstream face 35b opposite the upstream face 35a and facing the first annular radial flange 32 and the upstream radial hooking lug. 14.
  • the second portion 354 of the annular flange 35 comprises a bearing ring 356 extending in the axial direction D A from the downstream face 35b of the annular flange 35.
  • the bearing ring 356 has an internal face 356a and an external face 356b opposite the internal face 356a, a first free end 3561, and a second end 3562 integral with the downstream face 35b of the annular flange 35, the first end 3561 being downstream of the second end 3562 when the turbine ring assembly is mounted.
  • the support ring 356 comprises, on its first end 3561, a radial support 358 projecting from the outer face 356b of the support ring 356.
  • the central ferrule 31 of the ring support structure 3 further comprises a second radial rib 314 disposed between the first annular radial flange 32 and the second annular radial flange 36 and projecting in the radial direction D R from the central shell 31.
  • the second radial rib 314 extends in the direction of the ring 1, that is to say in the direction of the radial support 358 of the support ring 356.
  • the second radial rib 314 has at its free end an internal radial face 314a facing the radial support 358.
  • the radial support 358 has, on its free end, an external radial face 358b facing the second radial rib 314 of the central ferrule 31 of the ring support structure 3.
  • the support ring 356 provides greater resistance to tilting induced by the DHP force.
  • the support ring 356 takes up the significant tangential stresses caused by the DHP force and therefore limits the tilting of the annular flange 36.
  • FIG. 4 A sectional view of a second embodiment of the turbine ring assembly is shown.
  • the second embodiment illustrated in figure 4 differs from the first embodiment illustrated on the figures 1 to 3 in that the ring sector 10 has, in the plane defined by the axial D A and radial D R directions , a K-shaped section instead of an inverted ⁇ -shaped section.
  • the third and fourth embodiments illustrated in figures 5 and 6 differ from the first embodiment illustrated on the figures 1 to 3 in that the ring sector 10 has, in the plane defined by the axial D A and radial D R directions , over part of the ring sector 10, an O-shaped section instead of an O-shaped section ⁇ inverted, the ring section 10 being fixed to the ring support structure 3 using a screw 19 and a fastening part 20, the screws 38 being omitted.
  • the second annular radial flange 36 of the ring support structure 3 is separated from the first lug 33 of the annular flange 35 by a distance corresponding to the distance between the upstream radial hooking lugs and downstream 14 and 16 so as to maintain the latter between the first tab 33 of the annular flange 35 and the second annular radial flange 36.
  • the ring assembly comprises two first pins 119 cooperating with the upstream hooking lug 14 and the first lug 33 of the annular flange 35, and two second pins 120 cooperating with the downstream hooking lug 16 and the second annular radial flange 36.
  • the second portion 354 of the annular flange 35 comprises two orifices 3540 for receiving the two first pins 119
  • the third portion 365 of the annular radial flange 36 comprises two orifices 3650 configured to receive the two second 120 pawns.
  • each of the upstream and downstream radial hooking tabs 14 and 16 comprises a first end, 141 and 161, integral with the outer face 12b of the annular base 12 and a second end, 142 and 162, free.
  • the second end 142 of the upstream radial attachment tab 14 comprises two first lugs 17 each comprising an orifice 170 configured to receive a first pin 119.
  • the second end 162 of the downstream radial attachment tab 16 comprises two second ears 18 each comprising an orifice 180 configured to receive a second pin 120.
  • the first and second ears 17 and 18 project out in the radial direction D R of the turbine ring 1 respectively from the second end 142 of the upstream radial attachment tab 14 and of the second end 162 of the downstream radial attachment tab 16.
  • the orifices 170 and 180 can be circular or oblong.
  • the set of orifices 170 and 180 comprises a portion of circular orifices and a portion of oblong orifices.
  • the circular orifices make it possible to tangentially index the rings and prevent them from being able to move tangentially (in particular in the event of contact by the blade).
  • the oblong orifices make it possible to accommodate the differential expansions between the CMC and the metal. CMC has a much lower coefficient of expansion than metal. When hot, the lengths in the tangential direction of the ring sector and of the facing portion of the casing will therefore be different.
  • a first drilling diagram for a case with three lugs, would include a radial circular hole on one radial hooking flange and two tangential oblong holes on the other radial hooking flange
  • a second drilling diagram for a case with at least four ears, would include a circular orifice and an oblong orifice per radial hooking flange facing each other.
  • Other additional cases can also be considered.
  • the first two ears 17 are positioned at two different angular positions with respect to the axis of revolution of the turbine ring 1.
  • the two seconds lugs 18 are positioned at two different angular positions relative to the axis of revolution of the turbine ring 1.
  • each ring sector 10 has, along a plane defined by the axial D A and radial D R directions , a substantially K-shaped section comprising an annular base 12 with, in the radial direction D R of the ring, an internal face 12a coated with a layer 13 of abradable material forming a thermal and environmental barrier and which defines the gas stream flow stream in the turbine.
  • Upstream and downstream radial hooking tabs 140, 160 substantially S-shaped extend, in the radial direction D R , from the outer face 12b of the annular base 12 over the entire width thereof and at the bottom. above the upstream and downstream circumferential end portions 121 and 122 of the annular base 12.
  • the radial attachment tabs 140 and 160 have a first end, referenced respectively 1410 and 1610, integral with the annular base 12 and a second free end, respectively referenced 1420 and 1620.
  • the free ends 1420 and 1620 of the radial attachment tabs upstream and downstream 140 and 160 extend either parallel to the plane in which the annular base 12 extends, that is to say in a circular plane, or in a rectilinear manner while the hooking tabs 140 and 160 s 'extend annularly.
  • the surface supports then become linear supports. which offers greater sealing than in the case of point supports.
  • the second end 1620 of the downstream radial hook 160 is held between a portion 3610 of the second annular radial flange 36 projecting in the axial direction D A from the first end 361 of the second annular radial flange 36 in the direction opposite to the direction of flow F and the free end of the associated screw 38, that is to say the screw opposite to the screw head.
  • the second end 1410 of the upstream radial hooking lug 140 is held between a portion 3310 of the first lug 33 of the annular flange 35 projecting in the axial direction D A from the first end 331 of the first lug 33 in the direction flow F and the free end of the associated screw 38.
  • the ring sector 10 comprises an axial attachment tab 17 'extending between the upstream and downstream radial attachment tabs 14 and 16.
  • the axial attachment tab 17' extends more precisely, in the direction axial D A , between the second end 142 of the upstream radial attachment lug 14 and the second end 162 of the downstream radial attachment lug 16.
  • the axial hooking tab 17 ' comprises an upstream end 171' and a downstream end 172 'separated by a central part 170'.
  • the turbine ring assembly comprises a screw 19 and a fastening part 20.
  • the fastening part 20 is fixed to the axial hooking lug 17 '.
  • the fastener 20 further comprises an orifice 21 provided with an internal thread cooperating with a thread of the screw 19 to fix the fastener 20 to the screw 19.
  • the screw 19 comprises a screw head 190 whose diameter is greater. to the diameter of an orifice 39 made in the central ferrule 31 of the support structure of the ring 3 through which the screw 19 is inserted before being screwed to the fastener 20.
  • the support ring 356 further comprises an orifice 3560 traversed by the screw 19 and by a part of the fastening part 20.
  • the orifice 3560 has a diameter greater than that of the fastening part 20.
  • the radial connection of the ring sector 10 with the ring support structure 3 is achieved using the screw 19, the head 190 of which bears on the central crown 31 of the ring support structure 3, and the fastening piece 20 screwed to the screw 19 and fixed to the axial hooking lug 17 'of the ring sector 10, the screw head 190 and the fastener 20 exerting forces in opposite directions to hold together the ring 1 and the ring support structure 3 .
  • FIG. 6 There is shown a schematic sectional view of a fourth embodiment of the turbine ring assembly.
  • the fourth embodiment illustrated in figure 6 is a variant of the third embodiment illustrated in figure 5 .
  • the central ferrule 31 of each ring sector 10 does not include an orifice 39.
  • the ring sector 10 is fixed directly on the support ring 356 using the screw 19 and the fixing part 20.
  • the support ring 356 comprises an orifice 3560 through which it passes. by the screw 19.
  • the orifice 3560 has a diameter smaller than that of the screw head 190.
  • the radial connection of the ring sector 10 with the ring support structure 3 is achieved by means of the screw 19, the head 190 of which bears on the bearing ring 356 of the annular flange 35, and of the fastener 20 screwed to the screw 19 and fixed to the axial lug 17 'of the ring sector 10, the screw head 190 and the fastener 20 exerting forces in opposite directions to hold together the ring 1 and ring support structure 3.
  • each ring sector 10 further comprises rectilinear bearing surfaces 110 mounted on the faces of the upstream and downstream radial hooking tabs 14 and 16 in contact respectively with the first tab 33 of the annular flange 35 and the second radial flange annular 36, that is to say on the upstream face 14a of the upstream radial hooking lug 14 and on the downstream face 16b of the downstream radial hooking lug 16.
  • the rectilinear supports could be mounted on the first tab 33 of the annular flange 35 and on the second downstream annular radial flange 36.
  • the rectilinear supports 110 make it possible to have controlled sealing zones. Indeed, the bearing surfaces 110 between the upstream radial hooking lug 14 and the first lug 33 of the annular flange 35, on the one hand, and between the downstream radial latching lug 16 and the second annular radial flange 36 are included in the same rectilinear plane.
  • Each ring sector 10 described above is made of a ceramic matrix composite material (CMC) by forming a fiber preform having a shape close to that of the ring sector and densifying the ring sector with a ceramic matrix. .
  • CMC ceramic matrix composite material
  • Ceramic fiber threads for example SiC fiber threads such as those sold by the Japanese company Nippon Carbon under the name “Hi-NicalonS”, or carbon fiber threads. .
  • the fiber preform is advantageously produced by three-dimensional weaving, or multi-layer weaving with provision of unbinding zones making it possible to separate the parts of the preforms corresponding to the hooking tabs 14 and 16 of the sectors 10.
  • the weaving can be of the interlock type, as illustrated.
  • Other three-dimensional or multi-layered weaves can be used, for example multi-plain or multi-satin weaves.
  • the blank can be shaped to obtain a ring sector preform which is consolidated and densified by a ceramic matrix, the densification being able to be carried out in particular by chemical gas infiltration (CVI) which is well known in France. self.
  • CVI chemical gas infiltration
  • the textile preform can be hardened a little by CVI so that it is sufficiently rigid to be handled, before making liquid silicon rise by capillary action in the textile in order to make the densification (“Melt Infiltration”).
  • the ring support structure 3 is for its part made of a metallic material such as a Waspaloy® or inconel 718® or alternatively C263® alloy.
  • the ring sectors 10 are assembled together on an annular tool of the “spider” type comprising, for example, suction cups configured to each hold a ring sector 10.
  • the ring 1 is then mounted on the ring support structure 3 by inserting each second pin 120 into each of the orifices 180 of the second ears 18 of the downstream radial hooking flanges 16 of each ring sector 10 making up the ring. 1.
  • annular flange 35 is fixed to the ring support structure 3 and to the ring 1.
  • the annular flange 35 is cold-mounted on the ring support structure 3 in contact with the stop 32.
  • the shrinking takes place at the level of the two radial contacts.
  • the annular flange 35 is fixed to the ring by inserting each first pin 119 into each of the orifices 170 of the first lugs 17 of the upstream radial hooking tabs 14 of each ring sector 10 making up ring 1.
  • the ring 1 is thus held in position axially by means of the first lug 33 of the annular flange 35 and of the second annular radial flange 36 bearing respectively upstream and downstream on the rectilinear bearing surfaces 110 of the radial lugs. respectively upstream 14 and downstream 16 hooks.
  • an axial prestress can be applied to the first tab 33 of the annular flange 35 and to the upstream radial hooking lug 14 for compensate for the differential expansion effect between the CMC material of the ring 1 and the metal of the ring support structure 3.
  • the first tab 33 of the annular flange 35 is maintained in axial stress by mechanical elements placed upstream as this is shown in dotted lines on the figure 3 .
  • the ring 1 is held in position radially by means of the first and second pins 119 and 120 cooperating with the first and second ears 17 and 18 and the orifices 3540 and 3650 of the annular flange 35 and of the annular radial flange 36.
  • the invention thus provides a turbine ring assembly making it possible to maintain each ring sector in a deterministic manner while allowing, on the one hand, the ring sector, and by extension the ring, to be deformed under the effects of temperature rises and pressure variations, in particular independently of the metallic parts at the interface, and, on the other hand, while improving the seal between the non-duct sector and the duct sector and by simplifying manipulations and reducing their number for mounting the ring assembly.
  • the invention provides a turbine ring assembly comprising an upstream annular flange dedicated to the absorption of the DHP force and thus to induce low levels of force in the CMC ring, a contact stop between the annular flange dedicated to the absorption of the DHP force and the annular flange used to hold the ring, the stop making it possible to ensure non-contact of the lower parts of the two flanges during tilting of the upstream flange.
  • the turbine ring assembly according to the invention also makes it possible to control the rigidity at the level of the upstream and downstream axial contacts between the CMC ring and the metal casing. As a result, sealing is ensured in all circumstances, without inducing excessively high axial forces on the ring.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (7)

  1. Turbinenringanordnung, die eine Vielzahl von Ringsektoren (10), die einen Turbinenring (1) bilden, und eine Ringhalterstruktur (3) umfasst, wobei jeder Ringsektor (10) entlang einer Schnittebene, die durch eine axiale Richtung (DA) und eine radiale Richtung (DR) des Turbinenrings (1) definiert ist, einen Teil aufweist, der eine ringförmige Basis (12) mit, in der radialen Richtung (DR) des Turbinenrings (1), einer Innenseite (12a), die die Innenseite des Turbinenrings (1) definiert, und einer Außenseite (12b) bildet, von der aus hervorstehend sich eine erste und eine zweite Aufhängelasche (14, 16) erstrecken, wobei die Ringhalterstruktur (3) einen mittleren Mantel (31) umfasst, von dem aus hervorstehend sich ein erster und ein zweiter radialer Flansch (32, 36) erstrecken, zwischen denen die erste und die zweite Aufhängelasche (14, 16) von jedem Ringsektor (10) gehalten werden,
    dadurch gekennzeichnet, dass sie einen einstückigen ringförmigen Flansch (35) umfasst, der auf abnehmbare Weise an dem mittleren Mantel (31) befestigt ist, wobei der ringförmige Flansch (35) ein freies erstes Ende (351), ein zweites Ende (352), das an den mittleren Mantel (31) gekoppelt ist, wobei ein erster Abschnitt (353) sich von dem ersten Ende (351) erstreckt, ein zweiter Abschnitt (354) sich zwischen dem ersten Abschnitt (353) und dem zweiten Ende (352) erstreckt,
    wobei der erste Abschnitt (353) eine erste und eine zweite Lasche (33, 34) umfasst, die getrennt sind, wobei die erste Lasche (33) gegen die erste Aufhängelasche (14) aufliegt und die zweite Lasche (34) von der ersten Lasche (33) in der axialen Richtung (DA) entfernt ist, wobei die zweite Lasche (34) sich in Bezug auf die Richtung einer Luftströmung (F), die dazu bestimmt ist, die Turbinenringanordnung (1) zu durchqueren, stromaufwärts der ersten Lasche (33) befindet,
    der zweite Abschnitt (354) des ringförmigen Flansches (35) einen Stützmantel (356) umfasst, der sich hervorstehend stromabwärts in der axialen Richtung (DA) erstreckt, wobei der Stützmantel (356) eine radiale Stütze (358) umfasst, die mit dem mittleren Mantel (31) der Ringhalterstruktur (3) in Kontakt ist.
  2. Anordnung nach Anspruch 1, wobei der erste ringförmige radiale Bund (32) eine erste Rippe bildet, die in der radialen Richtung (DR) des Turbinenrings (1) hin zur Innenseite des Rings hervorsteht, und das zweite Ende (352) des ringförmigen Flansches (35) einen axialen Anschlag (355) umfasst, der sich in der radialen Richtung (DR) des Turbinenrings (1) hin zur Außenseite des Rings erstreckt, wobei der axiale Anschlag (355) stromaufwärts des ersten ringförmigen radialen Bundes (32) angeordnet ist und in der axialen Richtung (DA) des Turbinenrings gegen den ersten ringförmigen radialen Flansch (32) aufliegt.
  3. Anordnung nach einem der Ansprüche 1 oder 2, wobei der mittlere Mantel (31) der Ringhalterstruktur (3) ferner eine zweite Rippe (314) umfasst, die in der radialen Richtung (DR) des Turbinenrings (1) hin zur Innenseite des Rings hervorsteht und eine Stützoberfläche (314a) aufweist, auf die die radiale Stütze (358) des Stützmantels (356) sich stützt, wobei die zweite Rippe (314) zwischen dem ersten und dem zweiten radialen Bund (32, 36) der Ringhalterstruktur (3) angeordnet ist.
  4. Anordnung nach einem der Ansprüche 1 bis 3, wobei der Ringsektor (10) in der Schnittebene, die durch die axiale Richtung (DA) und die radiale Richtung (DR) definiert ist, einen Querschnitt mit der Form des umgekehrten griechischen Buchstaben Pi (n) aufweist, wobei die Anordnung für jeden Ringsektor (10) mindestens drei Stifte (119, 120) umfasst, um den Ringsektor (10) radial in Position zu halten, wobei die erste und die zweite Aufhängelasche (14, 16) von jedem Ringsektor (10) jeweils ein erstes Ende (141, 161), das mit der Außenseite (12b) der ringförmigen Basis (12) fest verbunden ist, ein freies zweites Ende (142, 162), mindestens drei Ösen (17, 18) zur Aufnahme der mindestens drei Stifte (119, 120), mindestens zwei Ösen (17), die sich von dem zweiten Ende (142, 162) von einer von der ersten oder der zweiten Aufhängelasche (14, 16) in der radialen Richtung (DR) des Turbinenrings (1) hervorstehend erstrecken, und mindestens eine Öse (18) umfassen, die sich von dem zweiten Ende (162, 142) der anderen Aufhängelasche (16, 14) in der radialen Richtung (DR) des Turbinenrings (1) hervorstehend erstreckt, wobei jede Aufnahmeöse (17, 18) eine Öffnung (170, 180) zur Aufnahme von einem der Stifte (119, 120) umfasst.
  5. Anordnung nach einem der Ansprüche 1 bis 3, wobei der Ringsektor (10) in der Schnittebene, die durch die axiale Richtung (DA) und die radiale Richtung (DR) definiert ist, einen Querschnitt aufweist, der die Form eines länglichen K aufweist, wobei die erste und die zweite Aufhängelasche (14, 16) eine S-Form aufweisen.
  6. Anordnung nach einem der Ansprüche 1 bis 3, wobei der Ringsektor (10) auf mindestens einem radialen Bereich des Ringsektors entlang der Schnittebene, die durch die axiale Richtung (DA) und die radiale Richtung (DR) definiert ist, einen O-förmigen Querschnitt aufweist, wobei die erste und die zweite Aufhängelasche (14, 16) jeweils ein erstes Ende (141, 161), das fest mit der Außenseite (12b) verbunden ist, und ein freies zweites Ende (142, 162) aufweisen, und jeder Ringsektor (10) eine dritte und eine vierte Aufhängelasche (17') umfasst, die sich jeweils in der axialen Richtung (DA) des Turbinenrings (1) zwischen einem zweiten Ende (142) der ersten Aufhängelasche (14) und einem zweiten Ende (162) der zweiten Aufhängelasche (16) erstrecken, wobei jeder Ringsektor (10) durch eine Befestigungsschraube (19), die einen Schraubenkopf (190), der gegen die Ringhalterstruktur (3) anliegt, und ein Gewinde umfasst, das mit einem Innengewinde zusammenwirkt, das in einer Befestigungsplatte (20) hergestellt ist, an der Ringhalterstruktur (3) befestigt ist, wobei die Befestigungsplatte (20) mit der dritten und der vierten Aufhängelasche (17') zusammenwirkt,
  7. Turbomaschine, die eine Turbinenringanordnung (1) nach einem der Ansprüche 1 bis 6 umfasst.
EP18714568.5A 2017-03-16 2018-03-13 Deckbanddichtungsvorrichtung Active EP3596315B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1752151A FR3064024B1 (fr) 2017-03-16 2017-03-16 Ensemble d'anneau de turbine
PCT/FR2018/050589 WO2018172655A1 (fr) 2017-03-16 2018-03-13 Ensemble d'anneau de turbine

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EP3596315A1 EP3596315A1 (de) 2020-01-22
EP3596315B1 true EP3596315B1 (de) 2021-07-28

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EP (1) EP3596315B1 (de)
CN (1) CN110573695B (de)
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CN109751088A (zh) * 2019-03-25 2019-05-14 中国船舶重工集团公司第七0三研究所 一种用于船用燃气轮机的分块式涡轮外环连接结构
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Also Published As

Publication number Publication date
CN110573695B (zh) 2022-06-07
FR3064024B1 (fr) 2019-09-13
US11028720B2 (en) 2021-06-08
CN110573695A (zh) 2019-12-13
EP3596315A1 (de) 2020-01-22
US20210115806A1 (en) 2021-04-22
WO2018172655A1 (fr) 2018-09-27
FR3064024A1 (fr) 2018-09-21

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