EP3870807B1 - Turbinenringanordnung mit einer gewölbten und rechteckigen auflagefläche - Google Patents

Turbinenringanordnung mit einer gewölbten und rechteckigen auflagefläche Download PDF

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Publication number
EP3870807B1
EP3870807B1 EP19842803.9A EP19842803A EP3870807B1 EP 3870807 B1 EP3870807 B1 EP 3870807B1 EP 19842803 A EP19842803 A EP 19842803A EP 3870807 B1 EP3870807 B1 EP 3870807B1
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EP
European Patent Office
Prior art keywords
ring
radial
turbine
sector
rectilinear
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Application number
EP19842803.9A
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English (en)
French (fr)
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EP3870807A1 (de
Inventor
Antoine Claude Michel Etienne Danis
Sébastien Serge Francis CONGRATEL
Clément Jean Pierre DUFFAU
Lucien Henri Jacques QUENNEHEN
Nicolas Paul TABLEAU
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP3870807A1 publication Critical patent/EP3870807A1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
    • 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

  • a turbine ring assembly includes a plurality of ceramic matrix composite material ring sectors and a ring support structure.
  • CMC materials have good mechanical properties making them suitable for forming 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 ring is clamped between two metal lugs.
  • the downstream leg is directly linked to the casing, describing a one-piece ring, ensuring increased sealing compared to a solution with a sectorized spacer.
  • the upstream leg includes a sectorized flange screwed onto the casing.
  • Another flange is dedicated to taking up the force of the high pressure distributor (force DHP). It makes it possible to take up the DHP force and to transfer it directly to the casing, without passing the forces through the CMC ring.
  • force DHP high pressure distributor
  • pre-tightening is carried out during assembly. This pre-tightening makes it possible to compensate for the differential axial expansion between the CMC ring and the metal parts in contact. Thus, when hot, axial contact is maintained and sealing between the vein cavity and the cavity outside the vein is ensured.
  • the invention aims to provide a turbine ring assembly allowing each ring sector to be held in a deterministic manner, that is to say in such a way as to control its position and prevent it from vibrating. , on the one hand, while allowing the ring sector, and by extension the ring, to deform under the effects of temperature rises and pressure variations, and this in particular independently of the metal parts at the interface, and , on the other hand, while improving sealing and simplifying 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 has, according to a section plane defined by an axial direction and a radial direction of the turbine ring, and orthogonal to a circumferential direction of the turbine ring, a part forming an annular base with, in the radial direction of the turbine ring, an inner face defining the inner face of the turbine ring and an outer face from which project a first and a second hooking lugs.
  • the ring support structure comprises a central ferrule from which project a first and a second radial flanges between which are held the first and second hooking lugs of each ring sector and an annular flange comprising a first free end resting against the first hooking lug and a second end opposite the first end and cooperating with the first radial flange of the central shroud of the ring support structure.
  • Each ring sector extends between a first circumferential end and a second circumferential end each intended to face another ring sector in the circumferential direction, and comprising rectilinear bearing surfaces mounted on the faces of the first and second attachment lugs in contact respectively with the second annular flange and the annular flange and extending along a tangent to the circumferential direction between the first and second circumferential ends of the ring sector.
  • the rectilinear support surfaces of each ring sector have, along the tangent to the circumferential direction, a variable thickness in the axial direction with a minimum thickness at the first and second circumferential ends. of the ring sector and a maximum thickness in a median portion of the rectilinear support.
  • the geometric conformation of the rectilinear support surfaces makes it possible to standardize the distribution of the contact forces between the sectorized CMC rings and the annular ring support structure.
  • the curvature of the rectilinear supports allows on the one hand to lower the maximum stress level in the CMC ring by 80% during assembly and by 20% during operation, compared to a solution, for an equivalent mass, with a straight rectilinear support, i.e. i.e. a rectilinear support having a thickness in the axial direction which is uniform along the tangent to the circumferential direction.
  • the curved shapes of rectilinear supports can be produced by electro-erosion (EDM).
  • curvature ie the distance between the highest point and the lowest point of the support.
  • the value is between 0.1 and 0.5mm.
  • the ring sectors can be made of ceramic matrix composite (CMC) material.
  • CMC ceramic matrix composite
  • the rectilinear bearing surfaces can be electro-eroded surfaces, that is to say produced by electro-erosion.
  • a difference between said maximum thickness and said minimum thickness of the rectilinear support surfaces can be 0.1 mm.
  • the minimum thickness of the rectilinear support surfaces may be less than 0.1 mm.
  • the shape of the bending which corresponds to the value of the radius, may vary according to the desired deformations.
  • the rectilinear bearing surfaces may form a strip extending along said tangent to the circumferential direction (D C ) and in the radial direction, the rectilinear bearing surfaces having a height extending in the radial direction of between 0.5 and 5 mm.
  • the height of the supports may vary. Beyond 5 mm a pressure would be too pronounced, and below 0.5 mm the risk of non-contact is too great.
  • the rectilinear bearing surfaces of each ring sector can comprise, in the radial direction, a first radial end and a second radial end, and have, along the radial direction, a variable thickness in the axial direction with a minimum thickness at the radial ends of the ring sector and a maximum thickness in a middle portion of the rectilinear support.
  • the rectilinear support surfaces may have a first axis of symmetry parallel to the radial direction and a second axis of symmetry parallel to the tangent to the circumferential direction.
  • the ring sector may have a section in the Greek letter pi ( ⁇ ) reversed according to the cutting plane defined by the axial direction and the radial direction, and the assembly may comprise, for each ring sector, at least three studs to radially hold the ring sector in position, the first and second hooking lugs 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 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 a pawns.
  • the ring sector may have, over at least one radial range of the ring sector, an O section along the section plane defined by the axial direction and the radial direction, the first and the second attachment lugs each having a first end secured to the external face and a second free end, and each ring sector comprising a third and a fourth attachment lugs each extending, in the axial direction of the turbine ring, between the second end of the first attachment lug and the second end of the second attachment lug, each ring sector being fixed to the structure of ring support by a fixing screw comprising a screw head resting against the ring support structure and a thread cooperating with a thread made in a fixing plate, the fixing plate cooperating with the third and fourth lugs of hooking.
  • the ring sector further comprises radial studs extending between the central ferrule and the third and fourth attachment lugs.
  • Another object of the invention proposes a turbomachine comprising a turbine ring assembly as defined above.
  • FIG 1 shows a high pressure turbine ring assembly comprising a ceramic matrix composite (CMC) material turbine ring 1 and a metal ring support 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 directions D A and radial D R , a section substantially in the shape of the inverted Greek letter ⁇ .
  • the section in fact comprises an annular base 12 and radial attachment lugs upstream and downstream, 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 an 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 inner face 12a of the annular base 12 is coated with a layer 13 of abradable material forming a thermal barrier and designed to cooperate with the rotating blades of the turbine.
  • the terms "internal” and “external” are used here in reference to the radial direction D R in the turbine.
  • the upstream and downstream radial attachment lugs 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 radial attachment lugs upstream and downstream 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 the ring sector 10.
  • the turbine ring portion 1 represented comprises a complete ring sector 10 surrounded by two half ring sectors 10.
  • the complete ring sector is referenced 10a and the half ring sectors are referenced 10b on the figure 2 .
  • the ring sectors will subsequently be referenced 10 to designate both 10a and 10b.
  • 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 shroud 31 towards the center of the ring 1. It comprises a first free end 361 and a second end 362 secured to the central shroud 31.
  • the second annular radial flange 36 comprises a first portion 363, a second portion 364, and a third portion 365 between the first portion 363 and the second portion 364.
  • the first portion 363 is 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 radial flange of downstream attachment 16.
  • the first portion 363 and the third portion 365 have an increased thickness compared to that of the second portion 364 to provide increased rigidity to the second radial flange compared to the upstream part comprising in particular the first radial flange 32 , so as to reduce the axial leakage of the ring in the case of a rectilinear support.
  • the first annular radial flange 32 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 321 and a second end 322 secured to the central shroud 31.
  • the first annular flange 33 is arranged downstream of the second annular flange 34.
  • the first annular flange 33 is in a single piece while the second annular flange 34 can be sectorized into a plurality of annular sectors of second flange 34 or be in a single piece. piece. Integrating a first annular flange in one piece, in other words non-sectored, makes it possible to ensure axial sealing between the sectorized CMC ring and the annular casing, in particular by avoiding inter-sector leaks compared to a case where the first upstream flange is sectorized.
  • the first annular flange 33 has a first free end 331 and a second end 332 removably fixed to the ring support structure 3, and more particularly to the first annular radial flange 32.
  • the first annular flange 33 has a first portion 333 and a second portion 334, the first portion 333 extending between the first end 331 and the second portion 334, and the second portion 334 extending between the first portion 333 and the second end 332.
  • the second annular flange 34 has a first free end 341 and a second end 342 opposite the first end 341 and in contact with the central ring 31.
  • the second end 342 of the second annular flange 34 is also fixed in a removable manner to the structure of ring support 3, and more particularly to the first annular radial flange 32.
  • the second annular flange 34 further comprises a first portion 343 and a second portion 344, the first portion 343 extending between the first end 341 and the second portion 344, and the second portion 344 extending between the first portion 343 and the second end 342.
  • the first portion 333 of the first upstream flange 33 bears against the radial upstream attachment lug 14 of the ring sector 10.
  • the first and second upstream flanges 33 and 34 are shaped to have the first portions 333 and 343 axially spaced apart. one from the other and the second portions 334 and 344 in contact, the two flanges 33 and 34 being removably fixed to the flange upstream annular radial 32 using screws 60 and fixing nuts 61, the screws 60 passing through orifices 3340, 3440 and 320 provided respectively in the second portions 334 and 344 of the two upstream flanges 33 and 34 as well as in the upstream annular radial flange 32.
  • the first portion 333 of the first annular flange 33 is in abutment against the radial attachment lug upstream 14 of each of the ring sectors 10 making up the turbine ring 1, and the second portion 334 of the first annular flange 34 is in abutment against at least a part of the first annular radial flange 32.
  • the second annular flange 34 is dedicated to taking up the force of the high pressure distributor (DHP) on the ring assembly 1 by passing this force to the casing line which is mechanically more robust, i.e. say towards the line of the ring support structure 3 as illustrated by the force arrows E presented on the picture 3 .
  • the residual force, which passes through the first upstream flange 33, is reduced since the first portion 333 of the first upstream flange 33 has a reduced section, and is therefore more flexible, which makes it possible to apply a minimum of force to the ring 1 CMC.
  • the second annular radial flange 36 of the ring support structure 3 is separated from the first annular flange 33 by a distance corresponding to the spacing of the radial attachment lugs upstream and downstream 14 and 16 so as to maintain the latter between the first annular radial flange 32 and the second annular radial flange 36.
  • the ring assembly comprises two first pins 19 cooperating with the upstream hooking lug 14 and the first annular flange 33, and two second pins 20 cooperating with the downstream attachment lug 16 and the second annular radial flange 36.
  • the second portion 334 of the first annular flange 33 comprises two orifices 3340 for receiving the first two pins 19, and the third portion 365 of the annular radial flange 36 comprises two orifices 3650 configured to receive the two second pawns 120.
  • each of the upstream and downstream radial attachment lugs 14 and 16 comprises a first end, 141 and 161, secured to 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 lug 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 lug 16 comprises two second lugs 18 each comprising an orifice 180 configured to receive a second pin 20.
  • the first and second lugs 17 and 18 project in the radial direction D R of the turbine ring 1 respectively from the second end 142 of the upstream radial attachment lug 14 and the second end 162 of the downstream radial attachment lug 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 holes allow the rings to be indexed tangentially and prevent them from moving tangentially (especially in the event of a blade strike).
  • the slotted holes accommodate differential expansion 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 housing portion facing each other will therefore be different. If there were only circular orifices, the metal casing would impose its movements on the CMC ring, which would be a source of high mechanical stresses in the ring sector.
  • a first drilling pattern for a case with three ears, would include a radial circular hole on a radial attachment flange and two tangential oblong holes on the other radial attachment flange
  • a second drilling diagram for a case with at least four lugs, would comprise a circular orifice and an oblong orifice per radial hooking flange facing each other.
  • Other ancillary cases can also be considered.
  • the first two lugs 17 are positioned at two different angular positions relative to the axis of revolution of the turbine ring 1.
  • the two seconds ears 18 are positioned at two different angular positions with respect to the axis of revolution of the turbine ring 1.
  • Each ring sector 10 further comprises rectilinear bearing surfaces 110 mounted on the faces of the upstream and downstream radial attachment lugs 14 and 16 in contact respectively with the first annular flange 33 and the second annular radial flange 36, c that is to say on the upstream face 14a of the upstream radial attachment lug 14 and on the downstream face 16b of the downstream radial attachment lug 16.
  • 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 annular flange 33, on the one hand, and between the radial downstream hooking lug 16 and the second annular radial flange 36 are included in the same rectilinear plane.
  • each rectilinear support 110 comprises a thickness measured in the axial direction D A which varies along the rectilinear support 110 in the direction of the tangent to the circumferential direction D C .
  • the thickness measured is minimum at the ends of the rectilinear support 110 and maximum in a median region 110m of the rectilinear support 110.
  • the ends of the rectilinear support 110 are located on either side of the ring sector 10 in the circumferential direction D C , each end of the ring sector 10a facing another ring sector 10b.
  • the ends of the rectilinear support 110 of a ring sector 10 are adjacent, even coincide with the circumferential ends 102 and 104 of the ring sector 10.
  • the minimum thickness of the rectilinear supports 110 is less than 0.1 mm and the difference between the maximum thickness and the minimum thickness of the rectilinear support surfaces 110 is 0.1 mm.
  • FIG. 5 schematically represents a view of a rectilinear support of the turbine ring assembly according to a section plane orthogonal to the circumferential direction D C , and comprising the axial direction D A and the radial direction D R , according to a variant mode achievement.
  • the rectilinear supports 110 form a strip extending along the tangent to the circumferential direction D C and along the radial direction D R .
  • the straight bearings 110 may comprise a uniform thickness in the radial direction, or, as illustrated in the figure 5 , a variable thickness in the radial direction D R .
  • the rectilinear supports 110 comprise, in the radial direction D R , a first radial end 112 and a second radial end 114, and have, along the radial direction D R , a variable thickness in the axial direction D A with a thickness minimum at the radial ends 112 and 114 of the ring sector 10 and a maximum thickness in a middle portion 116 of the rectilinear support 110.
  • the radial retention of the ring 1 is ensured by the first annular flange 33 which is pressed against the first annular radial flange 32 of the ring support structure 3 and on the upstream radial attachment lug 14.
  • the first annular flange 33 seals between the vein cavity and the cavity outside the ring vein.
  • the second annular flange 34 ensures the connection between the downstream part of the DHP, the ring support structure 3, or casing, by radial surface contact, and the first annular flange 33 by axial surface contact.
  • the ring support structure 3 further comprises radial studs 38 which allow the ring to be pressed in the low radial position, that is to say towards the vein, in a deterministic manner. There is indeed a clearance between the axial pins and the bores on the ring to compensate for the differential expansion between the metal and the CMC elements which occurs when hot.
  • the radial pins 38 cooperate with orifices 380 made in the radial direction D R in the central crown 31 of the ring support structure 3.
  • FIG. 6 Shown is a cross-sectional schematic view of a third embodiment of the turbine ring assembly.
  • the third embodiment illustrated in Figure 8 differs from the first embodiment illustrated in the figures 2 to 6 in that the ring sector 10 has, in the plane defined by the axial D A and radial D R directions, over a part of the ring sector 10, an O-shaped section instead of a ⁇ reversed, the ring section 10 being fixed to the ring support structure 3 by means of a screw 19 and a fixing piece 20, the screws 38 being eliminated.
  • the ring sector 10 comprises an axial attachment lug 17' extending between the radial upstream and downstream attachment lugs 14 and 16.
  • the axial attachment lug 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 attachment lug 17' comprises an upstream end 171' and a downstream end 172' separated by a central part 170'.
  • the upstream and downstream ends 171' and 172' of the axial hooking lug 17' protrude, in the radial direction D R , from the second end 142, 162 of the radial hooking lug 14, 16 to which they are coupled, so as to have a central part 170′ of axial attachment lug 17′ raised relative to the second ends 142 and 162 of the radial upstream and downstream attachment lugs 14 and 16.
  • the turbine ring assembly comprises a screw 19 and a fixing piece 20.
  • the fixing piece 20 is fixed on the axial attachment lug 17'.
  • the fixing part 20 further comprises an orifice 21 provided with a thread cooperating with a thread of the screw 19 to fix the fixing part 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 shroud 31 of the support structure of the ring 3 through which the screw 19 is inserted before being screwed to the fixing piece 20.
  • the radial connection of the ring sector 10 with the ring support structure 3 is carried out using the screw 19, the head 190 of which rests on the central crown 31 of the ring support structure. 3, and of the fixing part 20 screwed to the screw 19 and fixed to the axial attachment lug 17' of the ring sector 10, the screw head 190 and the fixing part 20 exerting forces in opposite directions to hold ring 1 and ring support structure 3 together.
  • the radial retention of the ring downwards can be ensured using four radial pins plated on the axial hooking lug 17 ', and the radial retention upwards of the ring can be ensured by a pick head, integral with the screw 19, placed under the ring in the cavity between the axial hooking lug 17' and the external face 12b of the annular base.
  • Each ring sector 10 described above is made of ceramic matrix composite material (CMC) by forming a fibrous preform having a shape close to that of the ring sector and densification of the ring sector by a ceramic matrix .
  • CMC ceramic matrix composite material
  • ceramic fiber yarns for example SiC fiber yarns such as those marketed by the Japanese company Nippon Carbon under the name "Hi-NicalonS", or carbon fiber yarns .
  • the fibrous preform is advantageously produced by three-dimensional weaving, or multilayer weaving with development 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 may be of the interlock type, as shown.
  • Other three-dimensional or multi-layer weaving weaves can be used, such as multi-linen or multi-satin weaves. You can refer to the document WO 2006/136755 .
  • 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 gas phase chemical infiltration (CVI) which is well known in self.
  • CVI gas phase chemical infiltration
  • the textile preform can be slightly hardened by CVI so that it is rigid enough to be handled, before bringing liquid silicon up by capillarity in the textile to carry out 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 even 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 20 into each of the orifices 180 of the second lugs 18 of the downstream radial attachment flanges 16 of each ring sector 10 making up the ring 1.
  • All the first pins 19 are then placed in the orifices 170 provided in the first lugs 17 of the radial attachment lug 14 of the ring 1.
  • first annular flange 33 and the second annular flange 34 are fixed to the ring support structure 3 and to the ring 1.
  • the first and second annular flanges 33 and 34 are fixed by shrink fitting to the support structure d ring 3.
  • the force DHP exerted in the direction of the flow F reinforces this attachment during engine operation.
  • the first annular flange 33 is fixed to the ring by inserting each first pin 19 into each of the orifices 170 of the first lugs 17 of the upstream radial attachment lugs 14 of each ring sector 10 composing ring 1.
  • the ring 1 is thus held in position axially by means of the first annular flange 33 and the second annular radial flange 36 resting respectively upstream and downstream on the rectilinear bearing surfaces 110 of the radial hooking lugs respectively upstream 14 and downstream 16.
  • an axial prestress can be applied to the first annular flange 33 and to the upstream radial hooking lug 14 to overcome the effect of differential expansion between the material CMC of the ring 1 and the metal of the ring support structure 3.
  • the first annular flange 33 is held in axial stress by mechanical elements placed upstream as shown in dotted lines on the picture 3 .
  • the ring 1 is held in position radially using the first and second pins 19 and 20 cooperating with the first and second lugs 17 and 18 and the orifices 3340 and 3650 of the first annular flange 33 and the annular radial flange 36.
  • the invention thus provides a turbine ring assembly allowing each ring sector to be maintained in a deterministic manner while allowing, on the one hand, 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 metal parts at the interface, and, on the other hand, while improving sealing and simplifying manipulations and reducing their number for the assembly of the ring assembly.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Support Of The Bearing (AREA)

Claims (10)

  1. Turbinenringanordnung, die eine Vielzahl von Ringsektoren (10a, 10b), die einen Turbinenring (1) bilden, und eine Ringtragstruktur (3) umfasst,
    wobei jeder Ringsektor (10a, 10b) entlang einer Schnittebene, die durch eine axiale Richtung (DA) und eine radiale Richtung (DR) des Rings und orthogonal zu einer Umfangsrichtung (DC) 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), welche die Innenseite des Turbinenrings (1) definiert, und einer Außenseite (12b) bildet, ausgehend von der sich eine erste und eine zweite Aufhängelasche (14, 16) hervorstehend erstrecken,
    wobei die Ringtragstruktur (3) einen mittleren Mantel (31) umfasst, ausgehend von dem sich hervorstehend ein erster und ein zweiter radialer Bund (32, 36) zum Halten jedes Ringsektors (10) und ein ringförmiger Flansch (33) erstrecken, der ein erstes freies Ende (331), das gegen die erste Aufhängelasche (14) in Auflage ist, und ein zweites Ende (332) aufweist, das dem ersten Ende (331) entgegengesetzt ist und mit dem ersten radialen Bund (32) zusammenwirkt,
    jeder Ringsektor (10a, 10b) sich zwischen einem ersten Umfangsende (102) und einem zweiten Umfangsende (104) erstreckt, die jeweils dazu bestimmt sind, einem anderen, in der Umfangsrichtung (DC) benachbarten Ringsektor (10b, 10a) gegenüberzustehen, und eine erste geradlinige Auflageoberfläche (110), die auf der stromaufwärtigen Seite (14a) der ersten Aufhängelasche (14) im Kontakt mit dem ringförmigen Flansch (33) angeordnet ist, und eine zweite geradlinige Auflageoberfläche (110) umfasst, die auf einer stromabwärtigen Seite (16b) der zweiten Aufhängelasche (16) im Kontakt mit dem zweiten radialen Bund (36) angeordnet ist, wobei jede von der ersten und der zweiten geradlinigen Auflageoberfläche (110) sich entlang einer Tangente zur Umfangsrichtung (DC) zwischen dem ersten und dem zweiten Umfangsende (102, 104) des Ringsektors (10a, 10b) erstreckt,
    dadurch gekennzeichnet, dass die geradlinigen Auflageoberflächen (110) von jedem Ringsektor (10a, 10b) entlang der Tangente zu der Umfangsrichtung (DC) eine in der axialen Richtung (DA) veränderliche Dicke mit einer Mindestdicke am ersten und am zweiten Umfangsende (102, 104) des Ringsektors (10a, 10b) und einer Höchstdicke in einem mittleren Abschnitt (110m) der geradlinigen Auflageoberfläche (110) besitzen.
  2. Anordnung nach Anspruch 1, wobei die geradlinigen Auflageoberflächen elektroerodierte Oberflächen sind.
  3. Anordnung nach einem der Ansprüche 1 oder 2, wobei ein Abstand zwischen der Höchstdicke und der Mindestdicke der geradlinigen Auflageoberflächen (110) zwischen 0,1 und 0,5 mm beträgt.
  4. Anordnung nach einem der Ansprüche 1 bis 3, wobei die Mindestdicke der geradlinigen Auflageoberflächen (110) kleiner als 0,1 mm ist.
  5. Anordnung nach einem der Ansprüche 1 bis 4, wobei die geradlinigen Auflageoberflächen (110) ein Band bilden, das sich entlang der Tangente zur Umfangsrichtung (DC) und entlang der radialen Richtung (DR) erstreckt, wobei die geradlinigen Auflageoberflächen (110) eine sich entlang der radialen Richtung (DR) erstreckende Höhe (H) von zwischen 0,5 und 5 mm aufweisen.
  6. Anordnung nach Anspruch 5, wobei die geradlinigen Auflageoberflächen (110) von jedem Ringsektor (10) in der radialen Richtung (DR) ein erstes radiales Ende (112) und ein zweites radiales Ende (114) umfassen und entlang der radialen Richtung (DR) eine in der axialen Richtung (DA) veränderliche Dicke mit einer Mindestdicke an den radialen Enden (112, 114) des Ringsektors (10a, 10b) und einer Höchstdicke in einem radial mittleren Abschnitt (116) der geradlinigen Auflage (110) besitzen.
  7. Anordnung nach Anspruch 6, wobei die geradlinigen Auflageoberflächen (110) eine erste Symmetrieachse parallel zur radialen Richtung (DR) und eine zweite Symmetrieachse parallel zur Tangente zur Umfangsrichtung (DC) aufweisen.
  8. Anordnung nach einem der Ansprüche 1 bis 7, wobei der Ringsektor einen pi-förmigen Querschnitt entlang der Schnittebene aufweist, die durch die axiale Richtung (DA) und die radiale Richtung (DR) definiert ist, und die Anordnung für jeden Ringsektor (10a, 10b) mindestens drei Stifte (19, 20) zum radialen Halten des Ringsektors (10a, 10b) an der Position umfasst, wobei die erste und die zweite Aufhängelasche (14, 16) von jedem Ringsektor (10a, 10b) jeweils ein erstes Ende (141, 161), das fest mit der Außenseite (12b) der ringförmigen Basis (12) verbunden ist, ein freies zweites Ende (142, 162), mindestens drei Ösen (17, 18) zur Aufnahme der mindestens drei Stifte (19, 20), mindestens zwei Ösen (17), die sich von dem zweiten Ende (142, 162) 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 eines der Stifte (19, 20) umfasst.
  9. Anordnung nach einem der Ansprüche 1 bis 7, wobei der Ringsektor einen O-förmigen Querschnitt entlang der Schnittebene aufweist, die durch die axiale Richtung (DA) und die radiale Richtung (DR) definiert ist, 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 (10a, 10b) eine dritte und eine vierte Aufhängelasche (17', 18') umfasst, die sich jeweils in der axialen Richtung (DA) des Turbinenrings (1) zwischen dem zweiten Ende (142) der ersten Aufhängelasche (14) und dem zweiten Ende (162) der zweiten Aufhängelasche (16) erstrecken, wobei jeder Ringsektor (10a, 10b) an der Ringtragstruktur (3) durch eine Befestigungsschraube (19) befestigt ist, die einen Schraubenkopf (190) in Auflage gegen die Ringtragstruktur (3) und ein Außengewinde umfasst, das mit einem Innengewinde zusammenwirkt, das in einer Befestigungsplatte (20) hergestellt ist, wobei die Befestigungsplatte (20) mit der dritten und der vierten Aufhängelasche (17', 18') zusammenwirkt.
  10. Turbinentriebwerk, das eine Turbinenringanordnung (1) nach einem der Ansprüche 1 bis 9 umfasst.
EP19842803.9A 2018-12-19 2019-12-10 Turbinenringanordnung mit einer gewölbten und rechteckigen auflagefläche Active EP3870807B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1873403A FR3090731B1 (fr) 2018-12-19 2018-12-19 Ensemble d’anneau de turbine à appuis rectilignes bombés.
PCT/FR2019/052989 WO2020128222A1 (fr) 2018-12-19 2019-12-10 Ensemble d'anneau de turbine à appuis rectilignes bombés

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EP3870807B1 true EP3870807B1 (de) 2023-04-05

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Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113638774B (zh) * 2020-05-11 2022-06-28 中国航发商用航空发动机有限责任公司 一种连接件及防热失配连接装置
WO2023280935A1 (de) * 2021-07-06 2023-01-12 Turbo Systems Switzerland Ltd. Verschleissarmer turbinengehäuse-klemmverbund
US11773751B1 (en) 2022-11-29 2023-10-03 Rolls-Royce Corporation Ceramic matrix composite blade track segment with pin-locating threaded insert
US11840936B1 (en) 2022-11-30 2023-12-12 Rolls-Royce Corporation Ceramic matrix composite blade track segment with pin-locating shim kit
US11713694B1 (en) 2022-11-30 2023-08-01 Rolls-Royce Corporation Ceramic matrix composite blade track segment with two-piece carrier
US11732604B1 (en) 2022-12-01 2023-08-22 Rolls-Royce Corporation Ceramic matrix composite blade track segment with integrated cooling passages
US11976571B1 (en) * 2022-12-13 2024-05-07 Rtx Corporation Machinable coating with thermal protection
US11885225B1 (en) 2023-01-25 2024-01-30 Rolls-Royce Corporation Turbine blade track with ceramic matrix composite segments having attachment flange draft angles

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2540939A1 (fr) 1983-02-10 1984-08-17 Snecma Anneau d'etancheite pour un rotor de turbine d'une turbomachine et installation de turbomachine munie de tels anneaux
US6733235B2 (en) 2002-03-28 2004-05-11 General Electric Company Shroud segment and assembly for a turbine engine
FR2887601B1 (fr) 2005-06-24 2007-10-05 Snecma Moteurs Sa Piece mecanique et procede de fabrication d'une telle piece
CN102272419A (zh) 2009-03-09 2011-12-07 斯奈克玛 涡轮环组件
FR2955898B1 (fr) 2010-02-02 2012-10-26 Snecma Etancheite amont d'un anneau en cmc dans une turbine de turbomachine
US8740552B2 (en) 2010-05-28 2014-06-03 General Electric Company Low-ductility turbine shroud and mounting apparatus
US8905709B2 (en) 2010-09-30 2014-12-09 General Electric Company Low-ductility open channel turbine shroud
US9759082B2 (en) 2013-03-12 2017-09-12 Rolls-Royce Corporation Turbine blade track assembly
US10301960B2 (en) * 2015-07-13 2019-05-28 General Electric Company Shroud assembly for gas turbine engine
FR3045715B1 (fr) * 2015-12-18 2018-01-26 Safran Aircraft Engines Ensemble d'anneau de turbine avec maintien a froid et a chaud
FR3055146B1 (fr) * 2016-08-19 2020-05-29 Safran Aircraft Engines Ensemble d'anneau de turbine
FR3055147B1 (fr) * 2016-08-19 2020-05-29 Safran Aircraft Engines Ensemble d'anneau de turbine

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WO2020128222A1 (fr) 2020-06-25
US11441434B2 (en) 2022-09-13
CN113195872A (zh) 2021-07-30
FR3090731B1 (fr) 2021-01-08
EP3870807A1 (de) 2021-09-01
US20220025775A1 (en) 2022-01-27
CN113195872B (zh) 2022-06-07

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