EP3298247B1 - Turbine ring assembly supported by flanges - Google Patents

Turbine ring assembly supported by flanges Download PDF

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Publication number
EP3298247B1
EP3298247B1 EP16729311.7A EP16729311A EP3298247B1 EP 3298247 B1 EP3298247 B1 EP 3298247B1 EP 16729311 A EP16729311 A EP 16729311A EP 3298247 B1 EP3298247 B1 EP 3298247B1
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EP
European Patent Office
Prior art keywords
ring
annular
flange
support structure
tabs
Prior art date
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EP16729311.7A
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German (de)
French (fr)
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EP3298247A1 (en
Inventor
Clément ROUSSILLE
Gaël EVAIN
Aline Planckeel
Claire GROLEAU
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP3298247A1 publication Critical patent/EP3298247A1/en
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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
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • 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
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • 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 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.
  • Ceramic matrix composite materials are known to retain their mechanical properties at high temperatures, which makes them suitable for constituting hot structural elements.
  • the production of turbine ring sectors in a single piece in CMC is described in particular in the document US 2012/0027572 .
  • the ring sectors comprise an annular base whose internal face defines the internal face of the turbine ring and an external face from which extend two parts forming tabs whose ends are engaged in housings of a structure metal ring support.
  • Turbine ring assemblies made from a plurality of ring sectors are also disclosed in the documents US 6,406,256 , US 4,650,394 And US 6,302,642 .
  • CMC ring sectors make it possible to significantly reduce the ventilation necessary for cooling the turbine ring.
  • maintaining the ring sectors in position remains a problem, particularly with regard to the differential expansions which can occur between the metal support structure and the CMC ring sectors.
  • another problem lies in the constraints caused by compulsory travel.
  • the ring sectors must be maintained in position even in the event of contact between the top of a blade of a moving wheel and the internal face of the ring sectors.
  • the invention aims to avoid such drawbacks and proposes for this purpose a turbine ring assembly comprising a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure comprising a first and second annular flanges, each ring sector having a part forming an annular base with an internal face defining the internal face of the turbine ring and an external face from which extend radially a first and a second lug , the tabs of each ring sector being held between the two annular flanges of the ring support structure, the first and second tabs of the ring sectors each comprising an annular groove on its face facing the first flange respectively ring and the second annular flange of the ring support structure, the first and second annular flanges of the ring support structure each comprising an annular projection on its face facing one of the ring sector lugs , the annular projection of the first flange being housed in the annular groove of the first tab of each ring sector while the annul
  • Each elastic element is interposed between the upper wall of the grooves present on the first tab, respectively on the second tab, ring sectors and the upper wall of the annular projection of the first flange, respectively of the second flange, of the ring structure, or each elastic element is interposed between the lower wall of the grooves present on the first tab, respectively on the second tab, of the ring sectors and the lower wall of the annular projection of the first flange, respectively of the second flange, of the ring structure.
  • each elastic element is formed of a split annular rod mounted elastically pre-stressed between one of the annular projections and the corresponding groove.
  • each elastic element is formed of at least one strip of a rigid material having a wavy shape.
  • the elastic element can in this case be formed from corrugated sheet metal.
  • the projections of the two annular flanges of the ring support structure exert a stress on the annular grooves of the tabs of the ring sectors, one of the flanges of the ring support structure being elastically deformable in the axial direction of the turbine ring.
  • the contact is further improved and, consequently , the seal between the flanges and the legs even when these elements are subjected to high temperatures.
  • the elasticity of one of the flanges of the ring structure makes it possible to compensate for the differential expansions between the legs of the CMC ring sectors and the flanges of the structure of metal ring support without significantly increasing the stress exerted “cold” by the flanges on the lugs of the ring sectors.
  • the elastically deformable flange of the ring support structure may in particular have a thickness less than that of the other flange of said ring support structure.
  • the turbine ring assembly according to the invention, it further comprises a plurality of pins engaged both in at least one of the annular flanges of the ring support structure and the tabs ring sectors facing said at least annular flange.
  • the pawns make it possible to block the possible rotation of the ring sectors in the ring support structure.
  • the elastically deformable flange of the ring support structure comprises a plurality of hooks distributed on its face opposite to that facing the lugs of the sectors of ring.
  • the presence of the hooks facilitates the spacing of the elastically deformable flange for the insertion of the lugs of the ring sectors between the flanges without having to forcefully slide the lugs between the flanges.
  • the ring support structure comprises an annular retention flange mounted on the turbine casing, the annular retention flange comprising an annular web forming one of the flanges of the ring support structure.
  • the flange comprises a first series of teeth distributed circumferentially on said flange while the turbine casing comprises a second series of teeth distributed circumferentially on said casing, the teeth of the first series of teeth and the teeth of the second series of teeth forming a circumferential clutch.
  • the turbine casing comprises an annular boss extending between a shroud of the casing and the flange of the ring structure. This prevents upstream-downstream leaks between the casing and the flange.
  • 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 5.
  • the turbine ring 1 is formed of a plurality of ring sectors 10, the figure 1 being a view in radial section along a plane passing between two contiguous ring sectors.
  • the arrow D A indicates the axial direction relative to the turbine ring 1 while the arrow DR indicates the radial direction relative to the turbine ring 1.
  • Each sector of ring 10 has a section substantially in the shape of an inverted ⁇ with an annular base 12 whose internal face coated with a layer 13 of abradable material defines the flow path of gas flow in the turbine.
  • Upstream and downstream tabs 14, 16 extend from the external face of the annular base 12 in the radial direction DR.
  • upstream and downstream are used here in reference to the direction of flow of the gas flow in the turbine (arrow F).
  • the ring support structure 3 which is integral with a turbine casing 30 comprises an annular upstream radial flange 32 comprising a projection 34 on its face facing the upstream lugs 14 of the ring sectors 10, the projection 34 being housed in an annular groove 140 present on the external face 14a of the upstream tabs 14.
  • the ring support structure comprises an annular downstream radial flange 36 comprising a projection 38 on its face facing the downstream tabs 16 of the sectors d ring 10, the projection 38 being housed in an annular groove 160 present on the external face 16a of the downstream lugs 16.
  • each ring sector 10 is mounted in pre-tension between the annular flanges 32 and 36 so that the flanges exert, at least "cold", this is that is to say at an ambient temperature of approximately 25°C, a stress on the legs 14 and 16.
  • the ring sectors 10 are also held by blocking pins. More precisely and as illustrated on the figure 1 , pins 40 are engaged both in the annular upstream radial flange 32 of the ring support structure 3 and in the upstream lugs 14 of the ring sectors 10. For this purpose, the pins 40 each pass through an orifice respectively 33 provided in the annular upstream radial flange 32 and an orifice 15 provided in each upstream lug 14, the orifices 33 and 15 being aligned during the assembly of the ring sectors 10 on the ring support structure 3. Likewise, pins 41 are engaged both in the annular downstream radial flange 36 of the ring support structure 3 and in the downstream lugs 16 of the ring sectors 10.
  • the pins 41 each pass through an orifice 37 provided in the annular downstream radial flange 36 and an orifice 17 provided in each downstream lug 16, the orifices 37 and 17 being aligned during the assembly of the ring sectors 10 on the ring support structure 3.
  • inter-sector sealing is ensured by sealing tabs housed in facing grooves in the facing edges of two neighboring ring sectors.
  • a tongue 22a extends over almost the entire length of the annular base 12 in the middle part thereof.
  • Another tab 22b extends along the tab 14 and over part of the annular base 12.
  • Another tab 22c extends along the tab 16. At one end, the tab 22c comes abutting on tongue 22a and on tongue 22b.
  • the tabs 22a, 22b, 22c are for example metallic and are mounted with cold clearance in their housings in order to ensure the sealing function at the temperatures encountered in service.
  • ventilation holes 32a formed in the flange 32 make it possible to bring cooling air to the exterior side of the turbine ring 10.
  • At least one elastic element is interposed between each projection of the annular flanges of the ring support structure and each annular groove of the tabs of the ring sectors. More precisely, in the embodiment described here, a split annular ring 60 is interposed between the upper wall 142 of the groove 140 present on the external face 14a of the upstream lugs 14 of the ring sectors 10 and the upper face 34c of the projection 34 of the annular upstream radial flange 32 while a split annular ring 70 is interposed between the upper wall 162 of the groove 160 present on the external face 16a of the downstream lugs 16 of the ring sectors 10 and the upper face 38c of the projection 38 of the annular downstream radial flange 36.
  • the split annular rods 60 and 70 constitute elastic elements in that they present in the free state, that is to say before assembly, a radius greater than the defined radius by the upper walls 142 and 162 respectively of the annular grooves 140 and 160.
  • the split annular rods 60 and 70 can be made for example of René 41 TM alloy. Before assembly, an elastic stress is applied to the rods 60 and 70 to tighten them on themselves and reduce their radius in order to insert them into the grooves 140 and 160. Once placed in the grooves 140 and 160, the rods 60 and 70 relax and press against the upper walls 142 and 162 of the annular grooves 140 and 160. The rods 60 and 70 thus ensure that the ring sectors 10 are maintained in position on the ring support structure 3.
  • the rods 60 and 70 exert a holding force Fm on the ring sectors 10 which is directed in the radial direction DR and which makes it possible to ensure contact, on the one hand, between the lower wall 143 of the groove 140 of the upstream tab 14 and the lower face 34b of the projection 34 of the annular upstream radial flange 32, and, on the other hand, between the lower wall 163 of the groove 160 of the upstream tab 16 and the lower face 38b of the projection 38 of the annular downstream radial flange 36 ( Figure 1 ).
  • Each ring sector 10 described above is made of ceramic matrix composite material (CMC) by formation of 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 can be used, for example SiC fiber yarns such as those marketed by the Japanese company Nippon Carbon under the name “Nicalon TM ", or carbon fiber yarns.
  • the fibrous preform is advantageously produced by three-dimensional weaving, or multilayer weaving with the provision of unbinding zones making it possible to separate the parts of preforms corresponding to the legs 14 and 16 of the sectors 10.
  • the weave can be interlock type, as shown.
  • Other three-dimensional or multi-layer weave weaves can be used, for example multi-canvas 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 infiltration in the gas phase (CVI) which is well known in self.
  • CVI gas phase
  • the ring support structure 3 is made of a metallic material such as a Waspaloy ® or Inconel 718 alloy.
  • the production of the turbine ring assembly continues by mounting the ring sectors 10 on the ring support structure 3.
  • the spacing E between the end 34a of the annular projection 34 of the annular upstream radial flange 32 and the end 38a of the annular projection 38 of the annular downstream radial flange 36 at “rest”, i.e. say when no ring sector is mounted between the flanges, is less than the distance D present between the funds 141 and 161 annular grooves 140 and 160 respectively of the upstream and downstream tabs 14 and 16 of the ring sectors.
  • the ring support structure comprises at least one annular flange which is elastically deformable in the axial direction D A of the ring.
  • the annular downstream radial flange 36 which is elastically deformable.
  • the annular downstream radial flange 36 of the ring support structure 3 has a reduced thickness compared to the annular upstream radial flange 32, which gives it a certain elasticity.
  • the split rods 60 and 70 are respectively placed against the upper walls 34c and 38c of the projections 34 and 38 of the annular radial flanges 32 and 36.
  • the ring sectors 10 are then mounted one after the other on the ring support structure 3.
  • the annular downstream radial flange 36 is pulled in the direction D A as shown on the figures 3 And 4 in order to increase the spacing between the flanges 32 and 36 and allow the insertion of the projections 34 and 38 present respectively on the flanges 32 and 36 in the grooves 140 and 160 present on the lugs 14 and 16 without risk of damage to the ring sector 10.
  • the projections 34 and 38 of the flanges 14 and 16 inserted into the grooves 140 and 160 of the tabs 14 and 16 and said tabs 14 and 16 positioned so as to align the orifices 33 and 15, of a hand, and 17 and 37 on the other hand, the flange 36 is released.
  • the projections 34 and 38 respectively of the flanges 32 and 36 then exert an axial constraint (direction D A ) holding on the lugs 14 and 16 of the ring sector while the rods 60 and 70 exert a radial constraint (direction D R ) on the legs 14 and 16 of the sectors.
  • the latter comprises a plurality of hooks 39 distributed on its face 36a, face which is opposite the face 36b of the flange 36 facing the downstream lugs 16 of the ring sectors 10 ( Figure 3 ).
  • the traction in the axial direction D A of the ring exerted on the elastically deformable flange 36 is here carried out by means of a tool 50 comprising at least one arm 51 whose end comprises a hook 510 which is engaged in a hook 39 present on the external face 36a of the flange 36.
  • the number of hooks 39 distributed on the face 36a of the flange 36 is defined according to the number of traction points that one wishes to have on the flange 36. This number depends mainly on the elastic nature of the flange. Other shapes and arrangements of means making it possible to exert traction in the axial direction D A on one of the flanges of the ring support structure can of course be envisaged in the context of the present invention.
  • each ring sector tab 14 or 16 may include one or more orifices for the passage of a locking pin .
  • the rods 60 and 70 can be placed between the lower wall of the grooves of the lugs of the ring sectors and the lower face of the projections of the annular radial flanges.
  • FIG 5 illustrates this alternative embodiment for the upstream tabs 14 of the ring sectors 10 and the annular upstream radial flange 32 of the ring support structure 3.
  • the ring 60 is placed between the lower wall 143 of the groove 140 of the upstream tab 14 of the ring sector 10 and the lower face 34b of the projection 34 of the annular upstream radial flange 32.
  • the ring 60 exerts a force of holding Fm which is directed in the radial direction DR and which makes it possible to ensure contact, on the one hand, between the upper wall 142 of the groove 140 of the upstream tab 14 and the upper face 34c of the projection 34 of the flange annular upstream radial 32.
  • the high turbine ring assembly pressure comprises a turbine ring 101 made of ceramic matrix composite (CMC) material and a metal ring support structure 103.
  • the turbine ring 101 surrounds a set of rotating blades 105.
  • the turbine ring 101 is formed of 'a plurality of ring sectors 110, the Figure 6 being a view in radial section along a plane passing between two contiguous ring sectors.
  • the arrow D A indicates the axial direction relative to the turbine ring 101 while the arrow D R indicates the radial direction relative to the turbine ring 101.
  • Each ring sector 110 has a section substantially in the shape of an inverted ⁇ with an annular base 112 whose internal face coated with a layer 113 of abradable material defines the gas flow path in the turbine.
  • Upstream and downstream tabs 114, 116 extend from the external face of the annular base 12 in the radial direction D R.
  • upstream and downstream are used here in reference to the direction of flow of the gas flow in the turbine (arrow F).
  • the ring support structure 103 is formed of two parts, namely a first part corresponding to an annular upstream radial flange 132 which is preferably formed integrally with a turbine casing 130 and a second part corresponding to an annular retention flange 150 mounted on the turbine casing 130.
  • the annular upstream radial flange 132 has a projection 134 on its face facing the upstream lugs 114 of the ring sectors 110, the projection 134 is housed in an annular groove 1140 present on the external face 114a of the upstream tabs 114.
  • the flange 150 On the downstream side, the flange 150 comprises an annular web 157 which forms an annular downstream radial flange 154 comprising a projection 155 on its face facing the downstream tabs 116 of the ring sectors 110, the projection being housed in an annular groove 160 present on the external face 116a of the downstream tabs 116.
  • the flange 150 comprises an annular body 151 extending axially and comprising, on the upstream side, the annular web 157 and, on the downstream side, a first series of teeth 152 distributed circumferentially on the flange 150 and spaced from each other by first engagement passages 153 ( figures 9 And 12 ).
  • the turbine casing 130 comprises on the downstream side a second series of teeth 135 extending radially from the internal surface of the shroud 138 of the turbine casing 130.
  • the teeth 135 are distributed circumferentially on the internal surface 138a of the ferrule 138 and spaced from each other by second engagement passages 136 ( Figure 9 ).
  • the teeth 152 and 135 cooperate with each other to form a circumferential clutch.
  • each ring sector 110 is mounted in pre-tension between the annular flanges 132 and 154 so that the flanges exert, at least "cold", this is that is to say at an ambient temperature of approximately 25°C, a stress on the legs 114 and 116.
  • the ring sectors 110 are also held by blocking pins. More precisely and as illustrated on the Figure 6 , pins 140 are engaged both in the annular upstream radial flange 132 of the ring support structure 103 and in the upstream lugs 114 of the ring sectors 110. For this purpose, the pins 140 each pass through an orifice respectively 133 provided in the annular upstream radial flange 132 and an orifice 115 provided in each upstream lug 114, the orifices 133 and 115 being aligned during the assembly of the ring sectors 110 on the ring support structure 103.
  • pins 141 are engaged both in the annular downstream radial flange 154 of the flange 150 and in the downstream lugs 116 of the ring sectors 110.
  • the pins 141 each pass through an orifice 156 provided in the annular downstream radial flange 154 and an orifice 117 provided in each downstream tab 116, the orifices 156 and 117 being aligned during the assembly of the ring sectors 110 on the ring support structure 103.
  • inter-sector sealing is ensured by sealing tabs housed in facing grooves in the facing edges of two neighboring ring sectors.
  • a tongue 122a extends over almost the entire length of the annular base 112 in the middle part thereof.
  • Another tab 122b extends along the tab 114 and over part of the annular base 112.
  • Another tab 122c extends along the tab 116. At one end, the tab 122c abuts the tab 122a and on the tab 122b.
  • the tabs 122a, 122b, 122c are for example metallic and are mounted with cold clearance in their housings in order to ensure the sealing function at the temperatures encountered in service.
  • ventilation holes 132a formed in the flange 132 make it possible to bring cooling air to the exterior side of the turbine ring 110.
  • the seal between the upstream and downstream of the turbine ring assembly is ensured by an annular boss 131 extending radially from the internal surface 138a of the shroud 138 of the turbine casing 103 and of which the free end is in contact with the surface of the body 151 of the flange 150.
  • At least one elastic element is interposed between each projection of the annular flanges of the ring support structure and each annular groove of the tabs of the ring sectors. More precisely, in the embodiment described here, a split annular corrugated sheet 170 is interposed between the upper wall 1142 of the groove 1140 present on the external face 114a of the upstream lugs 114 of the ring sectors 110 and the upper face 134c of the projection 134 of the annular upstream radial flange 132 while a split annular corrugated sheet 180 is interposed between the upper wall 1162 of the groove 1160 present on the external face 116a of the downstream lugs 116 of the ring sectors 110 and the upper face 155c of the projection 155 of the annular downstream radial flange 154.
  • the annular corrugated sheets 170 and 180 constitute elastic elements. They can in particular be made of metallic material such as a René 41 TM alloy or
  • the corrugated sheets 170 and 180 are alternately in contact with the annular grooves 1140 and 1160 and the projections 134 and 155. The corrugated sheets 170 and 180 thus ensure that the ring sectors 110 are maintained in position on the ring support structure. 103.
  • each ring sector 110 described above is made of ceramic matrix composite material (CMC) by formation of 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 can be used, for example SiC fiber yarns such as those marketed by the Japanese company Nippon Carbon under the name “Nicalon TM ", or carbon fiber yarns. 1
  • the fibrous preform is advantageously produced by three-dimensional weaving, or multilayer weaving with the provision of unbinding zones making it possible to separate the parts of preforms corresponding to the tabs 114 and 116 of the sectors 110.
  • the weave can be interlock type, as shown.
  • Other three-dimensional or multi-layer weave weaves can be used, for example multi-canvas 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 infiltration in the gas phase (CVI) which is well known in self.
  • CVI gas phase
  • the ring support structure 103 is made of a metallic material such as a Waspaloy ® or Inconel 718 alloy.
  • the production of the turbine ring assembly continues by mounting the ring sectors 110 on the ring support structure 103.
  • the ring sectors 110 are first fixed by their upstream tab 114 to the annular upstream radial flange 132 of the ring support structure 103 by pins 140 which are engaged in the aligned orifices 133 and 115 provided respectively in the annular upstream radial flange 132 and in the upstream tab 114, the annular corrugated sheet 170 having been previously placed against the upper face 134c of the projection 134 of the annular upstream radial flange 132.
  • the projection 134 present on the flange 132 is engaged in the grooves 1140 present on the legs 114.
  • the spacing E between the annular upstream radial flange 154 formed by the annular web 157 of the flange 150 and the external surface 152a of the teeth 152 of said flange is greater than the distance D present between the bottom 1161 grooves 1160 of the downstream tabs 116 of the ring sectors and the internal face 135b of the teeth 135 present on the turbine casing 130 ( figure 8 ).
  • the ring support structure comprises at least one annular flange which is elastically deformable in the axial direction D A of the ring.
  • the annular downstream radial flange 154 present on the flange 150 which is elastically deformable.
  • the annular web 157 forming the annular downstream radial flange 154 of the ring support structure 103 has a reduced thickness compared to the annular upstream radial flange 132, which gives it a certain elasticity.
  • the flange 150 is mounted on the turbine casing 130 by placing the annular corrugated sheet 180 against the upper face 155c of the projection 155 of the annular upstream radial flange 154 of the flange 150 and by engaging the projections 155 in the grooves 1160 present on the downstream tabs 116.
  • the teeth 152 present on the flange 150 are first positioned opposite the engagement passages 136 provided on the turbine casing 130, the teeth 135 present on said turbine casing also being placed opposite the engagement passages 153 provided between the teeth 152 on the flange 150.
  • pins 141 are engaged in the aligned orifices 156 and 117 provided respectively in the downstream annular radial flange 154 and in the downstream tab 116.
  • Each tab 114 or 116 of the ring sector can include a or several holes for the passage of a blocking pin.
  • the corrugated sheets 170 and 180 can be placed between the lower wall of the grooves of the tabs of the ring sectors and the lower face of the projections of the annular radial flanges.
  • the corrugated sheets 170 and 180 ensure elastic retention of the ring sectors 110 in the radial direction D R by alternating contact points, on the one hand, between the lower wall 1143 of the groove 1140 of the tab upstream 114 and the lower face 134b of the projection 134 of the annular upstream radial flange 132 (for the sheet 170), and, on the other hand, between the lower wall 1163 of the groove 1160 of the upstream tab 116 and the lower face 155b of the projection 155 of the annular downstream radial flange 154 (for the sheet 180).

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

Description

Arrière-plan de l'inventionBackground of the invention

Le domaine d'application de l'invention est notamment celui des moteurs aéronautiques à turbine à gaz. L'invention est toutefois applicable à d'autres turbomachines, par exemple des turbines industrielles.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.

Les matériaux composites à matrice céramique, ou CMC, sont connus pour conserver leurs propriétés mécaniques à des températures élevées, ce qui les rend aptes à constituer des éléments de structure chaude.Ceramic matrix composite materials, or CMC, are known to retain their mechanical properties at high temperatures, which makes them suitable for constituting hot structural elements.

Dans des moteurs aéronautiques à turbine à gaz, l'amélioration du rendement et la réduction de certaines émissions polluantes conduisent à rechercher un fonctionnement à des températures toujours plus élevées. Dans le cas d'ensembles d'anneau de turbine entièrement métalliques, il est nécessaire de refroidir tous les éléments de l'ensemble et en particulier l'anneau de turbine qui est soumis à des flux très chauds, typiquement supérieurs à la température supportable par le matériau métallique. Ce refroidissement a un impact significatif sur la performance du moteur puisque le flux de refroidissement utilisé est prélevé sur le flux principal du moteur. En outre, l'utilisation de métal pour l'anneau de turbine limite les possibilités d'augmenter la température au niveau de la turbine, ce qui permettrait pourtant d'améliorer les performances des moteurs aéronautiques.In gas turbine aeronautical engines, improving efficiency and reducing certain polluting emissions lead to the search for operation at ever higher temperatures. In the case of all-metallic turbine ring assemblies, it is necessary to cool all the elements of the assembly and in particular the turbine ring which is subjected to very hot flows, typically higher than the temperature bearable by the metallic material. This cooling has a significant impact on the performance of the engine since the cooling flow used is taken from the main flow of the engine. In addition, the use of metal for the turbine ring limits the possibilities of increasing the temperature at the turbine level, which would nevertheless improve the performance of aeronautical engines.

C'est pourquoi l'utilisation de CMC pour différentes parties chaudes des moteurs a déjà été envisagée, d'autant que les CMC présentent comme avantage complémentaire une masse volumique inférieure à celle de métaux réfractaires traditionnellement utilisés.This is why the use of CMC for various hot parts of engines has already been considered, especially since CMCs have the additional advantage of a lower density than that of refractory metals traditionally used.

Ainsi, la réalisation de secteurs d'anneau de turbine en une seule pièce en CMC est notamment décrite dans le document US 2012/0027572 . Les secteurs d'anneau comportent une base annulaire dont la face interne définit la face interne de l'anneau de turbine et une face externe à partir de laquelle s'étendent deux parties formant pattes dont les extrémités sont engagées dans des logements d'une structure métallique de support d'anneau.Thus, the production of turbine ring sectors in a single piece in CMC is described in particular in the document US 2012/0027572 . The ring sectors comprise an annular base whose internal face defines the internal face of the turbine ring and an external face from which extend two parts forming tabs whose ends are engaged in housings of a structure metal ring support.

Des ensembles d'anneau de turbine réalisés à partir d'une pluralité de secteurs d'anneau sont également divulgués dans les documents US 6 406 256 , US 4 650 394 et US 6 302 642 .Turbine ring assemblies made from a plurality of ring sectors are also disclosed in the documents US 6,406,256 , US 4,650,394 And US 6,302,642 .

L'utilisation de secteurs d'anneau en CMC permet de réduire significativement la ventilation nécessaire au refroidissement de l'anneau de turbine. Toutefois, le maintien en position des secteurs d'anneau demeure un problème en particulier vis-à-vis des dilatations différentielles qui peuvent se produire entre la structure métallique de support et les secteurs d'anneau en CMC. En outre, une autre problématique réside dans les contraintes engendrées par les déplacements imposés. Par ailleurs, le maintien en position des secteurs d'anneau doit être assuré même en cas de contact entre le sommet d'une aube d'une roue mobile et la face interne des secteurs d'anneau.The use of CMC ring sectors makes it possible to significantly reduce the ventilation necessary for cooling the turbine ring. However, maintaining the ring sectors in position remains a problem, particularly with regard to the differential expansions which can occur between the metal support structure and the CMC ring sectors. In addition, another problem lies in the constraints caused by compulsory travel. Furthermore, the ring sectors must be maintained in position even in the event of contact between the top of a blade of a moving wheel and the internal face of the ring sectors.

Objet et résumé de l'inventionObject and summary of the invention

L'invention vise à éviter de tels inconvénients et propose à cet effet un ensemble d'anneau de turbine comprenant une pluralité de secteurs d'anneau en matériau composite à matrice céramique formant un anneau de turbine et une structure de support d'anneau comportant une première et une deuxième brides annulaires, chaque secteur d'anneau ayant une partie formant base annulaire avec une face interne définissant la face interne de l'anneau de turbine et une face externe à partir de laquelle s'étendent radialement une première et une deuxième pattes, les pattes de chaque secteur d'anneau étant maintenues entre les deux brides annulaires de la structure de support d'anneau, les première et deuxième pattes des secteurs d'anneau comportant chacune une rainure annulaire sur sa face en regard respectivement de la première bride annulaire et de la deuxième bride annulaire de la structure de support d'anneau, les première et deuxième brides annulaires de la structure de support d'anneau comprenant chacune une saillie annulaire sur sa face en regard d'une des pattes de secteurs d'anneau, la saillie annulaire de la première bride étant logée dans la rainure annulaire de la première patte de chaque secteur d'anneau tandis que la saillie annulaire de la deuxième bride est logée dans la rainure annulaire de la deuxième patte de chaque secteur d'anneau, au moins un élément élastique étant interposé entre la saillie annulaire de la première bride et la rainure annulaire de la première patte et entre la saillie annulaire de la deuxième bride et la rainure annulaire de la deuxième patte. Chaque élément élastique est interposé entre la paroi supérieure des rainures présentes sur la première patte, respectivement sur la deuxième patte, des secteurs d'anneau et la paroi supérieure de la saillie annulaire de la première bride, respectivement de la deuxième bride, de la structure d'anneau, ou chaque élément élastique est interposé entre la paroi inférieure des rainures présentes sur la première patte, respectivement sur la deuxième patte, des secteurs d'anneau et la paroi inférieure de la saillie annulaire de la première bride, respectivement de la deuxième bride, de la structure d'anneau.The invention aims to avoid such drawbacks and proposes for this purpose a turbine ring assembly comprising a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure comprising a first and second annular flanges, each ring sector having a part forming an annular base with an internal face defining the internal face of the turbine ring and an external face from which extend radially a first and a second lug , the tabs of each ring sector being held between the two annular flanges of the ring support structure, the first and second tabs of the ring sectors each comprising an annular groove on its face facing the first flange respectively ring and the second annular flange of the ring support structure, the first and second annular flanges of the ring support structure each comprising an annular projection on its face facing one of the ring sector lugs , the annular projection of the first flange being housed in the annular groove of the first tab of each ring sector while the annular projection of the second flange is housed in the annular groove of the second tab of each ring sector, at least one elastic element being interposed between the annular projection of the first flange and the annular groove of the first tab and between the annular projection of the second flange and the annular groove of the second tab. Each elastic element is interposed between the upper wall of the grooves present on the first tab, respectively on the second tab, ring sectors and the upper wall of the annular projection of the first flange, respectively of the second flange, of the ring structure, or each elastic element is interposed between the lower wall of the grooves present on the first tab, respectively on the second tab, of the ring sectors and the lower wall of the annular projection of the first flange, respectively of the second flange, of the ring structure.

En utilisant la géométrie d'accrochage des secteurs d'anneau définie ci-avant et en interposant un élément élastique entre les saillies des brides et les rainures des pattes de secteurs d'anneau, on assure un maintien en position des secteurs d'anneau même en cas de dilatations différentielles entre les secteurs et la structure de support, ces dernières étant compensés par l'élasticité du maintien.By using the hooking geometry of the ring sectors defined above and by interposing an elastic element between the projections of the flanges and the grooves of the ring sector lugs, we ensure that the ring sectors are held in position even in the event of differential expansions between the sectors and the support structure, the latter being compensated by the elasticity of the support.

Selon un mode de réalisation de l'ensemble d'anneau de turbine selon l'invention, chaque élément élastique est formé d'un jonc annulaire fendu monté précontraint élastiquement entre une des saillies annulaires et la rainure correspondante.According to one embodiment of the turbine ring assembly according to the invention, each elastic element is formed of a split annular rod mounted elastically pre-stressed between one of the annular projections and the corresponding groove.

Selon un autre mode de réalisation de l'ensemble d'anneau de turbine selon l'invention, chaque élément élastique est formé d'au moins une bande d'un matériau rigide présentant une forme ondulée. L'élément élastique peut être dans ce cas formé d'une tôle ondulée.According to another embodiment of the turbine ring assembly according to the invention, each elastic element is formed of at least one strip of a rigid material having a wavy shape. The elastic element can in this case be formed from corrugated sheet metal.

Selon une caractéristique particulière de l'ensemble d'anneau de turbine de l'invention, les saillies des deux brides annulaires de la structure de support d'anneau exercent une contrainte sur les rainures annulaires des pattes des secteurs d'anneau, une des brides de la structure de support d'anneau étant élastiquement déformable dans la direction axiale de l'anneau de turbine.According to a particular characteristic of the turbine ring assembly of the invention, the projections of the two annular flanges of the ring support structure exert a stress on the annular grooves of the tabs of the ring sectors, one of the flanges of the ring support structure being elastically deformable in the axial direction of the turbine ring.

En maintenant les secteurs d'anneau entre des brides exerçant via des saillies une contrainte sur les pattes des secteurs, et ce, avec une des brides de la structure de support d'anneau étant élastiquement déformable, on améliore encore le contact et, par conséquent, l'étanchéité entre les brides et les pattes même lorsque ces éléments sont soumis à de hautes températures. En effet, l'élasticité d'une des brides de la structure d'anneau permet de compenser les dilatations différentielles entre les pattes des secteurs d'anneau en CMC et les brides de la structure de support d'anneau en métal sans augmenter significativement la contrainte exercée « à froid » par les brides sur les pattes des secteurs d'anneau.By maintaining the ring sectors between flanges exerting via projections a stress on the tabs of the sectors, and this, with one of the flanges of the ring support structure being elastically deformable, the contact is further improved and, consequently , the seal between the flanges and the legs even when these elements are subjected to high temperatures. Indeed, the elasticity of one of the flanges of the ring structure makes it possible to compensate for the differential expansions between the legs of the CMC ring sectors and the flanges of the structure of metal ring support without significantly increasing the stress exerted “cold” by the flanges on the lugs of the ring sectors.

La bride élastiquement déformable de la structure de support d'anneau peut notamment présenter une épaisseur inférieure à celle de l'autre bride de ladite structure de support d'anneau.The elastically deformable flange of the ring support structure may in particular have a thickness less than that of the other flange of said ring support structure.

Selon un autre aspect de l'ensemble d'anneau de turbine selon l'invention, celui-ci comprend en outre une pluralité de pions engagés à la fois dans au moins une des brides annulaires de la structure de support d'anneau et les pattes des secteurs d'anneau en regard de ladite au moins bride annulaire. Les pions permettent de bloquer la rotation éventuelle des secteurs d'anneau dans la structure de support d'anneau.According to another aspect of the turbine ring assembly according to the invention, it further comprises a plurality of pins engaged both in at least one of the annular flanges of the ring support structure and the tabs ring sectors facing said at least annular flange. The pawns make it possible to block the possible rotation of the ring sectors in the ring support structure.

Selon un autre aspect de l'ensemble d'anneau de turbine selon l'invention, la bride élastiquement déformable de la structure de support d'anneau comporte une pluralité de crochets répartis sur sa face opposée à celle en regard des pattes des secteurs d'anneau. La présence des crochets permet de faciliter l'écartement de la bride élastiquement déformable pour l'insertion des pattes des secteurs d'anneau entre les brides sans avoir à glisser en force les pattes entre les brides.According to another aspect of the turbine ring assembly according to the invention, the elastically deformable flange of the ring support structure comprises a plurality of hooks distributed on its face opposite to that facing the lugs of the sectors of ring. The presence of the hooks facilitates the spacing of the elastically deformable flange for the insertion of the lugs of the ring sectors between the flanges without having to forcefully slide the lugs between the flanges.

Selon un autre mode de réalisation de l'ensemble d'anneau de turbine selon l'invention, la structure de support d'anneau comprend un flasque annulaire de rétention monté sur le carter de turbine, le flasque annulaire de rétention comportant un voile annulaire formant une des brides de la structure de support d'anneau. Le flasque comprend une première série de dents réparties de manière circonférentielle sur ledit flasque tandis que le carter de turbine comprend une deuxième série de dents réparties de manière circonférentielle sur ledit carter, les dents de la première série de dents et les dents de la deuxième série de dents formant un crabotage circonférentiel. Cette liaison par crabotage permet un montage et un démontage aisé des secteurs d'anneau.According to another embodiment of the turbine ring assembly according to the invention, the ring support structure comprises an annular retention flange mounted on the turbine casing, the annular retention flange comprising an annular web forming one of the flanges of the ring support structure. The flange comprises a first series of teeth distributed circumferentially on said flange while the turbine casing comprises a second series of teeth distributed circumferentially on said casing, the teeth of the first series of teeth and the teeth of the second series of teeth forming a circumferential clutch. This interconnection connection allows easy assembly and disassembly of the ring sectors.

Selon un autre aspect de l'ensemble d'anneau de turbine selon l'invention, le carter de turbine comprend un bossage annulaire s'étendant entre une virole du carter et le flasque de la structure d'anneau. On empêche ainsi les fuites amont-aval entre la carter et le flasque.According to another aspect of the turbine ring assembly according to the invention, the turbine casing comprises an annular boss extending between a shroud of the casing and the flange of the ring structure. This prevents upstream-downstream leaks between the casing and the flange.

Brève description des dessins.Brief description of the designs.

L'invention sera mieux comprise à la lecture faite ci-après, à titre indicatif mais non limitatif, en référence aux dessins annexés sur lesquels :

  • la figure 1 est une vue en demi-coupe radiale montrant un mode de réalisation d'un ensemble d'anneau de turbine selon l'invention ;
  • les figures 2 à 4 montrent schématiquement le montage d'un secteur d'anneau dans la structure de support d'anneau de l'ensemble d'anneau de la figure 1 ;
  • la figure 5 est une vue partielle en demi-coupe montrant une variante de réalisation de l'ensemble d'anneau de turbine de la figure 1 ;
  • la figure 6 est une vue en demi-coupe radiale montrant un mode de réalisation d'un ensemble d'anneau de turbine selon l'invention ;
  • les figures 7 à 11 montrent schématiquement le montage d'un secteur d'anneau dans la structure de support d'anneau de l'ensemble d'anneau de la figure 6 ;
  • la figure 12 est une vue schématique en perspective du flasque des figures 6 et 8 à 11.
The invention will be better understood on reading below, for information but not limitation, with reference to the appended drawings in which:
  • there figure 1 is a radial half-section view showing an embodiment of a turbine ring assembly according to the invention;
  • THE figures 2 to 4 schematically show the mounting of a ring sector in the ring support structure of the ring assembly of the figure 1 ;
  • there Figure 5 is a partial half-section view showing an alternative embodiment of the turbine ring assembly of the figure 1 ;
  • there Figure 6 is a radial half-section view showing an embodiment of a turbine ring assembly according to the invention;
  • THE figures 7 to 11 schematically show the mounting of a ring sector in the ring support structure of the ring assembly of the Figure 6 ;
  • there Figure 12 is a schematic perspective view of the flange of the figures 6 And 8 to 11 .

Description détaillée de modes de réalisationDetailed description of embodiments

La figure 1 montre un ensemble d'anneau de turbine haute pression comprenant un anneau de turbine 1 en matériau composite à matrice céramique (CMC) et une structure métallique de support d'anneau 3. L'anneau de turbine 1 entoure un ensemble de pales rotatives 5. L'anneau de turbine 1 est formé d'une pluralité de secteurs d'anneau 10, la figure 1 étant une vue en coupe radiale selon un plan passant entre deux secteurs d'anneaux contigus. La flèche DA indique la direction axiale par rapport à l'anneau de turbine 1 tandis que la flèche DR indique la direction radiale par rapport à l'anneau de turbine 1.There figure 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 5. The turbine ring 1 is formed of a plurality of ring sectors 10, the figure 1 being a view in radial section along a plane passing between two contiguous ring sectors. The arrow D A indicates the axial direction relative to the turbine ring 1 while the arrow DR indicates the radial direction relative to the turbine ring 1.

Chaque secteur d'anneau 10 a une section sensiblement en forme de π inversé avec une base annulaire 12 dont la face interne revêtue d'une couche 13 de matériau abradable définit la veine d'écoulement de flux gazeux dans la turbine. Des pattes amont et aval 14, 16 s'étendent à partir de la face externe de la base annulaire 12 dans la direction radiale DR. Les termes "amont" et "aval" sont utilisés ici en référence au sens d'écoulement du flux gazeux dans la turbine (flèche F).Each sector of ring 10 has a section substantially in the shape of an inverted π with an annular base 12 whose internal face coated with a layer 13 of abradable material defines the flow path of gas flow in the turbine. Upstream and downstream tabs 14, 16 extend from the external face of the annular base 12 in the radial direction DR. The terms "upstream" and "downstream" are used here in reference to the direction of flow of the gas flow in the turbine (arrow F).

La structure de support d'anneau 3 qui est solidaire d'un carter de turbine 30 comprend une bride radiale amont annulaire 32 comportant une saillie 34 sur sa face en regard des pattes amont 14 des secteurs d'anneau 10, la saillie 34 étant logée dans une rainure annulaire 140 présente sur la face externe 14a des pattes amont 14. Du côté aval, la structure de support d'anneau comprend une bride radiale aval annulaire 36 comportant une saillie 38 sur sa face en regard des pattes aval 16 des secteurs d'anneau 10, la saillie 38 étant logée dans une rainure annulaire 160 présente sur la face externe 16a des pattes aval 16.The ring support structure 3 which is integral with a turbine casing 30 comprises an annular upstream radial flange 32 comprising a projection 34 on its face facing the upstream lugs 14 of the ring sectors 10, the projection 34 being housed in an annular groove 140 present on the external face 14a of the upstream tabs 14. On the downstream side, the ring support structure comprises an annular downstream radial flange 36 comprising a projection 38 on its face facing the downstream tabs 16 of the sectors d ring 10, the projection 38 being housed in an annular groove 160 present on the external face 16a of the downstream lugs 16.

Comme expliqué ci-après en détails, les pattes 14 et 16 de chaque secteur d'anneau 10 sont montées en précontrainte entre les brides annulaires 32 et 36 de manière à ce que les brides exercent, au moins à « froid », c'est-à-dire à une température ambiante d'environ 25°C, une contrainte sur les pattes 14 et 16.As explained below in detail, the tabs 14 and 16 of each ring sector 10 are mounted in pre-tension between the annular flanges 32 and 36 so that the flanges exert, at least "cold", this is that is to say at an ambient temperature of approximately 25°C, a stress on the legs 14 and 16.

Par ailleurs, dans l'exemple décrit ici, les secteurs d'anneau 10 sont en outre maintenus par des pions de blocage. Plus précisément et comme illustré sur la figure 1, des pions 40 sont engagés à la fois dans la bride radiale amont annulaire 32 de la structure de support d'anneau 3 et dans les pattes amont 14 des secteurs d'anneau 10. A cet effet, les pions 40 traversent chacun respectivement un orifice 33 ménagé dans la bride radiale amont annulaire 32 et un orifice 15 ménagé dans chaque patte amont 14, les orifices 33 et 15 étant alignés lors du montage des secteurs d'anneau 10 sur la structure de support d'anneau 3. De même, des pions 41 sont engagés à la fois dans la bride radiale aval annulaire 36 de la structure de support d'anneau 3 et dans les pattes aval 16 des secteurs d'anneau 10. A cet effet, les pions 41 traversent chacun respectivement un orifice 37 ménagé dans la bride radiale aval annulaire 36 et un orifice 17 ménagé chaque patte aval 16, les orifices 37 et 17 étant alignés lors du montage des secteurs d'anneau 10 sur la structure de support d'anneau 3.Furthermore, in the example described here, the ring sectors 10 are also held by blocking pins. More precisely and as illustrated on the figure 1 , pins 40 are engaged both in the annular upstream radial flange 32 of the ring support structure 3 and in the upstream lugs 14 of the ring sectors 10. For this purpose, the pins 40 each pass through an orifice respectively 33 provided in the annular upstream radial flange 32 and an orifice 15 provided in each upstream lug 14, the orifices 33 and 15 being aligned during the assembly of the ring sectors 10 on the ring support structure 3. Likewise, pins 41 are engaged both in the annular downstream radial flange 36 of the ring support structure 3 and in the downstream lugs 16 of the ring sectors 10. For this purpose, the pins 41 each pass through an orifice 37 provided in the annular downstream radial flange 36 and an orifice 17 provided in each downstream lug 16, the orifices 37 and 17 being aligned during the assembly of the ring sectors 10 on the ring support structure 3.

En outre, l'étanchéité inter-secteurs est assurée par des languettes d'étanchéité logées dans des rainures se faisant face dans les bords en regard de deux secteurs d'anneau voisin. Une languette 22a s'étend sur presque toute la longueur de la base annulaire 12 dans la partie médiane de celle-ci. Une autre languette 22b s'étend le long de la patte 14 et sur une partie de la base annulaire 12. Une autre languette 22c s'étend le long de la patte 16. A une extrémité, la languette 22c vient en butée sur la languette 22a et sur la languette 22b. Les languettes 22a, 22b, 22c sont par exemple métalliques et sont montées avec jeu à froid dans leurs logements afin d'assurer la fonction d'étanchéité aux températures rencontrées en service.In addition, inter-sector sealing is ensured by sealing tabs housed in facing grooves in the facing edges of two neighboring ring sectors. A tongue 22a extends over almost the entire length of the annular base 12 in the middle part thereof. Another tab 22b extends along the tab 14 and over part of the annular base 12. Another tab 22c extends along the tab 16. At one end, the tab 22c comes abutting on tongue 22a and on tongue 22b. The tabs 22a, 22b, 22c are for example metallic and are mounted with cold clearance in their housings in order to ensure the sealing function at the temperatures encountered in service.

De façon classique, des orifices de ventilation 32a formés dans la bride 32 permettent d'amener de l'air de refroidissement du côté extérieur de l'anneau de turbine 10.Conventionally, ventilation holes 32a formed in the flange 32 make it possible to bring cooling air to the exterior side of the turbine ring 10.

Conformément à la présente invention, au moins un élément élastique est interposé entre chaque saillie des brides annulaires de la structure de support d'anneau et chaque rainure annulaire des pattes des secteurs d'anneau. Plus précisément, dans le mode de réalisation décrit ici, un jonc annulaire fendu 60 est interposé entre la paroi supérieure 142 de la rainure 140 présente sur la face externe 14a des pattes amont 14 des secteurs d'anneau 10 et la face supérieure 34c de la saillie 34 de la bride radiale amont annulaire 32 tandis qu'un jonc annulaire fendu 70 est interposé entre la paroi supérieure 162 de la rainure 160 présente sur la face externe 16a des pattes aval 16 des secteurs d'anneau 10 et la face supérieure 38c de la saillie 38 de la bride radiale aval annulaire 36. Les joncs annulaires fendus 60 et 70 constituent des éléments élastiques en ce qu'ils présentent à l'état libre, c'est-à-dire avant montage, un rayon supérieur au rayon défini par les parois supérieures 142 et 162 respectivement des rainures annulaires 140 et 160. Les joncs annulaires fendus 60 et 70 peuvent être réalisés par exemple en alliage René 41™. Avant montage, une contrainte élastique est appliquée aux joncs 60 et 70 pour les resserrer sur eux-mêmes et diminuer leur rayon afin de les insérer dans les rainures 140 et 160. Une fois placé dans les rainures 140 et 160, les joncs 60 et 70 se détendent et se plaquent contre les parois supérieures 142 et 162 des rainures annulaires 140 et 160. Les joncs 60 et 70 assurent ainsi un maintien en position des secteurs d'anneau 10 sur la structure de support d'anneau 3. Plus précisément, les joncs 60 et 70 exercent une force de maintien Fm sur les secteurs d'anneau 10 qui est dirigée dans la direction radiale DR et qui permet d'assurer un contact, d'une part, entre la paroi inférieure 143 de la rainure 140 de la patte amont 14 et la face inférieure 34b de la saillie 34 de la bride radiale amont annulaire 32, et, d'autre part, entre la paroi inférieure 163 de la rainure 160 de la patte amont 16 et la face inférieure 38b de la saillie 38 de la bride radiale aval annulaire 36 (Figure 1).According to the present invention, at least one elastic element is interposed between each projection of the annular flanges of the ring support structure and each annular groove of the tabs of the ring sectors. More precisely, in the embodiment described here, a split annular ring 60 is interposed between the upper wall 142 of the groove 140 present on the external face 14a of the upstream lugs 14 of the ring sectors 10 and the upper face 34c of the projection 34 of the annular upstream radial flange 32 while a split annular ring 70 is interposed between the upper wall 162 of the groove 160 present on the external face 16a of the downstream lugs 16 of the ring sectors 10 and the upper face 38c of the projection 38 of the annular downstream radial flange 36. The split annular rods 60 and 70 constitute elastic elements in that they present in the free state, that is to say before assembly, a radius greater than the defined radius by the upper walls 142 and 162 respectively of the annular grooves 140 and 160. The split annular rods 60 and 70 can be made for example of René 41 ™ alloy. Before assembly, an elastic stress is applied to the rods 60 and 70 to tighten them on themselves and reduce their radius in order to insert them into the grooves 140 and 160. Once placed in the grooves 140 and 160, the rods 60 and 70 relax and press against the upper walls 142 and 162 of the annular grooves 140 and 160. The rods 60 and 70 thus ensure that the ring sectors 10 are maintained in position on the ring support structure 3. More precisely, the rods 60 and 70 exert a holding force Fm on the ring sectors 10 which is directed in the radial direction DR and which makes it possible to ensure contact, on the one hand, between the lower wall 143 of the groove 140 of the upstream tab 14 and the lower face 34b of the projection 34 of the annular upstream radial flange 32, and, on the other hand, between the lower wall 163 of the groove 160 of the upstream tab 16 and the lower face 38b of the projection 38 of the annular downstream radial flange 36 ( Figure 1 ).

On décrit maintenant un procédé de réalisation d'un ensemble d'anneau de turbine correspondant à celui représenté sur la figure 1.We now describe a method of producing a turbine ring assembly corresponding to that shown in the figure 1 .

Chaque secteur d'anneau 10 décrit ci-avant est réalisé en matériau composite à matrice céramique (CMC) par formation d'une préforme fibreuse ayant une forme voisine de celle du secteur d'anneau et densification du secteur d'anneau par une matrice céramique.Each ring sector 10 described above is made of ceramic matrix composite material (CMC) by formation of a fibrous preform having a shape close to that of the ring sector and densification of the ring sector by a ceramic matrix .

Pour la réalisation de la préforme fibreuse, on peut utiliser des fils en fibres céramique, par exemple des fils en fibres SiC tels que ceux commercialisés par la société japonaise Nippon Carbon sous la dénomination "Nicalon™", ou des fils en fibres de carbone.To produce the fibrous preform, ceramic fiber yarns can be used, for example SiC fiber yarns such as those marketed by the Japanese company Nippon Carbon under the name "Nicalon ™ ", or carbon fiber yarns.

La préforme fibreuse est avantageusement réalisée par tissage tridimensionnel, ou tissage multicouches avec aménagement de zones de déliaison permettant d'écarter les parties de préformes correspondant aux pattes 14 et 16 des secteurs 10.The fibrous preform is advantageously produced by three-dimensional weaving, or multilayer weaving with the provision of unbinding zones making it possible to separate the parts of preforms corresponding to the legs 14 and 16 of the sectors 10.

Le tissage peut être de type interlock, comme illustré. D'autres armures de tissage tridimensionnel ou multicouches peuvent être utilisées comme par exemple des armures multi-toile ou multi-satin. On pourra se référer au document WO 2006/136755 .The weave can be interlock type, as shown. Other three-dimensional or multi-layer weave weaves can be used, for example multi-canvas or multi-satin weaves. We can refer to the document WO 2006/136755 .

Après tissage, l'ébauche peut être mise en forme pour obtenir une préforme de secteur d'anneau qui est consolidée et densifiée par une matrice céramique, la densification pouvant être réalisée notamment par infiltration chimique en phase gazeuse (CVI) qui est bien connue en soi.After weaving, 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 infiltration in the gas phase (CVI) which is well known in self.

Un exemple détaillé de fabrication de secteurs d'anneau en CMC est notamment décrit dans le document US 2012/0027572 .A detailed example of manufacturing CMC ring sectors is described in particular in the document US 2012/0027572 .

La structure de support d'anneau 3 est quant à elle réalisée en un matériau métallique tel qu'un alliage Waspaloy® ou inconel 718.The ring support structure 3 is made of a metallic material such as a Waspaloy ® or Inconel 718 alloy.

La réalisation de l'ensemble d'anneau de turbine se poursuit par le montage des secteurs d'anneau 10 sur la structure de support d'anneau 3. Comme illustré sur la figure 2, l'écartement E entre l'extrémité 34a de la saillie annulaire 34 de la bride radiale amont annulaire 32 et l'extrémité 38a de la saillie annulaire 38 de la bride radiale aval annulaire 36 au « repos », c'est-à-dire lorsqu'aucun secteur d'anneau est monté entre les brides, est inférieur à la distance D présente entre les fonds 141 et 161 des rainures annulaires 140 et 160 respectivement des pattes amont et aval 14 et 16 des secteurs d'anneau.The production of the turbine ring assembly continues by mounting the ring sectors 10 on the ring support structure 3. As illustrated in the figure 2 , the spacing E between the end 34a of the annular projection 34 of the annular upstream radial flange 32 and the end 38a of the annular projection 38 of the annular downstream radial flange 36 at “rest”, i.e. say when no ring sector is mounted between the flanges, is less than the distance D present between the funds 141 and 161 annular grooves 140 and 160 respectively of the upstream and downstream tabs 14 and 16 of the ring sectors.

En définissant un écartement E entre les saillies des brides de la structure de support d'anneau inférieur à la distance D entre les fonds des rainures des pattes de chaque secteur d'anneau, il est possible de monter les secteurs d'anneau en précontrainte entre les brides de la structure de support d'anneau. Toutefois, afin de ne pas endommager les pattes des secteurs d'anneau en CMC lors du montage et conformément à l'invention, la structure de support d'anneau comprend au moins une bride annulaire qui est élastiquement déformable dans la direction axiale DA de l'anneau. Dans l'exemple décrit ici, c'est la bride radiale aval annulaire 36 qui est élastiquement déformable. En effet, la bride radiale aval annulaire 36 de la structure de support d'anneau 3 présente une épaisseur réduite par rapport à la bride radiale amont annulaire 32, ce qui lui confère une certaine élasticité.By defining a spacing E between the projections of the flanges of the ring support structure less than the distance D between the bottoms of the grooves of the tabs of each ring sector, it is possible to mount the ring sectors prestressed between the flanges of the ring support structure. However, in order not to damage the tabs of the CMC ring sectors during assembly and in accordance with the invention, the ring support structure comprises at least one annular flange which is elastically deformable in the axial direction D A of the ring. In the example described here, it is the annular downstream radial flange 36 which is elastically deformable. In fact, the annular downstream radial flange 36 of the ring support structure 3 has a reduced thickness compared to the annular upstream radial flange 32, which gives it a certain elasticity.

Avant le montage des secteurs d'anneau 10 sur la structure de support d'anneau 3, les joncs fendus 60 et 70 sont respectivement placés contre les parois supérieures 34c et 38c des saillies 34 et 38 des brides radiales annulaires 32 et 36.Before mounting the ring sectors 10 on the ring support structure 3, the split rods 60 and 70 are respectively placed against the upper walls 34c and 38c of the projections 34 and 38 of the annular radial flanges 32 and 36.

On monte ensuite les secteurs d'anneau 10 les uns après les autres sur la structure de support d'anneau 3. Lors du montage d'un secteur d'anneau 10, la bride radiale aval annulaire 36 est tirée dans la direction DA comme montré sur les figures 3 et 4 afin d'augmenter l'écartement entre les brides 32 et 36 et permettre l'insertion des saillies 34 et 38 présentes respectivement sur les brides 32 et 36 dans les rainures 140 et 160 présentes sur les pattes 14 et 16 sans risque d'endommagement du secteur d'anneau 10. Une fois les saillies 34 et 38 des brides 14 et 16 insérées dans les rainures 140 et 160 des pattes 14 et 16 et lesdites pattes 14 et 16 positionnées de manière à aligner les orifices 33 et 15, d'une part, et 17 et 37 d'autre part, la bride 36 est relâchée. Les saillies 34 et 38 respectivement des brides 32 et 36 exercent alors une contrainte axiale (direction DA) de maintien sur les pattes 14 et 16 du secteur d'anneau tandis que les joncs 60 et 70 exercent une contrainte radiale (direction DR) sur les pattes 14 et 16 des secteurs . Afin de faciliter l'écartement par traction de la bride radiale aval annulaire 36, celle-ci comporte une pluralité de crochets 39 répartis sur sa face 36a, face qui est opposée à la face 36b de la bride 36 en regard des pattes aval 16 des secteurs d'anneau 10 (figure 3). La traction dans la direction axiale DA de l'anneau exercée sur la bride 36 élastiquement déformable est ici réalisée au moyen d'un outil 50 comprenant au moins un bras 51 dont l'extrémité comporte un crochet 510 qui est engagé dans un crochet 39 présent sur la face externe 36a de la bride 36.The ring sectors 10 are then mounted one after the other on the ring support structure 3. When mounting a ring sector 10, the annular downstream radial flange 36 is pulled in the direction D A as shown on the figures 3 And 4 in order to increase the spacing between the flanges 32 and 36 and allow the insertion of the projections 34 and 38 present respectively on the flanges 32 and 36 in the grooves 140 and 160 present on the lugs 14 and 16 without risk of damage to the ring sector 10. Once the projections 34 and 38 of the flanges 14 and 16 inserted into the grooves 140 and 160 of the tabs 14 and 16 and said tabs 14 and 16 positioned so as to align the orifices 33 and 15, of a hand, and 17 and 37 on the other hand, the flange 36 is released. The projections 34 and 38 respectively of the flanges 32 and 36 then exert an axial constraint (direction D A ) holding on the lugs 14 and 16 of the ring sector while the rods 60 and 70 exert a radial constraint (direction D R ) on the legs 14 and 16 of the sectors. In order to facilitate the spacing by traction of the annular downstream radial flange 36, the latter comprises a plurality of hooks 39 distributed on its face 36a, face which is opposite the face 36b of the flange 36 facing the downstream lugs 16 of the ring sectors 10 ( Figure 3 ). The traction in the axial direction D A of the ring exerted on the elastically deformable flange 36 is here carried out by means of a tool 50 comprising at least one arm 51 whose end comprises a hook 510 which is engaged in a hook 39 present on the external face 36a of the flange 36.

Le nombre de crochets 39 répartis sur la face 36a de la bride 36 est défini en fonction du nombre de points de traction que l'on souhaite avoir sur la bride 36. Ce nombre dépend principalement du caractère élastique de la bride. D'autres formes et dispositions de moyens permettant d'exercer une traction dans la direction axiale DA sur une des brides de la structure de support d'anneau peuvent bien entendu être envisagées dans le cadre de la présente invention.The number of hooks 39 distributed on the face 36a of the flange 36 is defined according to the number of traction points that one wishes to have on the flange 36. This number depends mainly on the elastic nature of the flange. Other shapes and arrangements of means making it possible to exert traction in the axial direction D A on one of the flanges of the ring support structure can of course be envisaged in the context of the present invention.

Une fois le secteur d'anneau 10 inséré et positionné entre les brides 32 et 36, des pions 40 sont engagés dans les orifices alignés 33 et 15 ménagés respectivement dans la bride radiale amont annulaire 32 et dans la patte amont 14, et des pions 41 sont engagés dans les orifices alignés 37 et 17 ménagés respectivement dans la bride radiale aval annulaire 36 et dans la patte aval 16. Chaque patte 14 ou 16 de secteur d'anneau peut comporter un ou plusieurs orifices pour le passage d'un pion de blocage.Once the ring sector 10 inserted and positioned between the flanges 32 and 36, pins 40 are engaged in the aligned orifices 33 and 15 provided respectively in the annular upstream radial flange 32 and in the upstream tab 14, and pins 41 are engaged in the aligned orifices 37 and 17 provided respectively in the annular downstream radial flange 36 and in the downstream tab 16. Each ring sector tab 14 or 16 may include one or more orifices for the passage of a locking pin .

Dans une variante de réalisation, les joncs 60 et 70 peuvent être placés entre la paroi inférieure des rainures des pattes des secteurs d'anneau et la face inférieure des saillie des brides radiales annulaires. La figure 5 illustre cette variante de réalisation pour les pattes amont 14 des secteurs d'anneau 10 et la bride radiale amont annulaire 32 de la structure de support d'anneau 3. Sur la figure 5, le jonc 60 est placé entre la paroi inférieure 143 de la rainure 140 de la patte amont 14 du secteur d'anneau 10 et la face inférieure 34b de la saillie 34 de la bride radiale amont annulaire 32. Le jonc 60 exerce une force de maintien Fm qui est dirigée dans la direction radiale DR et qui permet d'assurer un contact, d'une part, entre la paroi supérieure 142 de la rainure 140 de la patte amont 14 et la face supérieure 34c de la saillie 34 de la bride radiale amont annulaire 32.In a variant embodiment, the rods 60 and 70 can be placed between the lower wall of the grooves of the lugs of the ring sectors and the lower face of the projections of the annular radial flanges. There Figure 5 illustrates this alternative embodiment for the upstream tabs 14 of the ring sectors 10 and the annular upstream radial flange 32 of the ring support structure 3. On the Figure 5 , the ring 60 is placed between the lower wall 143 of the groove 140 of the upstream tab 14 of the ring sector 10 and the lower face 34b of the projection 34 of the annular upstream radial flange 32. The ring 60 exerts a force of holding Fm which is directed in the radial direction DR and which makes it possible to ensure contact, on the one hand, between the upper wall 142 of the groove 140 of the upstream tab 14 and the upper face 34c of the projection 34 of the flange annular upstream radial 32.

La figure 6 montre un ensemble d'anneau de turbine haute pression conformément à un autre mode de réalisation de l'invention. Comme décrite précédemment l'ensemble d'anneau de turbine haute pression comprend un anneau de turbine 101 en matériau composite à matrice céramique (CMC) et une structure métallique de support d'anneau 103. L'anneau de turbine 101 entoure un ensemble de pales rotatives 105. L'anneau de turbine 101 est formé d'une pluralité de secteurs d'anneau 110, la figure 6 étant une vue en coupe radiale selon un plan passant entre deux secteurs d'anneaux contigus. La flèche DA indique la direction axiale par rapport à l'anneau de turbine 101 tandis que la flèche DR indique la direction radiale par rapport à l'anneau de turbine 101.There Figure 6 shows a high pressure turbine ring assembly in accordance with another embodiment of the invention. As described previously, the high turbine ring assembly pressure comprises a turbine ring 101 made of ceramic matrix composite (CMC) material and a metal ring support structure 103. The turbine ring 101 surrounds a set of rotating blades 105. The turbine ring 101 is formed of 'a plurality of ring sectors 110, the Figure 6 being a view in radial section along a plane passing between two contiguous ring sectors. The arrow D A indicates the axial direction relative to the turbine ring 101 while the arrow D R indicates the radial direction relative to the turbine ring 101.

Chaque secteur d'anneau 110 a une section sensiblement en forme de π inversé avec une base annulaire 112 dont la face interne revêtue d'une couche 113 de matériau abradable définit la veine d'écoulement de flux gazeux dans la turbine. Des pattes amont et aval 114, 116 s'étendent à partir de la face externe de la base annulaire 12 dans la direction radiale DR. Les termes "amont" et "aval" sont utilisés ici en référence au sens d'écoulement du flux gazeux dans la turbine (flèche F).Each ring sector 110 has a section substantially in the shape of an inverted π with an annular base 112 whose internal face coated with a layer 113 of abradable material defines the gas flow path in the turbine. Upstream and downstream tabs 114, 116 extend from the external face of the annular base 12 in the radial direction D R. The terms "upstream" and "downstream" are used here in reference to the direction of flow of the gas flow in the turbine (arrow F).

La structure de support d'anneau 103 est formée de deux parties, à savoir une première partie correspondant à une bride radiale amont annulaire 132 qui est de préférence formée intégralement avec un carter de turbine 130 et une deuxième partie correspondant à un flasque annulaire de rétention 150 monté sur le carter de turbine 130. La bride radiale amont annulaire 132 comporte une saillie 134 sur sa face en regard des pattes amont 114 des secteurs d'anneau 110, la saillie 134 est logée dans une rainure annulaire 1140 présente sur la face externe 114a des pattes amont 114. Du côté aval, le flasque 150 comporte un voile annulaire 157 qui forme une bride radiale aval annulaire 154 comportant une saillie 155 sur sa face en regard des pattes aval 116 des secteurs d'anneau 110, la saillie étant logée dans une rainure annulaire 160 présente sur la face externe 116a des pattes aval 116. Le flasque 150 comprend un corps annulaire 151 s'étendant axialement et comprenant, du côté amont, le voile annulaire 157 et, du côté aval, une première série de dents 152 réparties de manière circonférentielle sur le flasque 150 et espacées les unes des autres par des premiers passages d'engagement 153 (figures 9 et 12). Le carter de turbine 130 comporte du côté aval une deuxième série de dents 135 s'étendant radialement depuis la surface interne de la virole 138 du carter de turbine 130. Les dents 135 sont réparties de manière circonférentielle sur la surface interne 138a de la virole 138 et espacées les unes des autres par des deuxièmes passages d'engagement 136 (figure 9). Les dents 152 et 135 coopèrent entre elles pour former un crabotage circonférentiel.The ring support structure 103 is formed of two parts, namely a first part corresponding to an annular upstream radial flange 132 which is preferably formed integrally with a turbine casing 130 and a second part corresponding to an annular retention flange 150 mounted on the turbine casing 130. The annular upstream radial flange 132 has a projection 134 on its face facing the upstream lugs 114 of the ring sectors 110, the projection 134 is housed in an annular groove 1140 present on the external face 114a of the upstream tabs 114. On the downstream side, the flange 150 comprises an annular web 157 which forms an annular downstream radial flange 154 comprising a projection 155 on its face facing the downstream tabs 116 of the ring sectors 110, the projection being housed in an annular groove 160 present on the external face 116a of the downstream tabs 116. The flange 150 comprises an annular body 151 extending axially and comprising, on the upstream side, the annular web 157 and, on the downstream side, a first series of teeth 152 distributed circumferentially on the flange 150 and spaced from each other by first engagement passages 153 ( figures 9 And 12 ). The turbine casing 130 comprises on the downstream side a second series of teeth 135 extending radially from the internal surface of the shroud 138 of the turbine casing 130. The teeth 135 are distributed circumferentially on the internal surface 138a of the ferrule 138 and spaced from each other by second engagement passages 136 ( Figure 9 ). The teeth 152 and 135 cooperate with each other to form a circumferential clutch.

Comme expliqué ci-après en détails, les pattes 114 et 116 de chaque secteur d'anneau 110 sont montées en précontrainte entre les brides annulaires 132 et 154 de manière à ce que les brides exercent, au moins à « froid », c'est-à-dire à une température ambiante d'environ 25°C, une contrainte sur les pattes 114 et 116.As explained below in detail, the tabs 114 and 116 of each ring sector 110 are mounted in pre-tension between the annular flanges 132 and 154 so that the flanges exert, at least "cold", this is that is to say at an ambient temperature of approximately 25°C, a stress on the legs 114 and 116.

Par ailleurs, dans l'exemple décrit ici, les secteurs d'anneau 110 sont en outre maintenus par des pions de blocage. Plus précisément et comme illustrés sur la figure 6, des pions 140 sont engagés à la fois dans la bride radiale amont annulaire 132 de la structure de support d'anneau 103 et dans les pattes amont 114 des secteurs d'anneau 110. A cet effet, les pions 140 traversent chacun respectivement un orifice 133 ménagé dans la bride radiale amont annulaire 132 et un orifice 115 ménagé dans chaque patte amont 114, les orifices 133 et 115 étant alignés lors du montage des secteurs d'anneau 110 sur la structure de support d'anneau 103. De même, des pions 141 sont engagés à la fois dans la bride radiale aval annulaire 154 du flasque 150 et dans les pattes aval 116 des secteurs d'anneau 110. A cet effet, les pions 141 traversent chacun respectivement un orifice 156 ménagé dans la bride radiale aval annulaire 154 et un orifice 117 ménagé chaque patte aval 116, les orifices 156 et 117 étant alignés lors du montage des secteurs d'anneau 110 sur la structure de support d'anneau 103.Furthermore, in the example described here, the ring sectors 110 are also held by blocking pins. More precisely and as illustrated on the Figure 6 , pins 140 are engaged both in the annular upstream radial flange 132 of the ring support structure 103 and in the upstream lugs 114 of the ring sectors 110. For this purpose, the pins 140 each pass through an orifice respectively 133 provided in the annular upstream radial flange 132 and an orifice 115 provided in each upstream lug 114, the orifices 133 and 115 being aligned during the assembly of the ring sectors 110 on the ring support structure 103. Likewise, pins 141 are engaged both in the annular downstream radial flange 154 of the flange 150 and in the downstream lugs 116 of the ring sectors 110. For this purpose, the pins 141 each pass through an orifice 156 provided in the annular downstream radial flange 154 and an orifice 117 provided in each downstream tab 116, the orifices 156 and 117 being aligned during the assembly of the ring sectors 110 on the ring support structure 103.

En outre, l'étanchéité inter-secteurs est assurée par des languettes d'étanchéité logées dans des rainures se faisant face dans les bords en regard de deux secteurs d'anneau voisin. Une languette 122a s'étend sur presque toute la longueur de la base annulaire 112 dans la partie médiane de celle-ci. Une autre languette 122b s'étend le long de la patte 114 et sur une partie de la base annulaire 112. Une autre languette 122c s'étend le long de la patte 116. A une extrémité, la languette 122c vient en butée sur la languette 122a et sur la languette 122b. Les languettes 122a, 122b, 122c sont par exemple métalliques et sont montées avec jeu à froid dans leurs logements afin d'assurer la fonction d'étanchéité aux températures rencontrées en service.In addition, inter-sector sealing is ensured by sealing tabs housed in facing grooves in the facing edges of two neighboring ring sectors. A tongue 122a extends over almost the entire length of the annular base 112 in the middle part thereof. Another tab 122b extends along the tab 114 and over part of the annular base 112. Another tab 122c extends along the tab 116. At one end, the tab 122c abuts the tab 122a and on the tab 122b. The tabs 122a, 122b, 122c are for example metallic and are mounted with cold clearance in their housings in order to ensure the sealing function at the temperatures encountered in service.

De façon classique, des orifices de ventilation 132a formés dans la bride 132 permettent d'amener de l'air de refroidissement du côté extérieur de l'anneau de turbine 110.Conventionally, ventilation holes 132a formed in the flange 132 make it possible to bring cooling air to the exterior side of the turbine ring 110.

En outre, l'étanchéité entre l'amont et l'aval de l'ensemble d'anneau de turbine est assurée par un bossage annulaire 131 s'étendant radialement depuis la surface interne 138a de la virole 138 du carter de turbine 103 et dont l'extrémité libre est en contact avec la surface du corps 151 du flasque 150.In addition, the seal between the upstream and downstream of the turbine ring assembly is ensured by an annular boss 131 extending radially from the internal surface 138a of the shroud 138 of the turbine casing 103 and of which the free end is in contact with the surface of the body 151 of the flange 150.

Conformément à la présente invention, au moins un élément élastique est interposé entre chaque saillie des brides annulaires de la structure de support d'anneau et chaque rainure annulaire des pattes des secteurs d'anneau. Plus précisément, dans le mode de réalisation décrit ici, une tôle ondulée annulaire fendue 170 est interposée entre la paroi supérieure 1142 de la rainure 1140 présente sur la face externe 114a des pattes amont 114 des secteurs d'anneau 110 et la face supérieure 134c de la saillie 134 de la bride radiale amont annulaire 132 tandis qu'une tôle ondulée annulaire fendue 180 est interposée entre la paroi supérieure 1162 de la rainure 1160 présente sur la face externe 116a des pattes aval 116 des secteurs d'anneau 110 et la face supérieure 155c de la saillie 155 de la bride radiale aval annulaire 154. Les tôles ondulées annulaires 170 et 180 constituent des éléments élastiques. Elles peuvent être notamment réalisées en matériau métallique tel qu'un alliage René 41™ ou en | matériau composite tel qu'un matériau de type A500 constitué d'un renfort en fibres de carbone densifié par une matrice autocicatrisante SiC/B. Les tôles ondulées 170 et 180 sont alternativement en contact avec les rainures annulaires 1140 et 1160 et les saillies 134 et 155. Les tôles ondulées 170 et 180 assurent ainsi un maintien en position des secteurs d'anneau 110 sur la structure de support d'anneau 103. Plus précisément, les tôles ondulées 170 et 180 assurent un maintien élastique des secteurs d'anneau 110 dans la direction radiale DR par des points de contact alternés, d'une part, entre la paroi supérieure 1142 de la rainure 1140 de la patte amont 114 et la face supérieure 134c de la saillie 134 de la bride radiale amont annulaire 132 (pour la tôle 170), et, d'autre part, entre la paroi supérieure 1162 de la rainure 1160 de la patte amont 116 et la face supérieure 155c de la saillie 155 de la bride radiale aval annulaire 154 (pour la tôle 180). On décrit maintenant un procédé de réalisation d'un ensemble d'anneau de turbine correspondant à celui représenté sur la figure 6. Chaque secteur d'anneau 110 décrit ci-avant est réalisé en matériau composite à matrice céramique (CMC) par formation d'une préforme fibreuse ayant une forme voisine de celle du secteur d'anneau et densification du secteur d'anneau par une matrice céramique.According to the present invention, at least one elastic element is interposed between each projection of the annular flanges of the ring support structure and each annular groove of the tabs of the ring sectors. More precisely, in the embodiment described here, a split annular corrugated sheet 170 is interposed between the upper wall 1142 of the groove 1140 present on the external face 114a of the upstream lugs 114 of the ring sectors 110 and the upper face 134c of the projection 134 of the annular upstream radial flange 132 while a split annular corrugated sheet 180 is interposed between the upper wall 1162 of the groove 1160 present on the external face 116a of the downstream lugs 116 of the ring sectors 110 and the upper face 155c of the projection 155 of the annular downstream radial flange 154. The annular corrugated sheets 170 and 180 constitute elastic elements. They can in particular be made of metallic material such as a René 41 ™ alloy or | composite material such as an A500 type material consisting of carbon fiber reinforcement densified by a self-healing SiC/B matrix. The corrugated sheets 170 and 180 are alternately in contact with the annular grooves 1140 and 1160 and the projections 134 and 155. The corrugated sheets 170 and 180 thus ensure that the ring sectors 110 are maintained in position on the ring support structure. 103. More precisely, the corrugated sheets 170 and 180 ensure elastic retention of the ring sectors 110 in the radial direction DR by alternating contact points, on the one hand, between the upper wall 1142 of the groove 1140 of the tab upstream 114 and the upper face 134c of the projection 134 of the annular upstream radial flange 132 (for the sheet 170), and, on the other hand, between the upper wall 1162 of the groove 1160 of the upstream tab 116 and the upper face 155c of the projection 155 of the annular downstream radial flange 154 (for the sheet 180). We now describe a method for producing a turbine ring assembly corresponding to that shown on the Figure 6 . Each ring sector 110 described above is made of ceramic matrix composite material (CMC) by formation of a fibrous preform having a shape close to that of the ring sector and densification of the ring sector by a ceramic matrix .

Pour la réalisation de la préforme fibreuse, on peut utiliser des fils en fibres céramique, par exemple des fils en fibres SiC tels que ceux commercialisés par la société japonaise Nippon Carbon sous la dénomination "Nicalon™", ou des fils en fibres de carbone. 1To produce the fibrous preform, ceramic fiber yarns can be used, for example SiC fiber yarns such as those marketed by the Japanese company Nippon Carbon under the name "Nicalon ™ ", or carbon fiber yarns. 1

La préforme fibreuse est avantageusement réalisée par tissage tridimensionnel, ou tissage multicouches avec aménagement de zones de déliaison permettant d'écarter les parties de préformes correspondant aux pattes 114 et 116 des secteurs 110.The fibrous preform is advantageously produced by three-dimensional weaving, or multilayer weaving with the provision of unbinding zones making it possible to separate the parts of preforms corresponding to the tabs 114 and 116 of the sectors 110.

Le tissage peut être de type interlock, comme illustré. D'autres armures de tissage tridimensionnel ou multicouches peuvent être utilisées comme par exemple des armures multi-toile ou multi-satin. On pourra se référer au document WO 2006/136755 .The weave can be interlock type, as shown. Other three-dimensional or multi-layer weave weaves can be used, for example multi-canvas or multi-satin weaves. We can refer to the document WO 2006/136755 .

Après tissage, l'ébauche peut être mise en forme pour obtenir une préforme de secteur d'anneau qui est consolidée et densifiée par une matrice céramique, la densification pouvant être réalisée notamment par infiltration chimique en phase gazeuse (CVI) qui est bien connue en soi.After weaving, 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 infiltration in the gas phase (CVI) which is well known in self.

Un exemple détaillé de fabrication de secteurs d'anneau en CMC est notamment décrit dans le document US 2012/0027572 .A detailed example of manufacturing CMC ring sectors is described in particular in the document US 2012/0027572 .

La structure de support d'anneau 103 est quant à elle réalisée en un matériau métallique tel qu'un alliage Waspaloy® ou inconel 718.The ring support structure 103 is made of a metallic material such as a Waspaloy ® or Inconel 718 alloy.

La réalisation de l'ensemble d'anneau de turbine se poursuit par le montage des secteurs d'anneau 110 sur la structure de support d'anneau 103. Comme illustré sur les figures 7 et 8, les secteurs d'anneau 110 sont d'abord fixés par leur patte amont 114 à la bride radiale amont annulaire 132 de la structure de support d'anneau 103 par des pions 140 qui sont engagés dans les orifices alignés 133 et 115 ménagés respectivement dans la bride radiale amont annulaire 132 et dans la patte amont 114, la tôle ondulée annulaire 170 ayant été préalablement placée contre la face supérieure 134c de la saillie 134 de la bride radiale amont annulaire 132. La saillie 134 présente sur la bride 132 est engagée dans les rainures 1140 présentes sur les pattes 114.The production of the turbine ring assembly continues by mounting the ring sectors 110 on the ring support structure 103. As illustrated in the figures 7 and 8 , the ring sectors 110 are first fixed by their upstream tab 114 to the annular upstream radial flange 132 of the ring support structure 103 by pins 140 which are engaged in the aligned orifices 133 and 115 provided respectively in the annular upstream radial flange 132 and in the upstream tab 114, the annular corrugated sheet 170 having been previously placed against the upper face 134c of the projection 134 of the annular upstream radial flange 132. The projection 134 present on the flange 132 is engaged in the grooves 1140 present on the legs 114.

Une fois tous les secteurs d'anneau 110 ainsi fixés à la bride radiale amont annulaire 132, on procède à l'assemblage par crabotage du flasque annulaire de rétention 150 entre le carter de turbine 103 et les pattes aval 116 des secteurs d'anneau 110. Conformément au mode de réalisation décrit ici, l'écartement E entre la bride radiale amont annulaire 154 formée par le voile annulaire 157 du flasque 150 et la surface externe 152a des dents 152 dudit flasque est supérieur à la distance D présente entre le fond 1161 des rainures 1160 des pattes aval 116 des secteurs d'anneau et la face interne 135b des dents 135 présentes sur le carter de turbine 130 (figure 8).Once all the ring sectors 110 are thus fixed to the annular upstream radial flange 132, we proceed to the assembly by interconnection of the annular retention flange 150 between the turbine casing 103 and the downstream lugs 116 of the ring sectors 110 In accordance with the embodiment described here, the spacing E between the annular upstream radial flange 154 formed by the annular web 157 of the flange 150 and the external surface 152a of the teeth 152 of said flange is greater than the distance D present between the bottom 1161 grooves 1160 of the downstream tabs 116 of the ring sectors and the internal face 135b of the teeth 135 present on the turbine casing 130 ( figure 8 ).

En définissant un écartement E entre la bride radiale amont annulaire et la surface externe des dents du flasque supérieur à la distance D entre le fond des rainures des pattes aval des secteurs d'anneau et la face interne des dents présentes sur le carter de turbine, il est possible de monter les secteurs d'anneau en précontrainte entre les brides de la structure de support d'anneau. Toutefois, afin de ne pas endommager les pattes des secteurs d'anneau en CMC lors du montage et conformément à l'invention, la structure de support d'anneau comprend au moins une bride annulaire qui est élastiquement déformable dans la direction axiale DA de l'anneau. Dans l'exemple décrit ici, c'est la bride radiale aval annulaire 154 présente sur le flasque 150 qui est élastiquement déformable. En effet, le voile annulaire 157 formant la bride radiale aval annulaire 154 de la structure de support d'anneau 103 présente une épaisseur réduite par rapport à la bride radiale amont annulaire 132, ce qui lui confère une certaine élasticité.By defining a spacing E between the annular upstream radial flange and the external surface of the teeth of the flange greater than the distance D between the bottom of the grooves of the downstream lugs of the ring sectors and the internal face of the teeth present on the turbine casing, it is possible to mount the ring sectors prestressed between the flanges of the ring support structure. However, in order not to damage the tabs of the CMC ring sectors during assembly and in accordance with the invention, the ring support structure comprises at least one annular flange which is elastically deformable in the axial direction D A of the ring. In the example described here, it is the annular downstream radial flange 154 present on the flange 150 which is elastically deformable. Indeed, the annular web 157 forming the annular downstream radial flange 154 of the ring support structure 103 has a reduced thickness compared to the annular upstream radial flange 132, which gives it a certain elasticity.

Comme illustré sur les figures 9, 10 et 11, le flasque 150 est monté sur le carter de turbine 130 en plaçant la tôle ondulée annulaire 180 contre la face supérieure 155c de la saillie 155 de la bride radiale amont annulaire 154 du flasque 150 et en engageant les saillies 155 dans les rainures 1160 présentes sur les pattes aval 116. Afin de fixer le flasque 150 par crabotage, les dents 152 présentes sur le flasque 150 sont tout d'abord positionnées en vis-à-vis des passages d'engagement 136 ménagés sur le carter de turbine 130, les dents 135 présentes sur ledit carter de turbine étant également placées en vis-à-vis des passages d'engagement 153 ménagés entre les dents 152 sur le flasque 150. L'écartement E étant supérieur à la distance D, il est nécessaire d'appliquer un effort axial FA sur le flasque 150 dans la direction indiquée sur la figure 10 afin d'engager les dents 152 au-delà des dents 135 et permettre une rotation R du flasque suivant un angle correspondant sensiblement à la largeur des dents 135 et 152. Après cette rotation, le flasque 150 est relâché, ce dernier étant alors maintenu en contrainte axiale entre les pattes amont 116 des secteurs d'anneau 110 et la surface interne 135b des dents 135 du carter de turbine 130.As illustrated on the figures 9 , 10 And 11 , the flange 150 is mounted on the turbine casing 130 by placing the annular corrugated sheet 180 against the upper face 155c of the projection 155 of the annular upstream radial flange 154 of the flange 150 and by engaging the projections 155 in the grooves 1160 present on the downstream tabs 116. In order to fix the flange 150 by interconnection, the teeth 152 present on the flange 150 are first positioned opposite the engagement passages 136 provided on the turbine casing 130, the teeth 135 present on said turbine casing also being placed opposite the engagement passages 153 provided between the teeth 152 on the flange 150. The spacing E being greater than the distance D, it is necessary to apply an axial force F A on the flange 150 in the direction indicated on the Figure 10 in order to engage the teeth 152 beyond the teeth 135 and allow rotation R of the flange at an angle corresponding substantially to the width of the teeth 135 and 152. After this rotation, the flange 150 is released, the latter then being held in position. axial stress between the upstream tabs 116 of the ring sectors 110 and the internal surface 135b of the teeth 135 of the turbine casing 130.

Une fois le flasque ainsi mis en place, des pions 141 sont engagés dans les orifices alignés 156 et 117 ménagés respectivement dans la bride radiale aval annulaire 154 et dans la patte aval 116. Chaque patte 114 ou 116 de secteur d'anneau peut comporter un ou plusieurs orifice pour le passage d'un pion de blocage.Once the flange is thus in place, pins 141 are engaged in the aligned orifices 156 and 117 provided respectively in the downstream annular radial flange 154 and in the downstream tab 116. Each tab 114 or 116 of the ring sector can include a or several holes for the passage of a blocking pin.

Dans une variante de réalisation, les tôles ondulées 170 et 180 peuvent être placés entre la paroi inférieure des rainures des pattes des secteurs d'anneau et la face inférieure des saillie des brides radiales annulaires. Dans ce cas, les tôles ondulées 170 et 180 assurent un maintien élastique des secteurs d'anneau 110 dans la direction radiale DR par des points de contact alternés, d'une part, entre la paroi inférieure 1143 de la rainure 1140 de la patte amont 114 et la face inférieure 134b de la saillie 134 de la bride radiale amont annulaire 132 (pour la tôle 170), et, d'autre part, entre la paroi inférieure 1163 de la rainure 1160 de la patte amont 116 et la face inférieure 155b de la saillie 155 de la bride radiale aval annulaire 154 (pour la tôle 180).In a variant embodiment, the corrugated sheets 170 and 180 can be placed between the lower wall of the grooves of the tabs of the ring sectors and the lower face of the projections of the annular radial flanges. In this case, the corrugated sheets 170 and 180 ensure elastic retention of the ring sectors 110 in the radial direction D R by alternating contact points, on the one hand, between the lower wall 1143 of the groove 1140 of the tab upstream 114 and the lower face 134b of the projection 134 of the annular upstream radial flange 132 (for the sheet 170), and, on the other hand, between the lower wall 1163 of the groove 1160 of the upstream tab 116 and the lower face 155b of the projection 155 of the annular downstream radial flange 154 (for the sheet 180).

Claims (8)

  1. A turbine ring assembly comprising both a plurality of ring sectors (10) made of ceramic matrix composite material forming a turbine ring (1) and also a ring support structure (3) having first and second annular flanges (32, 36), each ring sector (10) having a portion (12) forming an annular base with an inner face defining the inside face of the turbine ring (1) and an outer face from which first and second tabs (14, 16) extend radially, the tabs (14, 16) of each ring sector (10) being held between the two annular flanges (32, 36) of the ring support structure (3), the first and second tabs (14, 16) of the ring sectors (10) each having an annular groove (140; 160) in its face (14a; 16a) respectively facing the first annular flange (32) and the second annular flange (36) of the ring support structure (3), the first and second annular flanges (32, 36) of the ring support structure (3) each having an annular projection (34; 38) on its face facing one of the ring sector tabs, the annular projection (34) of the first flange (32) being received in the annular groove (140) of the first tab (14) of each ring sector (10), while the annular projection (38) of the second flange (36) is received in the annular groove (160) of the second tab (16) of each ring sector (10), at least one resilient element being interposed between the annular projection (34) of the first flange (32) and the annular grooves (140) of the first tabs (14), and also between the annular projection (38) of the second flange (36) and the annular grooves (160) of the second tabs (16);
    the assembly being characterized in that each resilient element is interposed between the top walls (142) of the grooves (140) present in the first tabs (14), or respectively the second tabs (16), of the ring sectors (10) and the top wall (34c) of the annular projection (34) of the first flange (32), or respectively of the second flange (36), of the ring structure (3); or else
    in that each resilient element is interposed between the bottom walls (143) of the grooves (140) present in the first tabs (14), or respectively the second tabs (16) of the ring sectors (10) and the bottom wall (34b) of the annular projection (34) of the first flange (32), or respectively of the second flange (36), of the ring structure (3),
    and in that each resilient element serves to hold the ring sectors (10) in position on the ring support structure (3) in a radial direction (DR) of the turbine ring.
  2. An assembly according to claim 1, characterized in that each resilient element is formed by a split annular collar (60; 70) mounted with elastic prestress between one of the annular projections (34; 38) and the corresponding grooves (140; 160).
  3. An assembly according to claim 1, characterized in that each resilient element is formed by at least one strip (170; 180) of a rigid material presenting a corrugated shape.
  4. An assembly according to any one of claims 1 to 3, characterized in that the projections of the two annular flanges (32, 36) of the ring support structure (3) exert stress on the annular grooves (140, 160) of the tabs (14, 16) of the ring sectors (10), and in that one of the flanges (36) of the ring support structure (3) is elastically deformable in the axial direction (DA) of the turbine ring (1).
  5. A turbine ring assembly according to claim 4, characterized in that the elastically deformable flange (36) of the ring support structure (3) presents thickness that is less than the thickness of the other flange (32) of the ring support structure (3).
  6. A turbine ring assembly according to claim 4 or claim 5, characterized in that the elastically deformable flange (36) of the ring support structure (3) has a plurality of hooks (39) distributed over its face (36a) opposite from its face (36b) facing the tabs (16) of the ring sectors (10).
  7. An assembly according to any one of claims 1 to 3, characterized in that the ring support structure includes an annular retention band (150) mounted on the turbine casing (130), the annular retention band (150) including an annular web (157) forming one of the flanges (154) of the ring support structure (103), and in that the band (150) has a first series of teeth (152) distributed in circumferential manner on said band while the turbine casing (130) has a second series of teeth (135) distributed in circumferential manner on said casing, the teeth (152) of the first series of teeth and the teeth (135) of the second series of teeth together forming a circumferential twist-lock jaw coupling.
  8. An assembly according to claim 7, characterized in that the turbine casing (130) includes an annular projection (131) extending between a shroud (138) of said casing and the band (150) of the ring structure (103).
EP16729311.7A 2015-05-22 2016-05-19 Turbine ring assembly supported by flanges Active EP3298247B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1554627A FR3036436B1 (en) 2015-05-22 2015-05-22 TURBINE RING ASSEMBLY WITH HOLDING BY FLANGES
PCT/FR2016/051175 WO2016189224A1 (en) 2015-05-22 2016-05-19 Turbine ring assembly supported by flanges

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EP3298247A1 EP3298247A1 (en) 2018-03-28
EP3298247B1 true EP3298247B1 (en) 2023-10-25

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EP (1) EP3298247B1 (en)
JP (1) JP6760969B2 (en)
CN (1) CN107735549B (en)
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CA (1) CA2986663C (en)
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Publication number Publication date
CN107735549B (en) 2020-11-06
RU2720876C2 (en) 2020-05-13
WO2016189224A1 (en) 2016-12-01
EP3298247A1 (en) 2018-03-28
US10626745B2 (en) 2020-04-21
RU2017144769A (en) 2019-06-24
CN107735549A (en) 2018-02-23
CA2986663C (en) 2023-10-03
JP6760969B2 (en) 2020-09-23
FR3036436A1 (en) 2016-11-25
FR3036436B1 (en) 2020-01-24
BR112017024891A2 (en) 2018-07-31
JP2018520292A (en) 2018-07-26
CA2986663A1 (en) 2016-12-01
BR112017024891B1 (en) 2023-01-24
RU2017144769A3 (en) 2019-10-29
US20180149034A1 (en) 2018-05-31

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