EP3298247B1 - Ensemble d'anneau de turbine avec maintien par brides - Google Patents

Ensemble d'anneau de turbine avec maintien par brides 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
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EP16729311.7A
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German (de)
English (en)
French (fr)
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EP3298247A1 (fr
Inventor
Clément ROUSSILLE
Gaël EVAIN
Aline Planckeel
Claire GROLEAU
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP3298247A1 publication Critical patent/EP3298247A1/fr
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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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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16729311.7A 2015-05-22 2016-05-19 Ensemble d'anneau de turbine avec maintien par brides Active EP3298247B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1554627A FR3036436B1 (fr) 2015-05-22 2015-05-22 Ensemble d'anneau de turbine avec maintien par brides
PCT/FR2016/051175 WO2016189224A1 (fr) 2015-05-22 2016-05-19 Ensemble d'anneau de turbine avec maintien par brides

Publications (2)

Publication Number Publication Date
EP3298247A1 EP3298247A1 (fr) 2018-03-28
EP3298247B1 true EP3298247B1 (fr) 2023-10-25

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US (1) US10626745B2 (ja)
EP (1) EP3298247B1 (ja)
JP (1) JP6760969B2 (ja)
CN (1) CN107735549B (ja)
BR (1) BR112017024891B1 (ja)
CA (1) CA2986663C (ja)
FR (1) FR3036436B1 (ja)
RU (1) RU2720876C2 (ja)
WO (1) WO2016189224A1 (ja)

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RU2017144769A3 (ja) 2019-10-29
JP6760969B2 (ja) 2020-09-23
WO2016189224A1 (fr) 2016-12-01
EP3298247A1 (fr) 2018-03-28
RU2720876C2 (ru) 2020-05-13
RU2017144769A (ru) 2019-06-24
BR112017024891B1 (pt) 2023-01-24
CA2986663A1 (fr) 2016-12-01
FR3036436B1 (fr) 2020-01-24
CN107735549B (zh) 2020-11-06
US10626745B2 (en) 2020-04-21
BR112017024891A2 (pt) 2018-07-31
CN107735549A (zh) 2018-02-23
FR3036436A1 (fr) 2016-11-25
US20180149034A1 (en) 2018-05-31
JP2018520292A (ja) 2018-07-26
CA2986663C (fr) 2023-10-03

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