WO2016189224A1 - Ensemble d'anneau de turbine avec maintien par brides - Google Patents
Ensemble d'anneau de turbine avec maintien par brides Download PDFInfo
- Publication number
- WO2016189224A1 WO2016189224A1 PCT/FR2016/051175 FR2016051175W WO2016189224A1 WO 2016189224 A1 WO2016189224 A1 WO 2016189224A1 FR 2016051175 W FR2016051175 W FR 2016051175W WO 2016189224 A1 WO2016189224 A1 WO 2016189224A1
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- WO
- WIPO (PCT)
- Prior art keywords
- ring
- annular
- flange
- support structure
- turbine
- Prior art date
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
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- 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
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- 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
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- 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 aeronautical gas turbine 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 ring sectors comprise an annular base whose inner face defines the inner face of the turbine ring and an outer face from which extend two leg portions whose ends are engaged in housings of a structure. metal ring support.
- the use of ring segments in CMC significantly reduces the ventilation required to cool the turbine ring.
- maintaining the ring sectors in position remains a problem in particular with respect to the differential expansions that can occur between the metal support structure and the CMC ring sectors.
- another problem lies in the constraints generated by the imposed displacements.
- the position retention of the ring sectors must be ensured even in the event of contact between the top of a blade of a moving wheel and the inner face of the ring sectors.
- the aim of the invention is to avoid such drawbacks and proposes for this purpose a turbine ring assembly comprising a plurality of ring sectors 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 an annular base portion with an inner face defining the inner face of the turbine ring and an outer face from which radially extend first and second legs 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 having an annular groove on its face facing respectively the first flange.
- ring port each comprising an annular projection on its face facing one of the ring sector tabs, the annular projection of the first flange being housed in the annular groove of the first leg of each ring sector; the annular projection of the second flange is housed in the annular groove of the second leg 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 leg and between the annular projection of the second flange and the annular groove of the second leg.
- Each elastic element is interposed between the upper wall of the grooves present on the first leg, respectively on the second leg, 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 bottom wall of the grooves present on the first tab, respectively on the second tab, ring sectors and the lower wall of the annular projection of the first flange, respectively the second flange, of the ring structure.
- each elastic element is formed of a split annular ring mounted elastically preloaded 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 corrugated shape.
- the elastic element can be in this case formed of a corrugated sheet.
- the projections of the two annular flanges of the ring support structure exert a stress on the annular grooves of the legs of the ring sectors, one of the flanges 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 tabs of the CMC ring sectors and the flanges of the structure of the ring structure. metal ring support without significantly increasing the stress exerted "cold" by the flanges on the legs 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 legs ring sectors facing said at least annular flange.
- the pins 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 opposite the legs of the sectors of the invention. ring.
- the presence of the hooks facilitates the spacing of the elastically deformable flange for the insertion of the tabs of the ring sectors between the flanges without having to slide forcibly the tabs between the flanges.
- the ring support structure comprises an annular retention flange mounted on the turbine casing, the annular retention flange comprising an annular flange 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. teeth forming a circumferential clutch.
- the turbine casing comprises an annular boss extending between a shell of the casing and the flange of the ring structure. This prevents upstream-downstream leakage between the housing and the flange.
- FIG. 1 is a radial half-sectional view showing an embodiment of a turbine ring assembly according to the invention
- Figures 2 to 4 show schematically the mounting of a ring sector in the ring support structure of the ring assembly of Figure 1;
- FIG. 5 is a partial view in half section showing an alternative embodiment of the turbine ring assembly of FIG. 1;
- FIG. 6 is a radial half-sectional view showing an embodiment of a turbine ring assembly according to the invention.
- FIG. 7 to 11 schematically show the mounting of a ring sector in the ring support structure of the ring assembly of Figure 6;
- FIG. 12 is a schematic perspective view of the flange of FIGS. 6 and 8 to 11. DETAILED DESCRIPTION OF EMBODIMENTS
- FIG. 1 shows a high pressure turbine ring assembly comprising a turbine ring 1 made of ceramic matrix composite material (CMC) and a metal ring support structure 3.
- the turbine ring 1 surrounds a set of blades 5.
- the turbine ring 1 is formed of a plurality of ring sectors 10, Figure 1 being a radial sectional view along a plane passing between two sectors of contiguous rings.
- the arrow DA indicates the axial direction with respect to the turbine ring 1 while the arrow DR indicates the radial direction with respect to the turbine ring 1.
- Each ring sector 10 has a substantially inverted ⁇ -shaped section with an annular base 12 whose inner face coated with a layer 13 of abradable material defines the flow stream of gas flow in the turbine.
- Upstream and downstream tabs 14, 16 extend from the outer face of the annular base 12 in the radial direction DR.
- the terms "upstream” and “downstream” are used herein with reference to the flow direction 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 having a projection 34 on its face opposite the upstream tabs 14 of the ring sectors 10, the projection 34 being housed in an annular groove 140 has on the outer face 14a of the upstream lugs 14.
- the ring support structure On the downstream side, the ring support structure comprises an annular downstream radial flange 36 having a projection 38 on its face opposite the downstream tabs 16 of the d-shaped sectors. 10, the projection 38 being housed in an annular groove 160 on the outer face 16a of the downstream tabs 16.
- each ring sector 10 is preloaded between the annular flanges 32 and 36 so that the flanges exert, at least at "cold” is at an ambient temperature of about 25 ° C, a stress on the legs 14 and 16.
- the ring sectors 10 are further maintained by blocking pins. More precisely and as illustrated in FIG. 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 respectively pass through an orifice 33 formed in the annular upstream radial flange 32 and an orifice 15 formed in each upstream lug 14, the orifices 33 and 15 being aligned during the assembly of the ring sectors 10 on the support structure Likewise, pins 41 are engaged both in the annular downstream radial flange 36 of the ring support structure 3 and in the downstream legs 16 of the ring sectors 10.
- pins 41 each respectively pass through an orifice 37 formed in the annular downstream radial flange 36 and an orifice 17 formed 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 provided by sealing tabs housed in grooves facing in the opposite edges of two neighboring ring sectors.
- a tongue 22a extends over almost the entire length of the annular base 12 in the middle portion thereof.
- Another tab 22b extends along the tab 14 and on a portion of the annular base 12.
- Another tab 22c extends along the tab 16. At one end, the tab 22c comes abutting on the tongue 22a and on the tongue 22b.
- the tongues 22a, 22b, 22c are for example metallic and are mounted with cold play in their housings to ensure the sealing function at the temperatures encountered in service.
- Ventperes 32a formed in the flange 32 make it possible to supply cooling air to the outside of the turbine ring 10.
- At least one elastic member is interposed between each projection of the annular flanges of the ring support structure and each annular groove of the legs of the ring sectors. More specifically, in the embodiment described here, a split annular ring 60 is interposed between the upper wall 142 of the groove 140 on the outer face 14a of the upstream lugs 14 of the ring sectors 10 and the upper face 34c of the protrusion 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 on the outer face 16a of the downstream tabs 16 of the ring sectors 10 and the upper face 38c of the projection 38 of the annular downstream radial flange 36.
- the annular split rings 60 and 70 constitute elastic elements in that they have in the free state, that is to say before assembly, a radius greater than the radius defined by the upper walls 142 and 162 respectively of the annular grooves 140 and 160.
- the split annular rings 60 and 70 may be made for example alloy René 41.
- an elastic stress is applied e to the rods 60 and 70 to tighten them on themselves and reduce their radius to insert them 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 provide a holding position of the ring sectors 10 on the ring support structure 3.
- the rods 60 and 70 exert a force Fm holding on sectors of ring 10 which is directed in the radial direction DR and which ensures a contact, on the one hand, between the bottom wall 143 of the groove 140 of the upstream leg 14 and the lower face 34b of the projection 34 of the annular upstream radial flange 32, and, secondly, between the bottom 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 forming a fibrous preform having a shape close to that of the ring sector and densification of the ring sector by a ceramic matrix .
- CMC ceramic matrix composite material
- ceramic fiber yarns for example SiC fiber yarns, such as those marketed by the Japanese company Nippon Carbon under the name "Nicalon”, or carbon fiber yarns.
- the fiber preform is advantageously made by three-dimensional weaving, or multilayer weaving with development of debonding zones to separate the preform portions corresponding to the tabs 14 and 16 of the sectors 10.
- the weave can be interlock type, as illustrated.
- Other weaves of three-dimensional weave or multilayer can be used as for example multi-web or multi-satin weaves.
- the blank After weaving, the blank can be shaped to obtain a ring sector preform which is consolidated and densified by a ceramic matrix, the densification can be achieved in particular by chemical vapor infiltration (CVI) which is well known in itself.
- CVI chemical vapor infiltration
- the ring support structure 3 is made of a metallic material such as a Waspaloy® or inconel 718 alloy.
- the realization of the turbine ring assembly is continued by mounting the ring sectors 10 on the ring support structure 3.
- the distance E between the end 34a of the ring ring 3 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", that is to say when no ring sector is mounted between the flanges, is less than the distance D present between funds 141 and 161 annular grooves 140 and 160 respectively upstream and downstream lugs 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 DA of the invention. '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 relative to the annular upstream radial flange 32, which gives it a certain elasticity.
- the split rings 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 DA as shown in Figures 3 and 4 to increase the spacing between the flanges 32 and 36 and allow the insertion of the projections 34 and 38 respectively present on the flanges 32 and 36 in the grooves 140 and 160 present on the legs 14 and 16 without risk of damaging 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 to align the orifices 33 and 15, on the one 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 DA) for holding on the tabs 14 and 16 of the ring sector while the rods 60 and 70 exert a radial stress (direction DR) on the legs 14 and 16 of the sectors.
- DA axial constraint
- DR radial stress
- the annular downstream radial flange 36 it comprises a plurality of hooks 39 distributed on its face 36a, facing which is opposed to the face 36b of the flange 36 opposite the downstream tabs 16 of the ring sectors 10 ( Figure 3).
- the traction in the axial direction DA 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 outer face 36a of the flange 36.
- the number of hooks 39 distributed on the face 36a of the flange 36 is defined as a function of 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 forms and arrangements of means for exerting traction in the axial direction DA on one of the flanges of the ring support structure can of course be considered within the scope of the present invention.
- each lug 14 or 16 ring sector may comprise one or more orifices for the passage of a blocking pin .
- the rods 60 and 70 may be placed between the lower wall of the grooves of the legs of the ring sectors and the lower face of the projection of the annular radial flanges.
- FIG. 5 illustrates this variant 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 bottom 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 holding force Fm which is directed in the radial direction DR and which makes it possible to ensure a contact, on the one hand, between the upper wall 142 of the groove 140 of the upstream lug 14 and the upper face 34c of the projection 34 of the upstream radial annular flange 32.
- Fig. 6 shows a high pressure turbine ring assembly according to another embodiment of the invention.
- the high turbine ring assembly pressure comprises a turbine ring 101 made of ceramic matrix composite material (CMC) and a metal ring support structure 103.
- the turbine ring 101 surrounds a set of rotary blades 105.
- the turbine ring 101 is formed of a plurality of ring sectors 110, FIG. 6 being a radial sectional view along a plane passing between two contiguous ring sectors.
- the arrow DA indicates the axial direction with respect to the turbine ring 101 while the arrow DR indicates the radial direction with respect to the turbine ring 101.
- Each ring sector 110 has a substantially inverted ⁇ -shaped section with an annular base 112 whose inner face coated with a layer 113 of abradable material defines the flow stream of gas flow in the turbine.
- Upstream and downstream tabs 114, 116 extend from the outer face of the annular base 12 in the radial direction DR.
- upstream and downstream are used herein with reference to the flow direction of the gas flow in the turbine (arrow F).
- the ring support structure 103 is formed of two parts, namely a first portion corresponding to an annular upstream radial flange 132 which is preferably formed integrally with a turbine casing 130 and a second portion corresponding to an annular retention flange 150 mounted on the turbine housing 130.
- the annular upstream radial flange 132 has a projection 134 on its face opposite the upstream tabs 114 of the ring sectors 110, the projection 134 is housed in an annular groove 1140 on the outer 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 having a projection 155 on its opposite side of the downstream tabs 116 of the ring sectors 110, the projection being housed in an annular groove 160 has on the outer face 116a of the downstream tabs 116.
- the flange 150 comprises an annular body 151 extending axially and comprising, of the 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 apart from each other by first engagement passages 153 ( Figures 9 and 12).
- the turbine casing 130 has on the downstream side a second series of teeth 135 extending radially from the inner surface of the ferrule 138 of the turbine casing 130.
- the teeth 135 are circumferentially distributed on the inner surface 138a of the shell 138 and spaced apart from each other by second engagement passages 136 (Fig. 9).
- the teeth 152 and 135 cooperate with each other to form a circumferential clutch.
- each ring sector 110 is preloaded between the annular flanges 132 and 154 so that the flanges exert, at least "cold", it is at an ambient temperature of about 25 ° C., a stress on the tabs 114 and 116.
- the ring sectors 110 are further maintained by blocking pins. More precisely and as illustrated in FIG. 6, pins 140 are engaged both in the annular upstream radial flange 132 of the ring support structure 103 and in the upstream tabs 114 of the ring sectors 110.
- the pins 140 each pass respectively through an orifice 133 formed in the annular upstream radial flange 132 and an orifice 115 formed in each upstream lug 114, the orifices 133 and 115 being aligned during the assembly of the ring sectors 110 on the support structure
- pins 141 are engaged both in the annular downstream radial flange 154 of the flange 150 and in the downstream flaps 116 of the ring sectors 110.
- the pins 141 each pass through a respective flange.
- orifice 156 formed in the annular downstream radial flange 154 and an orifice 117 formed each downstream lug 116, the orifices 156 and 117 being aligned during assembly of the ring sectors 110 on the ring support structure 103.
- inter-sector sealing is provided by sealing tabs housed in grooves facing in the opposite edges of two neighboring ring sectors.
- a tongue 122a extends over almost the entire length of the annular base 112 in the middle portion thereof.
- Another tab 122b extends along the tab 114 and on a portion 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 tongue 122b.
- the tabs 122a, 122b, 122c are for example metallic and are mounted with cold play in their housings to ensure the sealing function at the temperatures encountered in service.
- ventilation orifices 132a formed in the flange 132 make it possible to bring cooling air to the outside of the turbine ring 110.
- the seal between the upstream and downstream of the turbine ring assembly is provided by an annular boss 131 extending radially from the inner surface 138a of the shell 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 member is interposed between each projection of the annular flanges of the ring support structure and each annular groove of the legs of the ring sectors. More specifically, in the embodiment described here, a split annular corrugated sheet 170 is interposed between the upper wall 1142 of the groove 1140 on the outer 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 on the outer 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 may in particular be made of metal material such as a René 41 alloy or composite material such as A500 type material consisting of a carbon fiber reinforcement densified by a SiC / B self-healing 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 provide a positional retention of the ring sectors 110 on the ring support structure 103.
- the corrugated sheets 170 and 180 provide an elastic retention of the ring sectors 110 in the radial direction DR by alternating points of contact, 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 lug 116 and the upper face 155c of the projection 155 of the annular downstream radial flange 154 (for the sheet 180).
- Each ring sector 110 described above is made of ceramic matrix composite material (CMC) by forming a fibrous preform having a shape close to that of the ring sector and densification of the ring sector by a ceramic matrix .
- CMC ceramic matrix composite material
- ceramic fiber yarns for example SiC fiber yarns, such as those marketed by the Japanese company Nippon Carbon under the name "Nicalon”, or carbon fiber yarns.
- the fiber preform is advantageously made by three-dimensional weaving, or multilayer weaving with development of debonding zones to separate the preform portions corresponding to the tabs 114 and 116 of the sectors 110.
- the weave can be interlock type, as illustrated.
- Other weaves of three-dimensional weave or multilayer can be used as for example multi-web or multi-satin weaves.
- the blank After weaving, the blank can be shaped to obtain a ring sector preform which is consolidated and densified by a ceramic matrix, the densification can be achieved in particular by chemical vapor infiltration (CVI) which is well known in itself.
- CVI chemical vapor infiltration
- the ring support structure 103 is made of a metallic material such as a Waspaloy® or inconel 718 alloy.
- the realization of the turbine ring assembly is continued by mounting the ring sectors 110 on the ring support structure 103.
- the ring sectors 110 are first fixed by their upstream leg 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 respectively formed in the annular upstream radial flange 132 and in the leg upstream 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 on the flange 132 is engaged in the grooves 1140 present on the tabs 114.
- the annular retaining flange 150 is assembled by interconnection between the turbine casing 103 and the downstream lugs 116 of the ring sectors 110.
- the spacing E between the annular upstream radial flange 154 formed by the annular web 157 of the flange 150 and the outer 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 lugs 116 of the ring sectors and the inner 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 DA of the invention. '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 relative 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 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 vis-à-vis the engagement passages 136 arranged on the turbine casing 130, the teeth 135 present on said turbine casing being also placed opposite the engagement passages 153 formed 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 FA to the flange 150 in the direction shown in Figure 10 to engage the teeth 152 beyond the teeth 135 and allow a 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 maintained in axial stress between the upstream lugs 116 of the ring sectors 110 and the inner surface 135b of the teeth 135 of the turbine casing 130.
- pins 141 are engaged in the aligned orifices 156 and 117 respectively formed in the annular downstream radial flange 154 and in the downstream lug 116.
- Each lug 114 or 116 of the ring sector may comprise a or several ports for the passage of a blocking pin.
- the corrugated sheets 170 and 180 may be placed between the lower wall of the grooves of the legs 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 DR by alternating points of contact, on the one hand, between the lower wall 1143 of the groove 1140 of the upstream leg 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 lug 116 and the lower face 155b the protrusion 155 of the annular downstream radial flange 154 (for the sheet 180).
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US15/575,968 US10626745B2 (en) | 2015-05-22 | 2016-05-19 | Turbine ring assembly supported by flanges |
CN201680033388.2A CN107735549B (zh) | 2015-05-22 | 2016-05-19 | 由法兰支撑的涡轮机环组件 |
RU2017144769A RU2720876C2 (ru) | 2015-05-22 | 2016-05-19 | Кольцевой узел турбины, поддерживаемый фланцами |
EP16729311.7A EP3298247B1 (fr) | 2015-05-22 | 2016-05-19 | Ensemble d'anneau de turbine avec maintien par brides |
JP2017560765A JP6760969B2 (ja) | 2015-05-22 | 2016-05-19 | フランジによって支持されるタービンリングアセンブリ |
BR112017024891-3A BR112017024891B1 (pt) | 2015-05-22 | 2016-05-19 | Conjunto de anel de turbina |
CA2986663A CA2986663C (fr) | 2015-05-22 | 2016-05-19 | Ensemble d'anneau de turbine avec maintien par brides |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1554627 | 2015-05-22 | ||
FR1554627A FR3036436B1 (fr) | 2015-05-22 | 2015-05-22 | Ensemble d'anneau de turbine avec maintien par brides |
Publications (1)
Publication Number | Publication Date |
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WO2016189224A1 true WO2016189224A1 (fr) | 2016-12-01 |
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PCT/FR2016/051175 WO2016189224A1 (fr) | 2015-05-22 | 2016-05-19 | Ensemble d'anneau de turbine avec maintien par brides |
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US (1) | US10626745B2 (fr) |
EP (1) | EP3298247B1 (fr) |
JP (1) | JP6760969B2 (fr) |
CN (1) | CN107735549B (fr) |
BR (1) | BR112017024891B1 (fr) |
CA (1) | CA2986663C (fr) |
FR (1) | FR3036436B1 (fr) |
RU (1) | RU2720876C2 (fr) |
WO (1) | WO2016189224A1 (fr) |
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FR3096726A1 (fr) * | 2019-06-03 | 2020-12-04 | Safran Ceramics | Ensemble pour turbine de turbomachine |
US11441447B2 (en) | 2017-01-12 | 2022-09-13 | Mitsubishi Heavy Industries, Ltd. | Ring-segment surface-side member, ring-segment support-side member, ring segment, stationary-side member unit, and method |
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US11761351B2 (en) * | 2021-05-25 | 2023-09-19 | Rolls-Royce Corporation | Turbine shroud assembly with radially located ceramic matrix composite shroud segments |
US11346251B1 (en) * | 2021-05-25 | 2022-05-31 | Rolls-Royce Corporation | Turbine shroud assembly with radially biased ceramic matrix composite shroud segments |
FR3142504A1 (fr) * | 2022-11-24 | 2024-05-31 | Safran Ceramics | Ensemble de turbine pour une turbomachine |
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US11885225B1 (en) | 2023-01-25 | 2024-01-30 | Rolls-Royce Corporation | Turbine blade track with ceramic matrix composite segments having attachment flange draft angles |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4650394A (en) * | 1984-11-13 | 1987-03-17 | United Technologies Corporation | Coolable seal assembly for a gas turbine engine |
US6302642B1 (en) * | 1999-04-29 | 2001-10-16 | Abb Alstom Power (Schweiz) Ag | Heat shield for a gas turbine |
US6406256B1 (en) * | 1999-08-12 | 2002-06-18 | Alstom | Device and method for the controlled setting of the gap between the stator arrangement and rotor arrangement of a turbomachine |
WO2006136755A2 (fr) | 2005-06-24 | 2006-12-28 | Snecma | Structure fibreuse de renfort pour piece en materiau composite et piece la comportant |
FR2955898A1 (fr) * | 2010-02-02 | 2011-08-05 | Snecma | Etancheite amont d'un anneau en cmc dans une turbine de turbomachine |
US20120027572A1 (en) | 2009-03-09 | 2012-02-02 | Snecma Propulsion Solide, Le Haillan | Turbine ring assembly |
FR3009740A1 (fr) * | 2013-08-13 | 2015-02-20 | Snecma | Amelioration pour le verrouillage de pieces de support d'aubage |
Family Cites Families (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2540939A1 (fr) * | 1983-02-10 | 1984-08-17 | Snecma | Anneau d'etancheite pour un rotor de turbine d'une turbomachine et installation de turbomachine munie de tels anneaux |
US5603510A (en) * | 1991-06-13 | 1997-02-18 | Sanders; William P. | Variable clearance seal assembly |
US5738490A (en) * | 1996-05-20 | 1998-04-14 | Pratt & Whitney Canada, Inc. | Gas turbine engine shroud seals |
US6315519B1 (en) | 1998-09-28 | 2001-11-13 | General Electric Company | Turbine inner shroud and turbine assembly containing such inner shroud |
FR2800797B1 (fr) * | 1999-11-10 | 2001-12-07 | Snecma | Assemblage d'un anneau bordant une turbine a la structure de turbine |
US6368054B1 (en) * | 1999-12-14 | 2002-04-09 | Pratt & Whitney Canada Corp. | Split ring for tip clearance control |
US6547522B2 (en) * | 2001-06-18 | 2003-04-15 | General Electric Company | Spring-backed abradable seal for turbomachinery |
US6572115B1 (en) * | 2001-12-21 | 2003-06-03 | General Electric Company | Actuating seal for a rotary machine and method of retrofitting |
JP2004036443A (ja) * | 2002-07-02 | 2004-02-05 | Ishikawajima Harima Heavy Ind Co Ltd | ガスタービンシュラウド構造 |
ITMI20022418A1 (it) * | 2002-11-15 | 2004-05-16 | Nuovo Pignone Spa | Assieme migliorato di cassa interna a dispositivo di |
US7435049B2 (en) * | 2004-03-30 | 2008-10-14 | General Electric Company | Sealing device and method for turbomachinery |
EP1643172B1 (fr) * | 2004-09-30 | 2008-06-18 | General Electric Company | Dispositif d'étanchéité flexible, système et méthode |
US7229246B2 (en) * | 2004-09-30 | 2007-06-12 | General Electric Company | Compliant seal and system and method thereof |
US7207771B2 (en) * | 2004-10-15 | 2007-04-24 | Pratt & Whitney Canada Corp. | Turbine shroud segment seal |
US7494317B2 (en) * | 2005-06-23 | 2009-02-24 | Siemens Energy, Inc. | Ring seal attachment system |
US8047773B2 (en) * | 2007-08-23 | 2011-11-01 | General Electric Company | Gas turbine shroud support apparatus |
FR2928961B1 (fr) * | 2008-03-19 | 2015-11-13 | Snecma | Distributeur sectorise pour une turbomachine. |
US8113771B2 (en) * | 2009-03-20 | 2012-02-14 | General Electric Company | Spring system designs for active and passive retractable seals |
EP2495399B1 (fr) * | 2011-03-03 | 2016-11-23 | Safran Aero Booster S.A. | Virole externe segmentée apte à compenser un désalignement du rotor par rapport au stator |
US9382813B2 (en) * | 2012-12-04 | 2016-07-05 | General Electric Company | Turbomachine diaphragm ring with packing retainment apparatus |
FR3003301B1 (fr) | 2013-03-14 | 2018-01-05 | Safran Helicopter Engines | Anneau de turbine pour turbomachine |
US9945243B2 (en) * | 2014-10-14 | 2018-04-17 | Rolls-Royce Corporation | Turbine shroud with biased blade track |
-
2015
- 2015-05-22 FR FR1554627A patent/FR3036436B1/fr active Active
-
2016
- 2016-05-19 CA CA2986663A patent/CA2986663C/fr active Active
- 2016-05-19 JP JP2017560765A patent/JP6760969B2/ja active Active
- 2016-05-19 BR BR112017024891-3A patent/BR112017024891B1/pt active IP Right Grant
- 2016-05-19 US US15/575,968 patent/US10626745B2/en active Active
- 2016-05-19 CN CN201680033388.2A patent/CN107735549B/zh active Active
- 2016-05-19 EP EP16729311.7A patent/EP3298247B1/fr active Active
- 2016-05-19 WO PCT/FR2016/051175 patent/WO2016189224A1/fr active Application Filing
- 2016-05-19 RU RU2017144769A patent/RU2720876C2/ru active
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4650394A (en) * | 1984-11-13 | 1987-03-17 | United Technologies Corporation | Coolable seal assembly for a gas turbine engine |
US6302642B1 (en) * | 1999-04-29 | 2001-10-16 | Abb Alstom Power (Schweiz) Ag | Heat shield for a gas turbine |
US6406256B1 (en) * | 1999-08-12 | 2002-06-18 | Alstom | Device and method for the controlled setting of the gap between the stator arrangement and rotor arrangement of a turbomachine |
WO2006136755A2 (fr) | 2005-06-24 | 2006-12-28 | Snecma | Structure fibreuse de renfort pour piece en materiau composite et piece la comportant |
US20120027572A1 (en) | 2009-03-09 | 2012-02-02 | Snecma Propulsion Solide, Le Haillan | Turbine ring assembly |
FR2955898A1 (fr) * | 2010-02-02 | 2011-08-05 | Snecma | Etancheite amont d'un anneau en cmc dans une turbine de turbomachine |
FR3009740A1 (fr) * | 2013-08-13 | 2015-02-20 | Snecma | Amelioration pour le verrouillage de pieces de support d'aubage |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11441447B2 (en) | 2017-01-12 | 2022-09-13 | Mitsubishi Heavy Industries, Ltd. | Ring-segment surface-side member, ring-segment support-side member, ring segment, stationary-side member unit, and method |
FR3068072A1 (fr) * | 2017-06-26 | 2018-12-28 | Safran Aircraft Engines | Ensemble pour la liaison souple entre un carter de turbine et un element annulaire de turbomachine |
FR3096726A1 (fr) * | 2019-06-03 | 2020-12-04 | Safran Ceramics | Ensemble pour turbine de turbomachine |
Also Published As
Publication number | Publication date |
---|---|
CA2986663A1 (fr) | 2016-12-01 |
FR3036436B1 (fr) | 2020-01-24 |
FR3036436A1 (fr) | 2016-11-25 |
JP2018520292A (ja) | 2018-07-26 |
BR112017024891A2 (pt) | 2018-07-31 |
EP3298247A1 (fr) | 2018-03-28 |
JP6760969B2 (ja) | 2020-09-23 |
CA2986663C (fr) | 2023-10-03 |
US20180149034A1 (en) | 2018-05-31 |
RU2720876C2 (ru) | 2020-05-13 |
BR112017024891B1 (pt) | 2023-01-24 |
CN107735549B (zh) | 2020-11-06 |
CN107735549A (zh) | 2018-02-23 |
RU2017144769A (ru) | 2019-06-24 |
RU2017144769A3 (fr) | 2019-10-29 |
EP3298247B1 (fr) | 2023-10-25 |
US10626745B2 (en) | 2020-04-21 |
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