EP3298246B1 - Turbinenringanordnung, die eine unterschiedliche wärmeausdehnung erlaubt - Google Patents

Turbinenringanordnung, die eine unterschiedliche wärmeausdehnung erlaubt Download PDF

Info

Publication number
EP3298246B1
EP3298246B1 EP16726369.8A EP16726369A EP3298246B1 EP 3298246 B1 EP3298246 B1 EP 3298246B1 EP 16726369 A EP16726369 A EP 16726369A EP 3298246 B1 EP3298246 B1 EP 3298246B1
Authority
EP
European Patent Office
Prior art keywords
ring
sectors
support structure
ring sectors
annular
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP16726369.8A
Other languages
English (en)
French (fr)
Other versions
EP3298246A1 (de
Inventor
Clément ROUSSILLE
Gaël EVAIN
Adèle LYPRENDI
Lucien QUENNEHEN
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
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to EP23198187.9A priority Critical patent/EP4273370B1/de
Publication of EP3298246A1 publication Critical patent/EP3298246A1/de
Application granted granted Critical
Publication of EP3298246B1 publication Critical patent/EP3298246B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • 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
    • F01D25/005—Selecting particular materials
    • 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

  • a turbine ring assembly includes a plurality of ceramic matrix composite material ring sectors and a ring support structure.
  • CMC materials have good mechanical properties making them suitable for constituting structural elements and advantageously retain these properties at high temperatures.
  • the use of CMC materials has advantageously made it possible to reduce the cooling flow required during operation and therefore to increase the performance of the turbomachines.
  • the use of CMC materials advantageously makes it possible to reduce the mass of the turbomachines and to reduce the hot expansion effect encountered with the metal parts.
  • the invention proposes, according to a first aspect, a turbine ring assembly according to claim 1.
  • the radial direction corresponds to the direction along a radius of the turbine ring (straight line connecting the center of the turbine ring to its periphery).
  • the axial direction corresponds to the direction along the axis of revolution of the turbine ring as well as to the direction of flow of the gas flow in the vein.
  • At least one of the flanges of the ring support structure is elastically deformable.
  • This advantageously makes it possible to even better compensate for the differential expansions between the attachment parts of the CMC ring sectors and the flanges of the metal ring support structure without significantly increasing the stress exerted "cold" by the flanges on the hooking parts of the ring sectors.
  • the two flanges of the ring support structure are elastically deformable or only one of the two flanges of the ring support structure is elastically deformable.
  • Each of the annular flanges of the ring support structure has a first and a second inclined portions bearing on the attachment parts of the ring sectors, said first and second inclined portions each forming, when observed in meridian section, a non-zero angle with respect to the radial direction and the axial direction.
  • the first inclined portion rests on the upper half of the attachment parts of the ring sectors and the second inclined portion rests on the lower half of the attachment parts of the ring sectors.
  • the upper half of a hooking part of a ring sector corresponds to the portion of said hooking part extending radially between the zone at mid-length of the hooking part and the end of the hooking part located on the side of the ring support structure.
  • the lower half of a hooking part of a ring sector corresponds to the portion of the hooking part extending radially between the zone at mid-length of the hooking part and the end of the hooking part located on the side of the annular base.
  • the ring support structure can have axial portions bearing on the attachment parts of the ring sectors, the axial portions each being able to extend parallel to the axial direction , these axial portions can be formed by the annular flanges or by a plurality of added elements engaged without cold play through the annular flanges.
  • the attachment parts of the ring sectors can be held to the ring support structure at such axial portions.
  • the annular flanges of the ring support structure can grip the hooking parts of the ring sectors over at least half the length of said hooking parts.
  • the annular flanges of the ring support structure can grip the hooking parts of the ring sectors at least at the level of the external radial ends of said hooking parts.
  • the external radial end of a hooking part corresponds to the end of this hooking part located on the side opposite the flow path of the gas flow.
  • the annular flanges of the ring support structure can grip the hooking parts of the ring sectors only at the level of the upper half of said hooking parts.
  • each ring sector can be in the form of tabs extending radially.
  • the external radial ends of the tabs of the ring sectors may not be in contact and the tabs of the ring sectors may define between them an interior ventilation volume for each of the ring sectors.
  • the hooking portion of each of the ring sectors is in the form of a bulb.
  • the ring sectors have a section substantially in the shape of ⁇ or substantially in the shape of ⁇ .
  • the present invention also relates to a turbomachine comprising a turbine ring assembly as described above.
  • the turbine ring assembly may be part of a gas turbine of an aeronautical engine or may alternatively be part of an industrial turbine.
  • upstream and downstream are used here in reference to the direction of flow of the gas flow in the turbine (see arrow F in section figure 1 , For example).
  • FIG. 1 shows a turbine ring sector 1 and a casing 2 made of metallic material constituting ring support structure.
  • the ring support structure 2 is made of a metallic material such as Waspaloy ® alloy or Inconel ® 718 alloy.
  • the set of ring sectors 1 is mounted on the casing 2 so as to form a turbine ring which surrounds a set of rotating blades 3.
  • the arrow F represents the direction of flow of the gas flow in the turbine.
  • the ring sectors 1 are in one piece and made of CMC.
  • the use of a CMC material to produce the ring sectors 1 is advantageous in order to reduce the ventilation requirements of the ring.
  • the ring sectors 1 have, in the example illustrated, a substantially ⁇ -shaped section with an annular base 5 whose radially internal face 6 coated with a layer 7 of abradable material defines the flow path of the gas flow in the turbine.
  • the annular base 5 also has a radially external face 8 from which a hooking portion 9 extends.
  • the hooking portion 9 is in the form of a solid bulb, we do not depart from the scope of the invention when the hooking portion is in the form of a hollow bulb or when the latter is in another form as detailed below. Inter-sector sealing is ensured by sealing tabs (not shown) housed in facing grooves in the facing edges of two neighboring ring sectors.
  • Each ring sector 1 described above is made of 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.
  • 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.
  • the fibrous preform is advantageously produced by three-dimensional weaving, or multilayer weaving. The weaving can be interlock type. Others Three-dimensional or multi-layer weave weaves can be used, for example multi-canvas or multi-satin weaves. For this, we can refer to the document WO 2006/136755 .
  • the blank can be shaped to obtain a ring sector preform which is then 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 itself.
  • CVI gas phase
  • the casing 2 comprises two annular radial flanges 11a and 11b made of metallic material extending radially towards a flow path of the gas flow.
  • the annular flanges 11a and 11b of the casing 2 axially enclose the attachment parts 9 of the ring sectors 1.
  • the hooking parts 9 of the ring sectors 1 are held between the annular flanges 11a and 11b, the hooking parts 9 being housed between the annular flanges 11a and 11b.
  • ventilation holes 34 formed in the flange 11a make it possible to bring cooling air to the exterior side of the turbine ring 1.
  • the annular flanges 11a and 11b each have two inclined portions bearing on the hooking parts 9 of the ring sectors 1 and ensuring their maintenance.
  • the inclined portions of the annular flanges 11a and 11b are in contact with the attachment parts 9 of the ring sectors 1.
  • the upstream annular flange 11a has a first inclined portion 12a as well as a second inclined portion 13a.
  • the flange 11a furthermore has a third portion 15a extending in the radial direction R and located between the first 12a and the second inclined portion 13a.
  • the downstream annular flange 11b also has a first inclined portion 12b as well as a second inclined portion 13b.
  • the flange 11b also has a third portion 15b extending in the radial direction R and located between the first 12b and the second inclined portion 13b.
  • the first inclined portion 12a of the upstream annular flange 11a forms a non-zero angle ⁇ 1 with the radial direction R and forms a non-zero angle ⁇ 2 with the axial direction A.
  • the second inclined portion 13a of the flange upstream annular flange 11a forms a non-zero angle ⁇ 3 with the radial direction R and forms a non-zero angle ⁇ 4 with the axial direction A.
  • first and second inclined portions 12b and 13b of the downstream annular flange 11b The same is true for the first and second inclined portions 12a and 13a of the downstream annular flange 11b .
  • the first and second inclined portions 12a and 13a extend in non-parallel directions (they form a non-zero angle between them). It is the same for the first and second inclined portions 12b and 13b.
  • the inclined portions of the annular flanges 11a and 11b extend forming a non-zero angle with the radial direction R and a non-zero angle with the axial direction A.
  • the inclined portions of the annular flanges 11a and 11b each extend in a straight line.
  • the inclined portions 12a, 12b, 13a and 13b each have an elongated shape.
  • all or part of the inclined portions of the annular flanges 11a and 11b can form an angle of between 30° and 60° with the radial direction.
  • the angle formed between its first inclined portion and the radial direction may or may not be equal to the angle formed between its second inclined portion and the radial direction, when the first and second inclined portions are observed in meridian section.
  • the annular flanges 11a and 11b enclose the attachment parts 9 of the ring sectors over more than half of the length l of said attachment parts 9, in particular over at least 75% of this length.
  • the length l is measured in the radial direction R.
  • the first inclined portions 12a and 12b are, when observed in meridian section, each resting on the upper half M 1 of the attachment parts 9 and the second inclined portions 13a and 13b are, when observed in meridian section, each resting on the lower half M 2 of the hooking parts 9.
  • the upper half M 1 corresponds to the portion of the hooking part 9 extending radially between the zone Z at mid-length of the hooking part 9 and the end E 1 of the hooking part located on the side of the ring support structure 2 (external radial end).
  • the lower half M 2 corresponds to the portion of the hooking part 9 extending radially between the zone Z at mid-length of the hooking part 9 and the end E 2 of the part hooking located on the side of the annular base 5 (internal radial end).
  • the inclined portions of the annular flanges 11a and 11b define two hooks between which the hooking portions 9 of the ring sectors 1 are gripped axially.
  • Each of these hooks has, in the example illustrated, substantially a C shape.
  • each of the annular flanges has an inclined portion bearing on the attachment parts of the ring sectors.
  • the implementation of the inclined portions advantageously makes it possible to compensate for the differences in expansion between the annular flanges 11a and 11b, on the one hand, and the ring sectors 1, on the other hand, and thus to reduce the mechanical stresses to which the ring sectors 1 are subjected during operation.
  • annular flanges flange 11b at the figure 1
  • hook 25 whose function will be detailed below.
  • the retention of the ring sectors 1 to the ring support structure 2 is only ensured by the annular flanges 11a and 11b (no presence of an added element such as a pin through the hooking part 9 of the ring sectors).
  • an added element such as a pin through the hooking part 9 of the ring sectors.
  • the attachment part of the ring sectors 1a is in the form of tabs 9a and 9b extending radially from the external face 8 of the annular base 5.
  • the external radial ends 10a and 10b of the tabs 9a and 9b of the ring sectors 1a are not in contact.
  • the external radial end of a tab of a ring sector corresponds to the end of said tab located on the side opposite to the flow path of the gas flow.
  • the external radial ends 10a and 10b are, in the example illustrated in Figure 3 , spaced along the axial direction A.
  • the legs 9a and 9b of the ring sectors define between them an interior ventilation volume V for each of the ring sectors 1a. It is thus possible to ventilate the ring sectors 1a by sending cooling air towards their annular base 5 through the ventilation orifice 14 defined between the legs 9a and 9b.
  • the ring sectors 1a of the Figure 3 substantially have an open ⁇ shape at its end located on the side of the ring support structure 2.
  • the fibrous preform intended to form the ring sector 1a of the type illustrated in Figure 3 can be produced by three-dimensional weaving, or multilayer weaving with the provision of unbinding zones making it possible to separate the preform parts corresponding to the legs 9a and 9b from the preform part corresponding to the base 5.
  • the preform parts corresponding to the legs can be made by weaving layers of wires crossing the preform part corresponding to the base 5.
  • each of the annular flanges 21a and 21b has a single inclined portion 13a or 13b bearing on the lugs 19a or 19b of the ring sectors 1b and forming a non-zero angle with respect to the radial direction R and in the axial direction A.
  • the axial portions 16a and 16b bear on the lugs 19a and 19b of the ring sectors.
  • the tabs 19a and 19b forming the attachment part of the ring sectors 1b are held to the ring support structure 2 at the level of the axial portions 16a and 16b.
  • the axial portions 16a and 16b formed by the annular flanges block the movement of the ring sectors 1b outwards in the radial direction R.
  • the annular flanges 21a and 21b axially enclose the lugs 19a and 19b of the ring sectors 1b at level of their external radial end 20a and 20b.
  • the inclined portion and the axial portion form for each of the annular flanges 21a and 21b a hook bearing on the lugs 19a and 19b of the ring sectors 1b.
  • the tabs 19a and 19b of the ring sectors 1b are clamped axially between these two hooks formed by the annular flanges 21a and 21b.
  • the ring sectors 1b have a substantially ⁇ -shaped section.
  • the pins 35 each pass through respectively an orifice made in the annular upstream radial flange 31a and an orifice made in each upstream tab 29a, the orifices of the flange 31a and of the tabs 29a being aligned during the assembly of the ring sectors 1c on the ring support structure 2.
  • pins 37 are engaged both in the annular downstream radial flange 31b of the ring support structure 2 and in the downstream tabs 29b of the ring sectors 1c .
  • the pins 37 each pass through respectively an orifice made in the annular downstream radial flange 31b and an orifice made in each downstream tab 29b, the orifices of the flange 31b and of the tabs 29b being aligned during the assembly of the ring sectors 1c on the ring support structure 2.
  • the pins 35 and 37 are engaged without cold play through the flanges 31a and 31b and the tabs 29a and 29b.
  • the pins 35 and 37 make it possible to block the ring sectors 1c from rotating.
  • the pins 35 and 37 block the movement of the ring sectors 1c inwards and outwards in the radial direction R.
  • the annular flanges 31a and 31b each also have a single inclined portion 13a or 13b making it possible to reduce the stress applied to the ring sectors 1c during the expansion of the annular flanges 31a and 31b during operation.
  • each sector of ring 1c has a substantially ⁇ -shaped section with an annular base 5 whose internal face coated with a layer 7 of abradable material defines the flow path of gas flow in the turbine.
  • Upstream and downstream tabs 29a and 29b extend from the external face of the annular base 5 in the radial direction R.
  • the ring support structure 2 is, in this embodiment, formed of two parts, namely a first part corresponding to an annular upstream radial flange 31a which is preferably formed integrally with a turbine casing and a second part corresponding to a annular retention flange 50 mounted on the turbine casing.
  • the annular upstream radial flange 31a comprises an inclined portion 13a as described above resting on the upstream lugs 29a of the ring sectors 1c.
  • the flange 50 comprises an annular web 57 which forms an annular downstream radial flange 54 comprising an inclined portion 13b as described above resting on the downstream lugs 29b of the ring sectors 1c.
  • the flange 50 comprises an annular body 51 extending axially and comprising, on the upstream side, the annular web 57 and, on the downstream side, a first series of teeth 52 distributed circumferentially on the flange 50 and spaced from each other by of the first passages of engagement 53 ( Figure 7 ).
  • the turbine casing comprises on the downstream side a second series of teeth 60 extending radially from the internal surface 38a of the shroud 38 of the turbine casing.
  • the teeth 60 are distributed circumferentially on the internal surface 38a of the ferrule 38 and spaced from each other by second engagement passages 61 ( Figure 13 ).
  • the teeth 52 and 60 cooperate with each other to form a circumferential clutch.
  • each ring sector 1c are mounted in pre-tension between the annular flanges 31a and 54 so that the flanges exert, at least “cold”, that is to say at ambient temperature of approximately 25°C, a stress on the legs 29a and 29b. Furthermore, as in the realization of the figure 5 , the ring sectors 1c are also held by blocking pins 35 and 37.
  • At least one of the flanges of the ring support structure is elastically deformable, which makes it possible to even better compensate for the differential expansions between the tabs of the CMC ring sectors and the flanges of the metal ring support structure without significantly increasing the stress exerted “cold” by the flanges on the lugs of the ring sectors.
  • annular boss 70 extending radially from the internal surface 38a of the shroud 38 of the turbine casing and of which the free end in contact with the surface of the body 51 of the flange 50.
  • THE figures 8 to 10 which will be described illustrate the assembly of the ring sectors in the case of producing the figure 5 .
  • the spacing E between the annular upstream radial flange 31a and the annular downstream radial flange 31b at “rest”, that is to say when no ring sector is mounted between the flanges is less than the distance D present between the external faces 29c and 29d of the upstream and downstream legs 29a and 29b of the ring sectors.
  • the spacing E is measured between the ends of the inclined portions 13a and 13b of the annular flanges 31a and 31b.
  • the ring support structure comprises at least one annular flange which is elastically deformable in the axial direction A of the ring.
  • the annular downstream radial flange 31b is elastically deformable.
  • the annular downstream radial flange 31b is pulled in the axial direction A as shown on the figures 9 And 10 in order to increase the spacing between the flanges 31a and 31b and allow the insertion of the tabs 29a and 29b between the flanges 31a and 31b without risk of damage.
  • the flange 31b is released in order to maintain the ring sector.
  • the latter comprises a plurality of hooks 25 distributed on its face 31c, face which is opposite to the face 31d of the flange 31b facing the downstream lugs 29b of the ring sectors 1c.
  • the traction in the axial direction A of the ring exerted on the elastically deformable flange 31b is here carried out by means of a tool 250 comprising at least one arm 251 whose end comprises a hook 252 which is engaged in the hook 25 present on the external face 31c of the flange 31b.
  • the number of hooks 25 distributed on the face 31c of the flange 31b is defined according to the number of traction points that we wish to have on the flange 31b. This number mainly depends on the elastic nature of the flange. Other shapes and arrangements of means making it possible to exert traction in the axial direction A on one of the flanges of the ring support structure can of course be envisaged.
  • Each ring sector tab 29a or 29b may include one or more orifices for the passage of a blocking pin.
  • the ring sectors 1c are first fixed by their upstream tab 29a to the annular upstream radial flange 31a of the ring support structure 2 by pins 35 which are engaged in the aligned orifices 35b and 35a provided respectively in the annular upstream radial flange 31a and in the upstream tab 29a.
  • the spacing E' between the annular downstream radial flange 54 formed by the annular web 57 of the flange 50 and the external surface 52a of the teeth 52 of said flange is greater than the distance D' present between the external face 29d of the downstream tabs 29b of the ring sectors and the internal face 60a of the teeth 60 present on the turbine casing.
  • the ring support structure comprises at least one annular flange which is elastically deformable in the axial direction A of the ring.
  • it is the annular downstream radial flange 54 present on the flange 50 which is elastically deformable.
  • the annular web 57 forming the annular downstream radial flange 54 of the ring support structure 2 has a reduced thickness compared to the annular upstream radial flange 31a, which gives it a certain elasticity.
  • the flange 50 is mounted on the turbine casing by placing the teeth 52 present on the flange 50 opposite the engagement passages 61 provided on the turbine casing, the teeth 60 present on said turbine casing being also placed opposite the engagement passages 53 provided between the teeth 52 on the flange 50.
  • the spacing E' being greater than the distance D', it is necessary to apply an axial force on the flange 50 in the direction indicated on the Figure 14 in order to engage the teeth 52 beyond the teeth 60 and allow rotation R' of the flange at an angle corresponding substantially to the width of the teeth 60 and 52. After this rotation, the flange 50 is released, the latter then being held in axial stress between the downstream tabs 29b of the ring sectors and the internal surface 60a of the teeth 60 of the turbine casing.
  • each ring sector tab 29a or 29b may include one or more orifices for the passage of a blocking pin.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (8)

  1. Turbinenringanordnung, umfassend mehrere Ringsektoren (1; 1a) aus keramischem Matrixverbundmaterial, die einen Turbinenring und eine Ringträgerstruktur (2) bilden, wobei jeder Ringsektor (1; 1a) einen ringförmigen Basisabschnitt (5) mit einer Innenfläche (6), die die Innenfläche des Turbinenrings definiert, und einer Außenfläche (8), von der sich ein Greifteil (9; 9a; 9b) des Ringsektors in die Ringträgerstruktur erstreckt, aufweist, wobei die Ringträgerstruktur (2) zwei ringförmige Flansche (11a; 11b) umfasst, zwischen denen der Greifteil jedes Ringsektors gehalten wird, wobei jeder der ringförmigen Flansche (11a; 11b) der Ringträgerstruktur (2) einen ersten (12a; 12b) und einen zweiten (13a; 13b) geneigten Abschnitt aufweist, die auf den Greifteilen (9; 9a; 9b) der Ringsektoren (1; 1a) aufliegen und sich in nicht parallelen Richtungen erstrecken, wobei der erste (12a; 12b) und der zweite (13a; 13b) geneigte Abschnitt jeweils im Meridianschnitt betrachtet einen Winkel ungleich null in Bezug auf die Radialrichtung (R) und die Axialrichtung (A) bilden, wobei die Anordnung dadurch gekennzeichnet ist, dass
    der erste geneigte Abschnitt auf der oberen Hälfte (M1) der Greifteile der Ringsektoren aufliegt und dass der zweite geneigte Abschnitt auf der unteren Hälfte (M2) der Greifteile der Ringsektoren aufliegt.
  2. Anordnung nach Anspruch 1, wobei die ringförmigen Flansche (11a; 11b) der Ringträgerstruktur (2) die Greifteile (9) der Ringsektoren (1) über zumindest die Hälfte der Länge ℓ der Greifteile (9) umgreifen.
  3. Anordnung nach Anspruch 1 oder 2, wobei die ringförmigen Flansche (21a; 21b) der Ringträgerstruktur (2) die Greifteile (19a; 19b) der Ringsektoren (1b) zumindest an den radial äußeren Enden (20a; 20b) der Greifteile (19a; 19b) umgreifen.
  4. Anordnung nach einem der Ansprüche 1 bis 3, wobei der Greifteil jedes Ringsektors in der Form von sich radial erstreckenden Schenkeln (9a; 9b; 19a; 19b; 29a; 29b) ist.
  5. Anordnung nach Anspruch 4, wobei die äußeren radialen Enden (10a; 10b; 20a; 20b) der Schenkel der Ringsektoren nicht in Kontakt sind und wobei die Schenkel der Ringsektoren zwischen sich ein inneres Ventilationsvolumen (V) für jeden der Ringsektoren definieren.
  6. Anordnung nach einem der Ansprüche 1 bis 3, wobei der Greifabschnitt von jedem der Ringsektoren in der Form einer Knolle (9) ist.
  7. Anordnung nach einem der Ansprüche 1 bis 6, wobei die Ringsektoren einen Querschnitt aufweisen, der im Wesentlichen in Form von Ω oder im Wesentlichen in Form von π ist.
  8. Turbomaschine, umfassend eine Turbinenringanordnung nach einem der Ansprüche 1 bis 7.
EP16726369.8A 2015-05-22 2016-05-18 Turbinenringanordnung, die eine unterschiedliche wärmeausdehnung erlaubt Active EP3298246B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP23198187.9A EP4273370B1 (de) 2015-05-22 2016-05-18 Turbinenringanordnung zur differentiellen thermischen ausdehnung

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1554626A FR3036435B1 (fr) 2015-05-22 2015-05-22 Ensemble d'anneau de turbine
PCT/FR2016/051168 WO2016189223A1 (fr) 2015-05-22 2016-05-18 Ensemble d'anneau de turbine.

Related Child Applications (2)

Application Number Title Priority Date Filing Date
EP23198187.9A Division EP4273370B1 (de) 2015-05-22 2016-05-18 Turbinenringanordnung zur differentiellen thermischen ausdehnung
EP23198187.9A Division-Into EP4273370B1 (de) 2015-05-22 2016-05-18 Turbinenringanordnung zur differentiellen thermischen ausdehnung

Publications (2)

Publication Number Publication Date
EP3298246A1 EP3298246A1 (de) 2018-03-28
EP3298246B1 true EP3298246B1 (de) 2023-11-22

Family

ID=53879645

Family Applications (2)

Application Number Title Priority Date Filing Date
EP23198187.9A Active EP4273370B1 (de) 2015-05-22 2016-05-18 Turbinenringanordnung zur differentiellen thermischen ausdehnung
EP16726369.8A Active EP3298246B1 (de) 2015-05-22 2016-05-18 Turbinenringanordnung, die eine unterschiedliche wärmeausdehnung erlaubt

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP23198187.9A Active EP4273370B1 (de) 2015-05-22 2016-05-18 Turbinenringanordnung zur differentiellen thermischen ausdehnung

Country Status (8)

Country Link
US (2) US10724401B2 (de)
EP (2) EP4273370B1 (de)
CN (2) CN111188655B (de)
BR (1) BR112017024871B1 (de)
CA (2) CA2986661C (de)
FR (1) FR3036435B1 (de)
RU (1) RU2741192C2 (de)
WO (1) WO2016189223A1 (de)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3033825B1 (fr) * 2015-03-16 2018-09-07 Safran Aircraft Engines Ensemble d'anneau de turbine en materiau composite a matrice ceramique
US10100649B2 (en) * 2015-03-31 2018-10-16 Rolls-Royce North American Technologies Inc. Compliant rail hanger
FR3045715B1 (fr) * 2015-12-18 2018-01-26 Safran Aircraft Engines Ensemble d'anneau de turbine avec maintien a froid et a chaud
FR3049003B1 (fr) * 2016-03-21 2018-04-06 Safran Aircraft Engines Ensemble d'anneau de turbine sans jeu de montage a froid
FR3055147B1 (fr) * 2016-08-19 2020-05-29 Safran Aircraft Engines Ensemble d'anneau de turbine
FR3056632B1 (fr) * 2016-09-27 2020-06-05 Safran Aircraft Engines Ensemble d'anneau turbine comprenant un element de repartition de l'air de refroidissement
US10697314B2 (en) 2016-10-14 2020-06-30 Rolls-Royce Corporation Turbine shroud with I-beam construction
FR3058756B1 (fr) * 2016-11-15 2020-10-16 Safran Aircraft Engines Turbine pour turbomachine
FR3068071B1 (fr) * 2017-06-26 2019-11-08 Safran Aircraft Engines Ensemble pour la liaison par palonnier entre un carter de turbine et un element annulaire de turbomachine
US10557365B2 (en) 2017-10-05 2020-02-11 Rolls-Royce Corporation Ceramic matrix composite blade track with mounting system having reaction load distribution features
US11035243B2 (en) * 2018-06-01 2021-06-15 Raytheon Technologies Corporation Seal assembly for gas turbine engines
US11008894B2 (en) 2018-10-31 2021-05-18 Raytheon Technologies Corporation BOAS spring clip
US10934877B2 (en) * 2018-10-31 2021-03-02 Raytheon Technologies Corporation CMC laminate pocket BOAS with axial attachment scheme
FR3090732B1 (fr) * 2018-12-19 2021-01-08 Safran Aircraft Engines Ensemble d’anneau de turbine avec flasques indexés.
FR3093344B1 (fr) * 2019-03-01 2021-06-04 Safran Ceram Ensemble pour une turbine de turbomachine
US11761343B2 (en) * 2019-03-13 2023-09-19 Rtx Corporation BOAS carrier with dovetail attachments
US11015485B2 (en) 2019-04-17 2021-05-25 Rolls-Royce Corporation Seal ring for turbine shroud in gas turbine engine with arch-style support
US11021987B2 (en) * 2019-05-15 2021-06-01 Raytheon Technologies Corporation CMC BOAS arrangement
US11149563B2 (en) 2019-10-04 2021-10-19 Rolls-Royce Corporation Ceramic matrix composite blade track with mounting system having axial reaction load distribution features
US11174795B2 (en) * 2019-11-26 2021-11-16 Raytheon Technologies Corporation Seal assembly with secondary retention feature
US11230937B2 (en) * 2020-05-18 2022-01-25 Rolls-Royce North American Technologies Inc. Turbine shroud assembly with dovetail retention system
CN113882910B (zh) * 2020-07-03 2024-07-12 中国航发商用航空发动机有限责任公司 涡轮外环连接组件、燃气涡轮发动机以及连接方法
FR3127981B1 (fr) * 2021-10-08 2025-07-11 Safran Aircraft Engines Virole annulaire de turbine
US11885225B1 (en) * 2023-01-25 2024-01-30 Rolls-Royce Corporation Turbine blade track with ceramic matrix composite segments having attachment flange draft angles
US12286906B1 (en) * 2023-12-04 2025-04-29 Rolls-Royce Corporation Locating plate for use with turbine shroud assemblies

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3501246A (en) * 1967-12-29 1970-03-17 Westinghouse Electric Corp Axial fluid-flow machine
FR2637650B1 (fr) * 1988-10-06 1990-11-16 Alsthom Gec Dispositifs reduisant les fleches et les contraintes dans les diaphragmes de turbines
US5961278A (en) * 1997-12-17 1999-10-05 Pratt & Whitney Canada Inc. Housing for turbine assembly
US6733235B2 (en) * 2002-03-28 2004-05-11 General Electric Company Shroud segment and assembly for a turbine engine
US6942203B2 (en) * 2003-11-04 2005-09-13 General Electric Company Spring mass damper system for turbine shrouds
FR2887601B1 (fr) 2005-06-24 2007-10-05 Snecma Moteurs Sa Piece mecanique et procede de fabrication d'une telle piece
US7771159B2 (en) * 2006-10-16 2010-08-10 General Electric Company High temperature seals and high temperature sealing systems
FR2942844B1 (fr) * 2009-03-09 2014-06-27 Snecma Ensemble d'anneau de turbine avec arret axial
RU2522264C2 (ru) * 2009-03-09 2014-07-10 Снекма Сборка обоймы турбины
US8740552B2 (en) 2010-05-28 2014-06-03 General Electric Company Low-ductility turbine shroud and mounting apparatus
JP5962887B2 (ja) * 2012-02-02 2016-08-03 株式会社Ihi 翼の連結部構造及びこれを用いたジェットエンジン
WO2014158286A1 (en) * 2013-03-12 2014-10-02 Thomas David J Turbine blade track assembly
EP2801702B1 (de) * 2013-05-10 2020-05-06 Safran Aero Boosters SA Stator-innenring eines turbotriebwerks mit abriebmaterial

Also Published As

Publication number Publication date
RU2017145079A3 (de) 2019-10-23
CN111188655A (zh) 2020-05-22
CN108138579B (zh) 2020-03-06
EP4273370B1 (de) 2025-04-30
EP3298246A1 (de) 2018-03-28
WO2016189223A1 (fr) 2016-12-01
US11118477B2 (en) 2021-09-14
CA2986661A1 (fr) 2016-12-01
RU2017145079A (ru) 2019-06-24
CA3228720A1 (fr) 2016-12-01
CN108138579A (zh) 2018-06-08
FR3036435A1 (fr) 2016-11-25
RU2741192C2 (ru) 2021-01-22
US20180156068A1 (en) 2018-06-07
BR112017024871A2 (pt) 2018-08-07
US20200291820A1 (en) 2020-09-17
US10724401B2 (en) 2020-07-28
EP4273370A2 (de) 2023-11-08
BR112017024871B1 (pt) 2023-03-07
CA2986661C (fr) 2024-06-18
FR3036435B1 (fr) 2020-01-24
EP4273370A3 (de) 2024-02-14
CN111188655B (zh) 2022-06-24

Similar Documents

Publication Publication Date Title
EP3298246B1 (de) Turbinenringanordnung, die eine unterschiedliche wärmeausdehnung erlaubt
EP3298244B1 (de) Turbinenringanordnung mit axialer arretierung
EP3390783B1 (de) Turbinendeckbandanordung und zugehörige turbine
CA2986663C (fr) Ensemble d'anneau de turbine avec maintien par brides
EP3390782B1 (de) In einem kaltzustand elastisch gehaltene turbinenringanordnung
EP3433471B1 (de) Turbinendeckbandanordnung mit spezifischer aufhängung im kalten zustand
EP2406466B1 (de) Turbinenringanordnung
EP3271556B1 (de) Vorrichtung von turbinenringen mit mehreren teilringen aus keramik-verbundswerkstoffen
EP3298245B1 (de) Turbinenringanordnung mit einer befestigung in der art einer klauenkupplung
FR2942844A1 (fr) Ensemble d'anneau de turbine avec arret axial
EP3857030A1 (de) Anordnung für eine turbomaschine und zugehörige turbomaschine
EP3274565B1 (de) Turbinenringanordnung mit besonderer haltevorrichtung von ringsegmenten aus keramischen faserverbundwerkstoff
FR3041994A1 (fr) Ensemble d'anneau de turbine
FR2942845A1 (fr) Ensemble d'anneau de turbine

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20171114

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RIN1 Information on inventor provided before grant (corrected)

Inventor name: QUENNEHEN, LUCIEN

Inventor name: EVAIN, GAEL

Inventor name: ROUSSILLE, CLEMENT

Inventor name: LYPRENDI, ADELE

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20210611

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20230609

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: DE

Ref legal event code: R096

Ref document number: 602016084259

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20231122

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20240223

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20240322

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1634042

Country of ref document: AT

Kind code of ref document: T

Effective date: 20231122

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20240322

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20240223

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20240222

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20240322

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20240222

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602016084259

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

26N No opposition filed

Effective date: 20240823

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240518

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240518

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240531

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20240531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240518

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20240531

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20250519

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20250527

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20250522

Year of fee payment: 10

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20160518

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20160518

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20231122