EP3309360B1 - Ensemble d'aubes mobiles pour un moteur à turbine à gaz - Google Patents

Ensemble d'aubes mobiles pour un moteur à turbine à gaz Download PDF

Info

Publication number
EP3309360B1
EP3309360B1 EP17195634.5A EP17195634A EP3309360B1 EP 3309360 B1 EP3309360 B1 EP 3309360B1 EP 17195634 A EP17195634 A EP 17195634A EP 3309360 B1 EP3309360 B1 EP 3309360B1
Authority
EP
European Patent Office
Prior art keywords
blade assembly
stiffening
carrier
assembly group
rotor blade
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
EP17195634.5A
Other languages
German (de)
English (en)
Other versions
EP3309360A1 (fr
Inventor
Miklos Gäbler
Sven Brüggmann
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP3309360A1 publication Critical patent/EP3309360A1/fr
Application granted granted Critical
Publication of EP3309360B1 publication Critical patent/EP3309360B1/fr
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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3069—Fixing blades to rotors; Blade roots ; Blade spacers between two discs or 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2240/90—Mounting on supporting structures or systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/31—Retaining bolts or nuts
    • 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
    • F05D2300/6032—Metal matrix composites [MMC]

Definitions

  • the invention relates to a blade assembly for an engine with a blade carrier with a plurality of blades.
  • Such a blade assembly is for example part of a compressor or a turbine of the engine, in particular of a gas turbine engine.
  • the blades are thereby provided along a circular line about a central axis of the blade assembly, which central axis usually coincides with a rotational or central axis of the engine.
  • the blade carrier, on which the blade is integrally formed or are fixed to the separately manufactured blades via a respective blade root, has a with respect to the blades radially inwardly in the direction of the central axis extending support portion.
  • a stiffening structure having first and second metal matrix composite (MMC) stiffening members at the ring - or disk-shaped blade carrier provide.
  • MMC metal matrix composite
  • a stiffening element is designed as a fiber reinforced MMC ring and arranged on a respective end face of the blade carrier.
  • two MMC rings are defined in mirror image at a connecting region of a radially inwardly extending support section of a blade carrier, namely on a first front end side and on a second rear end side of the blade carrier.
  • the blade carrier can be acted on with a smaller radial extension of the carrier section with higher rotational speeds and thus higher load capacity.
  • the weight of the blade carrier is significantly lower than with a blade carrier of the same load carrying capacity with a larger carrier section through the MMC rings.
  • the stiffening elements in the form of MMC rings are independently of each other positively fixed to one end face of the support portion and optionally additionally shrunk onto an axially extending projection of the connecting portion.
  • Each MMC ring is axially secured separately on the respective end face of the support section and arranged on a radially outwardly facing transverse direction above the associated axially extending projection on the connection region of the support section. The fixation and in particular axial securing of the individual stiffening elements in the form of the MMC rings is thus comparatively complicated.
  • the invention is therefore based on the object to provide an improved in this respect blade assembly, with which the aforementioned disadvantages are avoided or at least reduced.
  • a rotor blade assembly for an engine with a ring segment or disk segment-shaped blade carrier having a plurality of rotor blades is proposed in which at least two, first and second reinforcing elements of a reinforcing structure fixed to a connecting region of a carrier section of a blade carrier are not only connected to the connecting region but the first and second stiffening elements are also additionally connected to each other.
  • the inventive solution according to the first aspect of the invention is based on the basic idea that at the connecting region of the blade carrier - preferably to a radially extending with respect to the central axis transverse direction symmetrically configured and opposing - stiffening elements are arranged on opposite first and second end faces of the blade carrier, the by their additional connection with each other axially (relative to the central axis) are secured.
  • the axial securing of both stiffening elements of the stiffening structure is in this case realized in at least one connecting device with at least one separate connecting element which directly connects the two stiffening elements arranged at different end sides and secures them axially against one another. In this way, none of the stiffening elements should be axially displaceable relative to the other stiffening element. Both stiffening elements are thus held in an intended position on the support portion.
  • connection opening can be a passage opening, for example in the form of a bore, through the blade carrier above the connection area, ie, around a passage opening which is spaced in a radially outward direction from the connection area.
  • the at least one separate connecting element then extends, for example, through such a connecting opening of the blade carrier in order to fix the two reinforcing elements axially relative to one another.
  • the two stiffening elements can be fixed to one another via the at least one connecting element of the connecting device extending through the carrier section, but also the two stiffening elements on the carrier section.
  • the at least one separate connecting element of the connecting device extends through a connecting opening in the carrier section in order to connect the first and second reinforcing elements to one another.
  • the connecting element can in this case be designed, for example, in the form of a screw bolt and furthermore extend through a respective radially projecting connecting web of the first and second reinforcing elements.
  • the rotor blade assembly according to the invention along a circumferential direction around the central axis comprises a plurality of adjacent ring segment-shaped or disk segment-shaped blade carrier, each having at least one blade, which are connected at each end face with a common - for example, annular - stiffening element of the stiffening structure via a plurality of bolt connections ,
  • the connecting means of the blade assembly not only serve the fixation of the two first and second stiffening elements together, but also the fixing of the two first and second stiffening elements to a plurality of ring segment-shaped or disk segment-shaped blade carriers and a coupling of the individual ring segment-shaped or disk segment-shaped blade carrier with each other. Accordingly, an anti-rotation device for the stiffening elements on the one hand and the blade carrier on the other hand is also provided.
  • the connecting device of the blade assembly is set up and provided to connect the blade assembly with a connecting member via which the blade assembly with another Blade assembly is rotatably connected, which is axially offset within the engine along the central axis.
  • individual blade rows which are each formed by a blade assembly, arranged in a multi-stage compressor or in a multi-stage turbine of the engine behind each other and rotatably connected to each other.
  • a connecting component for the non-rotatable connection of individual axially offset blade rows is now fixed via a connecting device on a blade carrier, which is also used to connect the two arranged on different end faces of the blade carrier first and second stiffening elements together and preferably to fix each other and the blade carrier.
  • the connecting member is in this case, for example, sleeve-shaped and each with an annular mounting flange formed on each end face, via which the connecting member is fixed to a blade assembly.
  • a plurality of respective sleeve segment-shaped connecting components may be provided to non-rotatably connect two rows of blades in the region of a ring segment or disk segment-shaped blade carrier or in the region of a plurality of ring segment or disk segment-shaped blade carrier.
  • a separate connection element of the connection device extends both through a connection opening in the support section and through a connection opening in the connection component.
  • the connection opening of the connection component is a through-hole in a flange section of the connection component.
  • At least one of the first and second stiffening elements is at least partially made of a metal matrix composite material (English: “metal matrix composite”, short: “MMC”) produced.
  • MMC metal matrix composite
  • at least one of the first and second stiffening elements may comprise an externally sheathed core of a metal matrix composite material.
  • the core can for example consist of a reinforced titanium in MMC construction, ie, in particular of a titanium matrix with ceramic reinforcement.
  • the blade carrier on the rotor blade assembly-together with other ring segment or disk segment-shaped blade carriers- has a central passage opening extending axially relative to the center axis, which is radially bounded by inner edges of the carrier sections of the individual blade carriers.
  • a formed of a metal matrix composite portion of the first or second stiffening member extends axially below such an inner edge of the support portion of a ring segment or disk segment-shaped blade carrier.
  • the connecting region forms at least one axial projection, which is encompassed by a first or second stiffening element in a form-fitting manner, so that the axial projection is at least partially received between a radially outer and a radially inner portion of this stiffening element.
  • an axially protruding portion of the connecting portion extends between a radially outer and a radially inner portion of the stiffening member.
  • the axial projection may here be formed locally web-like protruding on the connection region and for example between the two Sections of the stiffening element to be received in a groove-shaped recess of the stiffening element.
  • the blade carrier together with further ring segment or disk segment-shaped blade carriers of the blade assembly may have a passage opening extending axially relative to the central axis, which is radially bounded by an inner edge of the carrier section, and may be a first or second stiffening element of the stiffening structure with at least a portion extending below this inner edge of the connecting region axially.
  • a first or second stiffening element of the stiffening structure thus extends here with at least one section axially on the inner edge of the connecting area along an end face in the direction of the other end face of the blade carrier.
  • a blade assembly for an engine having at least one annular segment or disk segment-shaped blade carrier having a plurality of blades is proposed in which a stiffening structure is provided having at least one stiffening element on a first or second end face of the blade carrier.
  • the connection region according to the second aspect of the invention forms at least one axial projection which is encompassed by the at least one stiffening element so that the axial projection is at least partially received between a radially outer and a radially inner portion of the stiffening element.
  • the blade assembly has a passage opening extending axially relative to the central axis of the blade assembly, which is radially delimited by an inner edge of the carrier section, and the at least one reinforcing element of the reinforcing structure having at least one section below this inner Edge of the connection region extends axially, ie from one end face in the direction of the other end face.
  • connection region can basically extend essentially parallel to the central axis and therefore substantially perpendicular to a radially extending end face of the carrier section. However, the axial projection can also assume a deviating from 90 ° angle to the front side.
  • the at least one axial projection may be part of a cross-sectionally T-shaped, I-shaped or fir-tree-shaped profile of the connection region.
  • a T-shaped profile two projections extending axially in opposite directions are integrally formed at the connecting portion.
  • at least two or three pairs arranged radially one above the other and spaced apart from each other are provided in opposite directions of axially extending projections, the axial extent of which gradually decreases or increases along a radial direction.
  • a T-shaped, I-shaped or fir-tree-shaped profile of the connecting region extends in a variant in the circumferential direction about the central axis.
  • the connecting region of the ring segment or disk segment-shaped blade carrier is provided with a T-shaped, I-shaped or fir-tree-shaped profile extending over the entire length of the blade carrier in the circumferential direction.
  • one blade row each forming blade assemblies each having a plurality of ring segment-shaped or disk segment-shaped blade carrier and according to the invention a stiffening structure fixed thereto, arranged axially behind one another and rotationally fixed to each other, in particular via an axially extending connecting member or a plurality of connecting components with at least one stiffening element of a stiffening structure are connected.
  • a combination of an inventively designed blade assembly for the formation of a blade row with another, not inventively designed blade assembly of another blade row is possible.
  • the air conveyed into the primary flow passage via the compressor V enters a combustion chamber section BK of the core engine in which the driving power for driving the turbine TT is generated.
  • the turbine TT has a high-pressure turbine 13, a medium-pressure turbine 14 and a low-pressure turbine 15.
  • the turbine TT thereby drives the rotor shaft S and thus the fan F via the energy released during combustion in order to generate the required thrust via the air conveyed into the bypass duct B.
  • Both the air from the bypass passage B and the exhaust gases from the primary flow passage of the core engine flow through an outlet A at the end of the engine T.
  • the outlet A in this case usually has a discharge nozzle with a centrally arranged outlet cone C.
  • each blade carrier 23, 24 or 25 of a prior art blade assembly 2a, 2b or 2c has a radially inwardly extending beam portion 230, 240 or 250.
  • a disk-shaped support portion 250 of the rear blade assembly 2c serves, for example, for the rotatable mounting of the rotatably connected blade assemblies 2a, 2b and 2c.
  • a central through hole O1 or O2 is provided, especially in the form of a bore, especially for weight reduction.
  • the two mutually remote end faces of a blade carrier 23 or 24 arranged stiffening rings 50 and 51 of a blade assembly 2a or 2b are each connected via a connecting device 6a or 6b and in the present case to each other and to the support portion 230 or 240 fixed.
  • the respective connecting device 6a or 6b here comprises at least one separate connecting element in the form of a screw bolt 60.
  • This screw bolt 60 is provided, inter alia, above the respective connecting region 231, 241 for the stiffening structure 5a or 5b.
  • a nut 61 is turned on the bolt 60.
  • stiffening structure 5a or 5b With the stiffening rings 50 and 51 arranged on the end faces of the blade carrier 23 or 24 facing away from one another, radially acting forces can be absorbed in particular.
  • radially acting forces can be absorbed in particular.
  • circumferentially encircling profiling of the connecting portion 231 or 241 but at the same time a simpler installation and simple radial securing of the blade carrier 23 or 24 to be mounted stiffening rings 50 and 51 is given.
  • the connecting region 241 exemplarily illustrated here forms pairs of projections 2410.1 / 2410.2, 2411.1 / 2411.2 and 2412.1 / 2412.2 extending in opposite directions.
  • Each of these axial projections 2410.1 to 2412.2 protrudes annularly on an end face of the support portion 240.
  • the axial length of the individual axial projections 2410.1 to 2412.1 or 2410.2 to 2412.2 per end face decreases in the radial direction, in the present case radially inwards.
  • the MMC core 500 of a stiffening ring 50 or 51 extends with at least a portion 500.1 or 500.2 of the metal matrix composite material below the inner edge of the support portion 240.
  • the MMC core in cross-section is substantially L-shaped.
  • the MMC core 500 is only axially adjacent to the connection region 241 and in particular adjacent to the projections 2410.1 to 2412.2 arranged.
  • the MMC core 500 is arranged axially next to the connection region 241 and at least partially below the connection region 241 and consequently in particular adjacent to the projections 2410.1 to 2412.2 and at least partially below the projections 2410.1 to 2412.2.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (15)

  1. Module d'aubes directrices pour un groupe moteur (T), comprenant au moins un support d'aubes (23, 24) qui présente plusieurs aubes directrices (20, 21) qui sont prévues, avec plusieurs autres aubes directrices (20, 21), le long d'un cercle autour d'un axe médian (M) du module d'aubes directrices (2a, 2b), dans lequel
    - le support d'aubes (23, 24) présente une portion de support (230, 240) s'étendant radialement vers l'intérieur dans la direction de l'axe médian (M) par rapport aux aubes directrices (20, 21),
    - la portion de support (230, 240) comprend une région de connexion (231, 241) au niveau de laquelle est fixée une structure de renforcement (5a, 5b) avec au moins un premier élément de renforcement (50) et au moins un deuxième élément de renforcement (51), et
    - le premier élément de renforcement (50) est disposé au niveau d'un premier côté frontal du support d'aubes (23, 24) et le deuxième élément de renforcement (51) est disposé au niveau d'un deuxième côté frontal opposé au premier côté frontal, l'au moins un premier élément de renforcement (50) et l'au moins un deuxième élément de renforcement (51) étant connectés à la région de connexion (231, 241) du support d'aubes (23, 24) et étant en outre connectés l'un à l'autre,
    caractérisé en ce que
    le support d'aubes (23, 24) est réalisé le long du cercle en forme de segment annulaire ou en forme de segment de disque.
  2. Module d'aubes directrices selon la revendication 1, caractérisé en ce que les premier et deuxième éléments de renforcement (50, 51) disposés sur des côtés frontaux différents du support d'aubes (23, 24) sont connectés l'un à l'autre par le biais d'au moins un dispositif de connexion (6a, 6b).
  3. Module d'aubes directrices selon la revendication 2, caractérisé en ce qu'au moins un élément de connexion séparé (60) du dispositif de connexion (6a, 6b) s'étend à travers une ouverture de connexion (243) dans la portion de support (230, 240), afin de connecter l'un à l'autre le premier et le deuxième élément de renforcement (50, 51).
  4. Module d'aubes directrices selon la revendication 2 ou 3, caractérisé en ce que le dispositif de connexion (6a, 6b) est en outre disposé et prévu pour connecter le module d'aubes directrices (2a, 2c) à un composant de connexion (7a, 7b) par le biais duquel le module d'aubes directrices (2a, 2b) est connecté de manière solidaire en rotation à un module d'aubes directrices supplémentaire (2b, 2a, 2c) qui est disposé à l'intérieur du groupe moteur (T) de manière décalée axialement le long de l'axe médian (M).
  5. Module d'aubes directrices selon les revendications 3 et 4, caractérisé en ce que l'au moins un élément de connexion séparé (60) s'étend à la fois à travers une ouverture de connexion (243) dans la portion de support (230, 240) ainsi qu'à travers une ouverture de connexion dans le composant de connexion (7a, 7b).
  6. Module d'aubes directrices selon l'une quelconque des revendications précédentes, caractérisé en ce qu'au moins le premier ou le deuxième élément de renforcement (50, 51) est réalisé sous forme annulaire.
  7. Module d'aubes directrices selon l'une quelconque des revendications précédentes, caractérisé en ce qu'au moins l'un des premier et deuxième éléments de renforcement (50, 51) est fabriqué au moins en partie en un matériau composite à matrice métallique.
  8. Module d'aubes directrices selon la revendication 7, caractérisé en ce qu'au moins l'un des premier et deuxième éléments de renforcement (50, 51) présente un noyau (500) à gaine extérieure constitué d'un matériau composite à matrice métallique.
  9. Module d'aubes directrices selon la revendication 7 ou 8, caractérisé en ce que le module d'aubes directrices (2a, 2b) présente une ouverture de passage (O1, O2) s'étendant axialement par rapport à l'axe médian (M), qui est limitée radialement par un bord intérieur de la portion de support (230, 240), et une portion du premier ou du deuxième élément de renforcement (50, 51), formée d'un matériau composite à matrice métallique, s'étend axialement radialement à l'intérieur quant au bord intérieur de la région de connexion (231, 241) .
  10. Module d'aubes directrices selon l'une quelconque des revendications précédentes, caractérisé en ce que la région de connexion (231, 241) constitue au moins une saillie axiale (2410.1-2412.2) qui est saisie sur son pourtour par engagement par correspondance de formes par un premier ou un deuxième élément de renforcement (50, 51), de telle sorte que la saillie axiale (2410.1-2410.2) soit reçue au moins en partie entre une portion radialement extérieure et une portion radialement intérieure de cet élément de renforcement (50, 51) .
  11. Module d'aubes directrices selon l'une quelconque des revendications précédentes, caractérisé en ce que le module d'aubes directrices (2a, 2b) présente une ouverture de passage (O1, O2) s'étendant axialement par rapport à l'axe médian (M), qui est limitée radialement par un bord intérieur de la portion de support (230, 240), et un premier ou un deuxième élément de renforcement (50, 51) de la structure de renforcement (5a, 5b) s'étend axialement, avec au moins une portion (50.1, 50.2), radialement à l'intérieur quant au bord intérieur de la région de connexion (231, 241) .
  12. Module d'aubes directrices pour un groupe moteur (T), en particulier selon l'une quelconque des revendications 1 à 11, comprenant au moins un support d'aubes (23, 24), qui présente plusieurs aubes directrices (20, 21) qui sont prévues, avec plusieurs autres aubes directrices (20, 21), le long d'un cercle autour d'un axe médian (M) du module d'aubes directrices (2a, 2b), dans lequel
    - le support d'aubes (23, 24) présente une portion de support (230, 240) s'étendant radialement vers l'intérieur dans la direction de l'axe médian (M) par rapport aux aubes directrices (20, 21),
    - la portion de support (230, 240) comprend une région de connexion (231, 241) au niveau de laquelle est fixée une structure de renforcement (5a, 5b) avec au moins un élément de renforcement (50, 51), et
    - l'élément de renforcement (50, 51) est disposé au niveau d'un premier ou d'un deuxième côté frontal du support d'aubes (23, 24),
    caractérisé en ce que
    le support d'aubes (23, 24) est réalisé le long du cercle en forme de segment annulaire ou en forme de segment de disque et
    (a) la région de connexion (231, 241) constitue au moins une saillie axiale (2410.1-2412.2) qui est saisie sur son pourtour par engagement par correspondance de formes par l'au moins un élément de renforcement (50, 51), de telle sorte que la saillie axiale (2410.1-2412.2) soit reçue au moins en partie entre une portion radialement extérieure et une portion radialement intérieure de l'élément de renforcement (50, 51), et/ou
    (b) le module d'aubes directrices (2a, 2b) présente une ouverture de passage (O1, O2) s'étendant axialement par rapport à l'axe médian (M), qui est limitée radialement par un bord intérieur de la portion de support (230, 240), et l'au moins un élément de renforcement (50, 51) de la structure de renforcement (5a, 5b) s'étend axialement, avec au moins une portion (50.1, 51.2), radialement à l'intérieur quant au bord intérieur de la région de connexion (231, 241) .
  13. Module d'aubes directrices selon la revendication 10 ou 12, caractérisé en ce que la saillie axiale (2410.1-2412.2) fait partie d'un profilé de la région de connexion (231, 241) de section transversale en forme de T, en forme de I ou en forme de sapin.
  14. Module d'aubes directrices selon la revendication 13, caractérisé en ce que le profilé en forme de T, en forme de I ou en forme de sapin de la région de connexion (231, 241) s'étend au moins en partie le long d'un cercle autour de l'axe médian (M).
  15. Moteur à turbine à gaz comprenant au moins un module d'aubes directrices (2a, 2b) selon l'une quelconque des revendications 1 à 14.
EP17195634.5A 2016-10-12 2017-10-10 Ensemble d'aubes mobiles pour un moteur à turbine à gaz Active EP3309360B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102016219818.1A DE102016219818A1 (de) 2016-10-12 2016-10-12 Laufschaufelbaugruppe mit ringsegment- oder scheibensegmentförmigem Schaufelträger und radial innenliegender Versteifungsstruktur

Publications (2)

Publication Number Publication Date
EP3309360A1 EP3309360A1 (fr) 2018-04-18
EP3309360B1 true EP3309360B1 (fr) 2019-07-03

Family

ID=60051436

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17195634.5A Active EP3309360B1 (fr) 2016-10-12 2017-10-10 Ensemble d'aubes mobiles pour un moteur à turbine à gaz

Country Status (3)

Country Link
US (1) US10794199B2 (fr)
EP (1) EP3309360B1 (fr)
DE (1) DE102016219818A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US12000308B2 (en) 2022-08-23 2024-06-04 General Electric Company Rotor blade assemblies for turbine engines

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1325208A (en) * 1919-12-16 Elastic-fi
US1178452A (en) * 1913-10-01 1916-04-04 Terry Steam Turbine Company Turbine-blading.
US3501249A (en) * 1968-06-24 1970-03-17 Westinghouse Electric Corp Side plates for turbine blades
US3610772A (en) * 1970-05-04 1971-10-05 Gen Motors Corp Bladed rotor
US3610777A (en) * 1970-05-15 1971-10-05 Gen Motors Corp Composite drum rotor
US3656864A (en) * 1970-11-09 1972-04-18 Gen Motors Corp Turbomachine rotor
FR2143561B1 (fr) * 1971-06-29 1974-03-08 Snecma
US3765796A (en) * 1972-05-01 1973-10-16 United Aircraft Corp Filament reinforced rotor assembly
US3787141A (en) * 1972-11-30 1974-01-22 United Aircraft Corp Filament reinforced motor assembly
DE4132332A1 (de) * 1990-12-14 1992-06-25 Ottomar Gradl Anordnung zum befestigen von schaufeln an der scheibe eines rotors
DE4324755C1 (de) * 1993-07-23 1994-09-22 Mtu Muenchen Gmbh Verfahren zur Herstellung faserverstärkter Triebwerkskomponenten
US5660526A (en) * 1995-06-05 1997-08-26 Allison Engine Company, Inc. Gas turbine rotor with remote support rings
US5632600A (en) * 1995-12-22 1997-05-27 General Electric Company Reinforced rotor disk assembly
GB2456637B (en) * 1997-06-03 2010-01-13 Rolls Royce Plc A fibre reinforced metal rotor
US6213720B1 (en) * 1999-06-11 2001-04-10 Alliedsignal, Inc. High strength composite reinforced turbomachinery disk
DE10163951C1 (de) 2001-12-22 2002-12-19 Mtu Aero Engines Gmbh Rotorscheibe aus Metall mit örtlichen Faserverstärkungen
DE10218459B3 (de) 2002-04-25 2004-01-15 Mtu Aero Engines Gmbh Verdichter in mehrstufiger Axialbauart
FR2845436B1 (fr) * 2002-10-02 2004-12-31 Snecma Moteurs Tambour formant en particulier un rotor de turbomachine, compresseur et turbomoteur comprenant un tel tambour
DE10358421A1 (de) * 2003-12-13 2005-07-07 Mtu Aero Engines Gmbh Rotor für eine Turbomaschine
DE102006015838A1 (de) * 2006-04-03 2007-10-04 Rolls-Royce Deutschland Ltd & Co Kg Axialkompressor für ein Gasturbinentriebwerk
FR2941487B1 (fr) * 2009-01-28 2011-03-04 Snecma Aube de turbomachine en materiau composite a pied renforce

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
US20180100402A1 (en) 2018-04-12
DE102016219818A1 (de) 2018-04-12
US10794199B2 (en) 2020-10-06
EP3309360A1 (fr) 2018-04-18

Similar Documents

Publication Publication Date Title
DE69930711T2 (de) Nasenhaube für ein Gasturbinentriebwerk
EP1483482B1 (fr) Fixation d'une aube directrice dans le canal d'ecoulement d'une turbine a gaz d'avion
DE102007025006A1 (de) Doppelwellen-Gasturbine
EP2320030B1 (fr) Rotor et aube de rotor pour une turbomachine axiale
EP2728122B1 (fr) Fixation de support d'étanchéité pour turbomachine
EP3309359B1 (fr) Ensemble d'aubes mobiles pour un moteur à turbine à gaz
EP3287611B1 (fr) Turbine à gaz
EP3236011B1 (fr) Rotor comprenant un porte à faux sur les pales pour un élément de sécurité
EP2994614A1 (fr) Rotor pour turbomachine thermique
EP2994615B1 (fr) Rotor pour une turbomachine thermique
EP3431708A1 (fr) Dispositif d'écoulement autour, turbomachine et application associées
EP3022393B1 (fr) Rotor pour une turbomachine thermique
EP3121385B1 (fr) Dispositif de rotor d'un réacteur d'avion avec un disposiitf d'amortissement entre des pales
DE102012215413B4 (de) Baugruppe einer Axialturbomaschine
EP2394028B1 (fr) Dispositif d'étanchéité sur l'arbre à aubes d'un étage de rotor d'une turbomachine axiale et son utilisation
EP3309360B1 (fr) Ensemble d'aubes mobiles pour un moteur à turbine à gaz
EP2526263B1 (fr) Système de boîtier pour une turbomachine axiale
EP3401503A1 (fr) Dispositif rotor d'une turbomachine
WO2018060068A1 (fr) Aubes à tracé en forme de s dans la direction d'écoulement pour des roues à aubes à type de construction radiale
EP3225789A1 (fr) Ensemble de moteur avec carter de soufflante et diffuseur d'entrée
DE102020122418A1 (de) Planetengetriebe
EP3406860B1 (fr) Turboréacteur
EP3246521B1 (fr) Rampe pour plaque de recouvrement d'aube directrice et embase d'aube mobile
DE102018205480A1 (de) Laufschaufelbaugruppe mit einem Sperrelement zur axialen Sicherung eines Versteifungselements einer radial innenliegenden Versteifungsstruktur
EP4069947A1 (fr) Support d'étanchéité conçu pour une turbomachine comportant des ouvertures de type fentes dans le corps d'étanchéité

Legal Events

Date Code Title Description
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: THE APPLICATION HAS BEEN PUBLISHED

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

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: 20181018

RBV Designated contracting states (corrected)

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

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/02 20060101AFI20181108BHEP

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: 20190104

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

GRAR Information related to intention to grant a patent recorded

Free format text: ORIGINAL CODE: EPIDOSNIGR71

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

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

INTC Intention to grant announced (deleted)
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

INTG Intention to grant announced

Effective date: 20190524

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: AT

Ref legal event code: REF

Ref document number: 1151221

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190715

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502017001682

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: GERMAN

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20190703

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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: 20190703

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: 20190703

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: 20190703

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: 20191003

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: 20190703

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: 20191104

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: 20190703

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: 20190703

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: 20191003

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

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: 20190703

Ref country code: AL

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: 20190703

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: 20191004

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: 20190703

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: 20191103

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

Ref country code: TR

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: 20190703

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

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: 20190703

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: 20190703

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: 20190703

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: 20190703

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: 20190703

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: 20200224

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: 20190703

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: 20190703

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: 20190703

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502017001682

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

PG2D Information on lapse in contracting state deleted

Ref country code: IS

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: 20191010

26N No opposition filed

Effective date: 20200603

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20191031

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: 20190703

Ref country code: BE

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

Effective date: 20191031

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: 20190703

Ref country code: IE

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

Effective date: 20191010

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

Effective date: 20190703

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: CH

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: 20201031

Ref country code: LI

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: 20201031

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

Ref country code: MT

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: 20190703

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: 20171010

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

Ref country code: MK

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: 20190703

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230528

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1151221

Country of ref document: AT

Kind code of ref document: T

Effective date: 20221010

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

Ref country code: GB

Payment date: 20231024

Year of fee payment: 7

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 NON-PAYMENT OF DUE FEES

Effective date: 20221010

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

Ref country code: FR

Payment date: 20231026

Year of fee payment: 7

Ref country code: DE

Payment date: 20231027

Year of fee payment: 7