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
  • F01D5/32—Locking, e.g. by final locking blades or keys
  • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
• • 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
  • F01D5/3084—Fixing blades to rotors; Blade roots ; Blade spacers the blades being made of ceramics
• • 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
  • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
• • 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
  • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters
• • 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
  • F05D2240/50—Bearings
  • F05D2240/54—Radial bearings
• • 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
  • F05D2250/00—Geometry
  • F05D2250/70—Shape
  • F05D2250/71—Shape curved

Definitions

• TITLE WEDGE FOR TURBOMACHINE ROTOR, ROTOR AND ASSOCIATED TURBOMACHINE ASSEMBLY
• the present invention relates to the field of turbomachines such as turboprops or turbojets.
• the invention relates to a wedge for a turbomachine rotor, as well as a rotor assembly equipping such a turbomachine.
• a turbomachine rotor for example a rotor used in a low pressure turbine extending around a longitudinal axis and conventionally comprises one or more rotor disks carrying at the external periphery a plurality of moving blades.
• the moving blades have a radially internal part, or blade root, extended by a blade. These moving blades are housed at their base in cells which open onto the outer peripheral surface of the rotor disk.
• the positioning of the blade roots in the cells of the rotor disks is done by translation along an axis substantially longitudinal to the axis of the turbomachine.
• Documents FR 2994 211 and FR 3 072 122 present such moving blades provided with stilts so as to limit their radial movements towards the axis of revolution of the engine or towards the outside when they are housed in the cells of the disc of rotor.
• Such stilts can in particular include low walls abutting against the teeth formed between two successive cells, thus allowing radial maintenance of the position of the moving blades.
• the invention aims to remedy at least partly the disadvantages mentioned above relating to the prior art.
• the invention relates to a wedge for a moving blade being intended to present a blade root mounted in a cell which opens out at the external periphery of a turbomachine rotor disk of longitudinal axis X, the wedge comprising a base configured to be mounted in the cell and which is configured to be mounted in contact with the blade root.
• said base has at least one so-called elastic portion which is corrugated so as to apply a radial force outwards on said blade root when the blade root rests on the base mounted in the cell.
• the base has an upstream longitudinal end and a downstream longitudinal end configured to come into axial support against one of the disk or the blade root.
• the invention proposes a solution making it possible to resolve at least in part some of the disadvantages of the prior art.
• the geometry of the moving blade is simplified. which allows a saving of time for the production of such a moving blade, as well as savings in material.
• the invention allows radial retention of the moving blades which is adaptable to all types of moving blades, regardless of the material in which the moving blades are made.
• the wedge comprises an upstream tongue extending from said upstream longitudinal end of said base and/or a downstream tongue extending from said downstream longitudinal end of said base, said upstream and downstream tongues forming means for axially stopping a blade relative to the disk.
• said upstream tongue extends in a radial direction of said turbomachine and/or said downstream tongue extends in a radial direction of said turbomachine.
• said upstream tongue extends in a direction orthogonal to the axial direction of said turbomachine and/or said downstream tongue extends in a direction orthogonal to the axial direction of said turbomachine.
• the axial stopping means can be held against the rotor disk.
• said elastic portion extends longitudinally in the center of said base.
• this makes it possible to have a radial force exerted by the wedge on the blade root which is relatively balanced so as not to have a tilting of the movable blade towards upstream or downstream.
• the invention also relates to a rotor assembly for a turbomachine comprising a rotor disk carrying a plurality of movable blades housed at their blade root in cells which open out at the external periphery of said disk, the assembly further comprising a plurality of wedges according to one of the aforementioned embodiments, each of the wedges being arranged between the blade root and the bottom of one of said cells.
• said base has a length taken along the longitudinal axis substantially equal to the length taken along the longitudinal axis of each of said cells
• said base has a single undulation which extends from the upstream longitudinal end to the downstream longitudinal end and is in contact with said blade root at the level of the upstream and downstream longitudinal ends of the base.
• the base is in contact with the bottom of said cell at a longitudinally central portion.
• the rotor assembly further comprises a plurality of foils, each disposed between one of said blade roots and one of said wedges.
• At least one of said blades is at least partially composed of ceramic matrix composite material.
• the invention also relates to a turbomachine for an aircraft comprising a rotor assembly according to one of the aforementioned embodiments.
• FIG. 1 is a schematic sectional view of a turbomachine
• FIG. 2 is a sectional view of a part of a turbomachine rotor assembly
• FIG. 3 is a detailed view of zone A of Figure 2;
• FIG. 4 is a perspective view of part of a turbomachine rotor assembly
• FIG. 5 is another sectional view of a spacer for a turbomachine rotor according to one embodiment of the invention.
• turbomachine any type of turbomachine, and in particular to aircraft turbomachines.
• This turbomachine which extends along an axis wing or even at the rear of the fuselage of the aircraft.
• the turbomachine 1 illustrated in Figure 1 is a twin-body, dual-flow, direct-drive turbojet. This is however not limiting since the turbomachine 1 may not be intended to be mounted on an aircraft, be another type of turbojet, such as a geared turbojet, a turboprop or an auxiliary power unit (also called " APU”, for “Auxiliary Power Unit”).
• an axial direction corresponds to the direction of the longitudinal axis X and a radial direction is a direction perpendicular to the longitudinal axis longitudinal X.
• an axial plane is a plane containing the longitudinal axis X and a radial plane is a plane perpendicular to the longitudinal axis X.
• the turbomachine 1 comprises, from upstream to downstream, a fan 10, a compressor section 12, a combustion chamber 14 and a turbine section 16.
• the blower 10 sucks in a flow of air, a portion of which, circulating within a primary vein 100, is successively compressed within the compressor section 12, ignited within the combustion chamber 14, and relaxed within the turbine section 16 before being ejected out of the turbomachine 1.
• the turbomachine 1 generates thrust. This thrust can also, for example, be used for the benefit of the aircraft on which the turbomachine 1 is attached and fixed.
• the compressors and turbines comprise an alternation of mobile disks mounted to rotate around the longitudinal axis X of the turbomachine, called rotor disks, and fixed disks, called stator disks.
• Each rotor disk assembly comprises a plurality of cells 90 hollowed out on their peripheral surface and which open out at the external periphery of the disk. These cells are intended to each accommodate a moving blade, and more particularly a blade root 30, so that each rotor disk carries a plurality of moving blades, each moving blade being intended to present a blade root mounted in one of the cells which opens out to the outer periphery of the rotor disk.
• the moving blades are preferably at least partially composed of ceramic matrix composite material.
• the assembly further comprises a plurality of shims mounted in the cells 90, and arranged between the blade root 30 and the bottom of one of the cells 90.
• These shims can for example be made at least partially from a metal or a metal alloy.
• the wedge 2 for turbomachine rotor 1 comprises a base 20.
• This base is intended to be housed in a space 8 formed between a cell 90 dug on the outer peripheral surface of a rotor disk 9 and a foot 30 blade 3 housed in the cell 90, and coming into contact with the blade root 30 and the disc
• the base 20 has a length taken along the longitudinal axis, or axial length, substantially equal to the axial length of each of the cells 90.
• the base 20 has at least one elastic portion which is corrugated so as to apply a radial force outwards on the blade root 30.
• This radial force exerted by the base on the blade root thus ensures radial retention of the movable blade in the cell and prevents the movable blade from shifting radially or even sinking into the cell. .
• the base 20 has an upstream longitudinal end and a downstream longitudinal end configured to come into axial support against one of the disc or blade root 30.
• the base 20 therefore presents here an elasticity which allows the wedge to deform during assembly to then apply a pushing force, that is to say a force towards the outside of the turbomachine. More particularly in this embodiment, and as visible in particular in Figure 2, the elastic portion extends to the center of the base 20, so that the wedge provides a radial force which is relatively balanced and avoids tilting of the movable blade towards upstream or downstream. However, one could provide embodiments in which the elastic portion would be offset towards the upstream longitudinal end or the downstream longitudinal end so as to compensate for a distribution of mass or force of the movable blade.
• This elastic portion therefore corresponds here to a central portion which is here, as visible for example in Figure 3, in contact with the bottom of the cell 90, while the base 20 is in contact with the blade root 30.
• the wedge 2 further comprises axial stopping means in the form of an upstream tongue 21 and a downstream tongue 22.
• the wedge 2 also comprises a downstream tongue 22 extending from a downstream end of the base 20.
• This downstream tongue 22 extends here in a radial direction of the turbomachine, and more particularly radially towards the outside of the turbomachine.
• the orientation of the tongues depends in particular on the implementation of an upstream or downstream flange at the level of the rotor disk, another embodiment could be provided in which the upstream tongue would extend radially towards the outside of the turbomachine and the downstream tongue would extend radially towards the inside of the turbomachine.
• the upstream 21 and downstream 22 tongues in this embodiment are in contact with the rotor disk 9.
• tongues here form means for axially stopping the movable blade, respectively towards the upstream and downstream, and allow the movable blade not to shift axially relative to the cell of the rotor disk.
• the rotor assembly for a turbomachine further comprises a plurality of foils 4.
• Each of these foils 4 is here arranged between one of the blade roots 30 and one of the wedges 2. More particularly, each foil 4 is here mounted so as to be in contact with the blade root and to form a layer making it possible to protect the blade root against wear and deformation.
• each foil 4 comprises a foil base configured to be in contact with a lower face of the blade root 30, and two side fins configured to be in contact with lateral surfaces of the blade root.
• each foil 4 has a substantially U-shaped shape with two fins connected by a foil base.
• the elastic portion of the base 20, which therefore extends longitudinally in the center of the base 20, applies a radial force towards the outside of the central portion of the base of the foil 4.
• upstream and downstream longitudinal ends of the base 20 they are, in this embodiment, resting against the upstream and downstream longitudinal ends of the base of the foil 4.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Ceramic Engineering (AREA)
• Turbine Rotor Nozzle Sealing (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=86007569

Family Applications (1)

Country Status (4)

Family Cites Families (8)

• 2023
  • 2023-01-23 FR FR2300607A patent/FR3145186A1/fr active Pending
• 2024
  • 2024-01-18 WO PCT/FR2024/050069 patent/WO2024156954A1/fr not_active Ceased
  • 2024-01-18 CN CN202480006235.3A patent/CN120500575A/zh active Pending
  • 2024-01-18 EP EP24704231.0A patent/EP4655488A1/de active Pending

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