Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
  • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
• • 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
  • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
• • 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
  • F01D25/08—Cooling; Heating; Heat-insulation
  • F01D25/12—Cooling
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
  • F01D25/246—Fastening of diaphragms or stator-rings
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • 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]
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• the invention relates to a turbine ring assembly for a turbomachine in which the assembly comprises a plurality of angular ring sectors placed end to end to form a turbine ring of ceramic matrix composite material.
• One field of application of the invention is in particular that of gas turbine aero engines.
• Ceramic matrix composite materials are known to retain their mechanical properties at high temperatures, which makes them suitable for forming hot structural elements.
• a metal turbine ring assembly deforms under the influence of heat flows, which changes the clearances in the flow stream and, consequently, the performance of the turbine.
• the production of turbine ring sectors in a single piece in CMC is described in particular in document US 2012/0027572.
• the ring sectors comprise an annular base, the internal face of which defines the internal face of the turbine ring and an external face from which extend radially two legs, the ends of which are held between the two flanges of a structure. metal ring holder.
• CMC ring sectors thus significantly reduces the ventilation required to cool the turbine ring.
• the CMC having a different mechanical behavior from a metallic material, its integration as well as the way of positioning it within the turbine had to be rethought.
• CMC does not support shrink-wrapped assemblies (usually used for metal rings) and its thermal expansion is lower than that of a metallic material.
• CMC ring sectors increase the number of parts necessary for its integration on the turbine housing, which increases the cost and weight of the assembly and requires complex assembly operations (shrinking of bushings, pin assembly, etc.).
• the main object of the present invention is therefore to provide a turbine ring assembly which does not have the aforementioned drawbacks.
• a turbine ring assembly extending around an axis, comprising a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure maintained.
• each ring sector comprising a base from which extend radially outward an upstream lug and a downstream lug spaced axially from one another, the ring support structure comprising a spacer having a flange against which the downstream lug of the ring sectors is held, a first upstream flange against which the upstream lug of the ring sectors is held, and, upstream of the first flange upstream, a second upstream load-absorbing flange against which the first upstream flange is held.
• the turbine ring assembly according to the invention is remarkable in particular in that the CMC ring is held directly on the turbine housing by means of a ring support structure without resorting to a pressure housing. ring holder.
• the assembly according to the invention does not have a ring support housing and the radial pins allowing the ring support structure to be held on this housing are omitted.
• the ring support structure is made of several separate and independent parts, which allows this structure to be mounted in angular sectors and no longer in a ring.
• the assembly of the turbine ring assembly is simplified and requires no tools.
• the manufacturing tolerances are less severe, the spacers making it possible to make up for the gaps between the ring sectors, which a 360 ° flange cannot do.
• the removal of radial pins decreases the machining operations of the parts of the ring support structure. The result is a saving in parts, and therefore a reduction in the weight and cost of the assembly.
• the ring support structure further comprises an air diffuser for diffusing cooling air on an outer face of the base of the ring sectors.
• the air diffuser of the ring support structure may include a flange held between the spacer and the first upstream flange.
• the ring support structure further comprises a plurality of fixing means screwed into the spacer and passing through from upstream to downstream to fix the first upstream flange, the second upstream flange and the diffuser flange between them. 'air.
• the assembly further comprises upstream axial pins intended to hold the first upstream flange of the ring support structure against the upstream tab of the ring sectors.
• the assembly preferably further comprises downstream axial pins intended to hold the flange. of the spacer of the ring support structure against the downstream leg of the ring sectors.
• the ring support structure spacer may include an upstream hook for mounting said ring support structure to the turbine housing.
• the first flange upstream of the ring support structure may include a hook for mounting said ring support structure on the turbine housing.
• the spacer of the ring support structure may further include a downstream hook for holding a low-pressure turbine manifold positioned downstream of the turbine assembly.
• the subject of the invention is also a turbomachine comprising an assembly as defined above.
• Figure 1 is a longitudinal sectional view of a turbine ring assembly according to the invention.
• Figure 2 is a schematic perspective view of the turbine assembly of Figure 1.
• Figure 1 shows, in longitudinal section, a turbine ring assembly 2 according to the invention.
• This assembly 2 comprises in particular a turbine ring 4 made of ceramic matrix composite material (CMC) centered on a longitudinal axis XX and a metal ring support structure 6.
• the turbine ring 4 surrounds a set of turbine blades.
• the turbine ring 4 is formed from a plurality of angular ring sectors 10 which are placed end to end circumferentially to form a ring.
• the arrow DA indicates the axial direction of the turbine ring while the arrow DR indicates the radial direction of the turbine ring.
• Each angular sector of ring 10 has a section substantially in the form of an inverted Pi (or TT) with a base 12 provided with an internal face 12a which defines a angular portion of the internal face of the turbine ring and which is typically provided with an abradable coating layer 14 also acting as a thermal and environmental barrier.
• Two legs - namely an upstream leg 16 and a downstream leg 18 - extend radially from the outer face 12b of the base 12 opposite the inner face 12a. These tabs 16, 18 extend over the entire width of the ring sector 10 (in the circumferential direction).
• the ring support structure 6 is produced by assembling a plurality of parts which are distinct (i.e. independent) from each other.
• these parts include in particular a spacer 20, a first upstream flange 22, a second upstream flange 24 for absorbing forces, and an air diffuser 26.
• the spacer 20 comprises a flange 20a against which the downstream leg 18 of the ring sectors 10 is held by means of a plurality of downstream axial pins 28 regularly distributed around the longitudinal axis X-X of the ring.
• the spacer 20 also includes an upstream hook 20b which is intended to engage with a downstream hook 30 of a turbine housing 32 to allow mounting of the ring support structure directly on the turbine housing.
• the spacer 20 also comprises a downstream hook 20c which is intended to engage in a corresponding hook (not shown in the figures) of a low-pressure turbine distributor 34 located downstream of the ring assembly 2. turbine in order to maintain it.
• the spacer 20 may be a part of revolution (that is to say 360 °) or be produced by an assembly of a plurality of spacer sectors placed end to end.
• the upstream tab 16 of the ring sectors 10 is held against the first upstream flange 22.
• the first upstream flange 22 also comprises a hook 22a which is intended to engage in an upstream hook 36 of the turbine casing 32 in order to allow the ring support structure to be mounted directly on the turbine casing.
• the first upstream flange 22 may be a part of revolution (that is to say of 360 °) or else be produced by an assembly of two half-flanges of 180 ° each.
• the first upstream flange 22 is held upstream against a second upstream flange 24 for absorbing forces.
• the latter is intended to take up the forces of a high-pressure turbine distributor 38 which is positioned upstream of the turbine ring assembly.
• This front flange 24 may be a part of revolution (that is to say of 360 °) or be a sectored part.
• the air diffuser 26 is intended to diffuse cooling air on the outer face 12b of the base 12 of the ring sectors. To this end, it comprises a cavity 26a positioned around the base 12 of the ring sectors, supplied with cooling air taken from a stage of the compressor of the turbomachine and opening out towards the outer face of the base of the ring sectors by through a multi-perforation of its walls (not shown in the figures).
• the air diffuser 26 also includes a flange 26b coming directly into axial abutment against the upstream lug 16 of the ring sectors 10.
• the ring support structure 6 further comprises a plurality of fixing means 40 (for example bolted connections) which are screwed into the spacer 20 and pass from upstream to downstream to fix the first upstream flange 22 between them, the second upstream flange 24 for absorbing forces and the flange 26b of the air diffuser 26.
• fixing means 40 for example bolted connections
• the turbine ring assembly 2 further comprises upstream axial pins 42 which are intended to hold the first upstream flange 22 of the ring support structure against the upstream lug 16 of the ring sectors 10. These upstream pins 42 are regularly distributed around the longitudinal axis XX of the ring.
• control of the clearance at the top of the turbine blades 8 can be achieved by varying the thicknesses of the turbine casing 32 or by providing the latter with pilot bosses (not shown in the figures).

Applications Claiming Priority (2)

Publications (1)

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Family Applications (1)

Country Status (6)

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Family Cites Families (15)

• 2019
  • 2019-05-03 FR FR1904663A patent/FR3095668B1/fr active Active
• 2020
  • 2020-04-03 JP JP2021564987A patent/JP2022531385A/ja active Pending
  • 2020-04-03 US US17/604,904 patent/US20220195894A1/en active Pending
  • 2020-04-03 EP EP20715092.1A patent/EP3963184A1/de active Pending
  • 2020-04-03 WO PCT/EP2020/059592 patent/WO2020224891A1/fr unknown
  • 2020-04-03 CN CN202080032798.1A patent/CN113811670A/zh active Pending

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