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
  • 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
  • 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
  • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
  • F01D11/005—Sealing means between non relatively rotating elements
• • 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
  • F05D2240/00—Components
  • F05D2240/55—Seals
• • 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

Definitions

• TITLE Annular assembly for turbomachine turbine
• This document relates to a sealing member for a turbomachine, and more particularly for a low pressure turbine.
• a turbomachine consists, upstream to downstream, of a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine.
• the low-pressure turbine makes it possible to harness and release the power generated in a combustion chamber located upstream of said low-pressure turbine.
• Two air flows are to be considered within a turbomachine: a primary annular flow and a secondary annular flow.
• the secondary flow bypasses the entire hot part of the turbomachine.
• the other flow called the primary flow passes through the entire turbomachine from the low pressure compressor to the low pressure turbine and is surrounded by the secondary air flow. This primary flow circulates within a primary vein.
• a turbine comprises an alternation of annular rows of stator vanes and mobile vanes arranged within a housing.
• Figure 1 illustrates part of such a turbine 1 and shows an upstream distributor 2 and an annular row of downstream blades 4.
• the distributor 2 comprises an external annular platform 6 fixed to a radial blade 8.
• the row of movable blades 4 comprises an external annular platform 10 from which wipers 12 extend radially outwardly cooperating in sealing with an abradabe 14, for example of the honeycomb type belonging to a sectorized ring carried by the housing 16 as illustrated in FIG. 1.
• the circumferentially sectorized ring comprises a ring 18 bearing on its radially internal face the abradable 14.
• the ring also comprises a thermal deflector 20 carried by the upstream end of the ring 18.
• the ring 18 is fixed to the turbine housing 16. by a clamping tab 22 in the form of a solid C of the upstream end of an external platform of the distributor arranged downstream of the movable wheel.
• the upstream end of the ring comprises a C-shaped member 24 for fixing the ring on a cylindrical rail 26 of the housing 16 and on a radial arm 28 of the upstream distributor 2.
• the deflector 20 is attached to an upstream edge 30 of the ring 18 and extends radially inward.
• the present document aims to remedy these drawbacks in a reliable, efficient and inexpensive manner.
• annular assembly for a turbine engine, in particular an aircraft, said annular assembly extending along an axial direction X and comprising:
• paddle wheel being surrounded by a circumferentially sectorized ring and carried by the outer casing and formed of a ring arranged radially outside the paddle wheel and an annular deflector carried by an upstream edge of the ring and extending radially inwards from said upstream edge of the crown characterized in that it comprises sealing members between two circumferentially adjacent ring sectors, these sealing members comprising first circumferential sealing means between two circumferentially consecutive deflector sectors.
• This sealing member provides better aerothermal sealing between the thermal deflector sectors.
• the seal provides thermal protection of the crankcase by preventing leakage of hot gases from combustion at the circumferential junctions of the heat deflector sectors.
• the first circumferential sealing means can be arranged at the junction between two circumferentially consecutive deflector sectors.
• the sealing members may comprise second circumferential sealing means between two circumferentially consecutive crown sectors, these second sealing means being integral with the first sealing means.
• the second sealing means make it possible to prevent combustion gas leaks between two circumferentially consecutive crown sectors.
• the securing of the second sealing means with the first sealing means makes it possible to facilitate the assembly of said sealing member.
• the circumferential sealing between two crown sectors is thus produced simultaneously with the sealing between two circumferentially consecutive deflector seteurs, which avoids omissions in assembly.
• the first sealing means may comprise a wall element applied from downstream to the circumferentially facing ends of two circumferentially consecutive deflector sectors.
• the design of the first sealing means as a wall element eliminates doubts about the presence of the sealing element during an endoscopic inspection. This design also eliminates any risk of forgetting when fitting the sealing members, but also the risk of making a mistake in the mounting direction. The shape of these components thus achieves a keying when they are mounted between two ring sectors.
• the second sealing means may comprise at least a first wafer and a second wafer disjoint and connected to each other to the first sealing means, the first wafer and the second wafer being engaged in a slot of one edge. of a first crown sector and for another part in a slot of a circumferentially facing edge of a second circumferentially adjacent crown sector.
• Each sealing member may include a first junction element connecting a first plate to the wall element, this first junction element being interposed circumferentially between two edges of circumferentially adjacent deflector sectors.
• Each sealing member may include a second junction element connecting a second plate to the wall element, this second junction element being interposed circumferentially between two edges of circumferentially adjacent crown sectors.
• first and second junction elements make it possible to impart robustness and solidity to said sealing member. These first and second junction elements make it possible to facilitate the mounting direction of said sealing member.
• first and second junction elements make it possible to mechanically hold the first sealing means to the second sealing means.
• the second junction element can be arranged radially on the outside of two edges of circumferentially adjacent deflector sectors.
• This document relates to a turbine for a turbomachine comprising a low pressure turbine comprising an annular assembly according to the aforementioned characteristics and a high pressure turbine, the outer casing of the low pressure turbine comprising an upstream annular flange for attachment to a downstream annular flange of a high pressure turbine outer casing.
• a turbomachine comprising an annular assembly of the aforementioned type.
• FIG. 1 shows a partial schematic half-view in axial section of a turbomachine module
• FIG. 2 shows a partial schematic half-view in axial section of a turbomachine module according to the invention
• FIG. 3 is a schematic perspective view of a sealing ring sector of the module of Figure 2, according to the invention.
• FIG. 4 is a schematic perspective view of two circumferentially consecutive ring sectors and a sealing member, according to the invention.
• FIG. 5 is a schematic perspective view of a sealing member mounted in a ring sector seen from the side, according to the invention.
• FIG. 6 is a schematic perspective view of a sealing member mounted in a ring sector seen from downstream, according to the invention.
• FIG. 7 is a schematic perspective view of a seal member as melted, according to the invention.
• a turbine comprises an upstream high pressure turbine and a downstream low pressure turbine.
• the high pressure turbine and the low pressure turbine each comprise an alternation of annular rows of stator vanes and mobile vanes arranged inside a casing.
• a first wheel of downstream mobile blades 4 is surrounded on the outside by a casing of the low pressure turbine 16a while an upstream outlet distributor 2 of the high pressure turbine is surrounded on the outside by a casing of the high pressure turbine.
• high pressure turbine 16b The distributor 2 comprises an outer annular platform 6 to which are connected the radially outer ends of the radial blades 8.
• a hooking lug 32 is at one end of said outer platform 6 of the distributor 2. The circumferential and axial retention of the distributor 2 is ensured by means of said tab hooking 32 which is engaged in an annular groove 33 of the high pressure turbine housing 16b, this annular groove 33 opening downstream.
• This high pressure turbine housing 16b is fixed at its downstream end by means of an annular flange 36 to an annular flange 38 of the upstream end of the low pressure turbine housing 16a.
• the annular flanges 36, 38 are positioned radially at the level of the annular space between the outlet distributor 2 of the high pressure turbine and the first movable wheel 4 of the low pressure turbine.
• the first impeller 4 is rotatably mounted about a longitudinal axis X in a ring attached to the outer casing 16a of the low pressure turbine.
• the sectored ring is formed of several ring sectors which are arranged circumferentially end to end and each carried by the outer casing 16a of the low pressure turbine.
• the downstream ends of the ring sectors are clamped radially by a C-shaped clamp 22, located downstream of the ring sectors.
• each ring sector comprises a ring sector 18 arranged radially outside the impeller 4 and an annular thermal deflector sector 20.
• the deflector sector 20 is generally z-shaped and has a substantially curved orientation.
• the deflector sector 20 comprises, from upstream to downstream, a wall sector extending radially inwardly 40, an annular wall sector 42 and a wall sector extending radially outwardly 44.
• the sector radially outwardly extending wall 44 is fixed by brazing to a downstream edge of a radial wall 46 of the crown sector 18.
• the annular wall sector 42 of the deflector sector 20 circumferentially follows the direction of extension of the sector. 18.
• the deflector sector 20 has a circumferential extent substantially the same as that of the crown sector 18 and the abradable 14 so that the circumferential ends of the deflector sector 20 are substantially axially aligned with those of the crown sector 18.
• This deflector sector 20 may be an annular sheet metal sector.
• the crown sector 18 extends circumferentially and comprises an annular wall sector 48 whose inner face carries an abradable 14, a radial wall sector 46 extending radially inwardly connected to a cylindrical wall sector 50 engaged in an annular groove 34 carried by the annular flange 38 of the upstream end of the low pressure turbine housing 16a.
• the abradable 14 is of the honeycomb type and seals at the level of the blade wheel 4 by means of annular wipers 12 extending radially outwards from the outer annular platform 10 of the movable wheel 4 , in order to limit the passage of air radially to the outside of the movable wheel 4.
• sealing tongues 52 are inserted at the level of longitudinal slots located in the longitudinal edges of the circumferential ends of the annular wall sector 48 of the crown sector 18. These sealing tongues 52 are each inserted, on a first side, into a slot of a longitudinal edge of a circumferential end of an annular wall sector 48 a first crown sector 18 and a second side of said sealing tongue 52, in a slot of a longitudinal edge of a circumferential end of an annular wall sector 48 of a second crown sector 18 circumferentially consecutive. These sealing tabs 52 have a generally flat and elongated shape.
• the radial edges of the circumferential ends of the radial wall sector 46 of the crown sector 18 and the longitudinal edges of the circumferential ends of the cylindrical wall sector 48 of the crown sector 18 have slots 54, 55 for housing d. 'a sealing member.
• the sealing member 56 comprises first circumferential sealing means 58 between two circumferentially consecutive deflector sectors 20, that is to say at the junction between two deflector sectors 20 circumferentially consecutive. It can also include second sealing means 60 between two circumferentially consecutive crown sectors 18.
• the first sealing means 58 comprise a wall element 62 comprising a downstream radial wall 64 extending radially outwards and the radially inner end of which is connected to an inclined wall 66 converging towards the axis of rotation going towards upstream, this inclined wall 66 being connected at its upstream end to an upstream radial wall 68 extending radially inward.
• This wall element 62 is shaped identically to the thermal deflector sectors 20 so as to be able to perfectly match the three-dimensional shape of two edges of circumferentially facing deflector sectors 20.
• the second sealing means 60 between two circumferentially consecutive crown sectors 18 comprise a first plate 70 and a second plate 72 which are disjointed. These first 70 and second 72 plates have a planar, substantially rectangular shape.
• the first plate 70 is able to be inserted on a first side into a slot 54 of an edge of a circumferential end of a cylindrical wall sector 50 of a first crown sector 18 and of a second side. , opposite the first side, in a slot 54 of an edge of a circumferential end of a cylindrical wall sector 50 of a second circumferentially consecutive crown sector 18.
• the second plate 72 is able to be inserted on a first side into a slot 55 of a radial edge of a circumferential end of a radial wall sector 46 of a first ring sector 18 and of a second side, opposite to the first side, in a slot 55 of a radial edge of one end circumferential of a radial wall sector of a second circumferentially consecutive crown sector 18.
• the sealing member 56 comprises a first junction element 74 connecting the first plate 70 to the inclined wall 66 converging towards the axis of rotation going upstream of the wall element 62.
• the first junction element 74 extends radially with a substantially frustoconical shape with a section widening radially inwards. This first junction element 74 is fixed at its radially inner end to the wall element 62 and its radially outer end to the inner face of the first plate 70.
• the first junction element 74 extends radially and longitudinally.
• the seal member 56 also includes a second junction element 76 connecting the second plate 72 to the downstream radial wall 64 extending radially outward from the wall member 62.
• the second junction member extends longitudinally with a substantially rectangular shape.
• This second junction element 76 is fixed at its radially inner end to the wall element 62 and its radially outer end to the inner face of the second plate 72.
• the second junction element 76 can extend radially up to a third. a radial length of the second wafer 72 from an inner end of the second wafer 72.
• the first junction element 70 and the second junction element 72 are flat and between 0.2 and 0.4 mm thick. This thickness is of the same order of magnitude as that of the first and second sealing means.
• This sealing member 56 can be manufactured by additive manufacturing. Said sealing member 56 is mounted in circumferential translation, the radially outer face of said wall element 62 conforming to the shape of the downstream face of the thermal deflector sector 20, the first 70 and second 72 plates being inserted into said slots 54, 55 of housings of two circumferentially consecutive crown sectors 18.
• the sealing member 56 makes it possible to prevent combustion gases from passing through the circumferential and radial clearances present between two sectors of circumferentially consecutive rings 18 and between two sectors of consecutive deflectors 20.
• the sealing member 56 makes it possible to block the air in the interstice between the first 70 and the second 72 disjointed wafer.
• the securing of the second sealing means 60 with the first sealing means 58 makes it possible to facilitate the assembly of said sealing member 56.
• the circumferential sealing between two crown sectors 18 is thus achieved simultaneously with the sealing. between two seteurs 20 circumferentially consecutive deflector which avoids omissions in assembly.
• the design of the first sealing means 58 as a wall element 62 eliminates doubts about the presence of the sealing element 56 during an endoscopic inspection.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)

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• 2020
  • 2020-06-11 FR FR2006131A patent/FR3111382B1/fr active Active
• 2021
  • 2021-06-10 EP EP21737109.5A patent/EP4165286B1/de active Active
  • 2021-06-10 WO PCT/FR2021/051043 patent/WO2021250357A1/fr unknown
  • 2021-06-10 US US18/009,952 patent/US12018576B2/en active Active
  • 2021-06-10 CN CN202180048776.9A patent/CN115917120A/zh active Pending

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