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
  • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
  • F01D11/20—Actively adjusting tip-clearance
  • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
• • 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
  • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
  • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
• • 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
  • F01D9/00—Stators
  • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
  • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
• • 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
  • F05D2230/30—Manufacture with deposition of material
  • F05D2230/31—Layer deposition
• • 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

Definitions

• TITLE Ring for a turbine engine or turbine engine turbine
• the invention relates to a ring for a turbomachine or turbine engine turbine, intended to surround a bladed wheel of a turbine rotor.
• a turbomachine conventionally comprises, from upstream to downstream in the direction of gas flow, a fan, a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine.
• the air from the blower is divided into a primary flow flowing in a primary annular vein, and a secondary flow flowing in a secondary annular vein surrounding the primary annular vein.
• the low-pressure compressor, the high-pressure compressor, the combustion chamber, the high-pressure turbine and the low-pressure turbine are provided in the primary stream.
• the high pressure turbine rotor and the high pressure compressor rotor are rotatably coupled through a first shaft to form a high pressure body.
• the rotor of the low pressure turbine and the rotor of the low pressure compressor are coupled in rotation by means of a second shaft so as to form a low pressure body, the fan being able to be connected directly to the rotor of the low pressure compressor or by via an epicyclic gear train, for example.
• the rotors of high pressure and low pressure turbines have bladed wheels surrounded by a ring belonging to the stator.
• the radial clearances between the radially outer ends or tops of the blades and the radially inner surface of the ring delimiting the flow path of the hot gas stream should be limited. The definition of these clearances must in particular take into account the expansion phenomena of the parts in operation.
• the invention aims to remedy the aforementioned drawbacks in a simple, reliable and inexpensive manner.
• the invention relates to a one-piece ring for a turbomachine turbine, intended to surround a bladed wheel of a turbine rotor, said ring extending circumferentially around an axis and comprising an annular and continuous support part.
• radially external and a part delimiting a flow path of a gas flow, radially internal and comprising several angular segments distributed over the periphery and located adjacent to each other so as to form an annular part delimiting the vein, characterized in that circumferential clearances are formed between the circumferential ends of the adjacent segments located opposite each other, each segment being connected to the support part by means of a connection zone, an annular channel of circulation of cooling fluid being delimited radially between the external support part and the internal part delimiting the stream.
• annular cooling air circulation channel effectively cools the segments of the internal part, said segments being subjected to high temperatures.
• circumferential clearances between the segments makes it possible to limit radial expansions.
• Such a one-piece structure is moreover inexpensive, reliable and not bulky.
• the radially outer support portion is annular and continuous, that is, not segmented. In other words, the radially outer support portion extends in a single part over the entire circumference.
• connection zone can extend circumferentially over a shorter distance than the corresponding segment of the radially internal part delimiting the vein.
• the circumferential dimension of each sector of the radially internal part is for example greater than 5 times the circumferential distance of the corresponding connection zone.
• connection zone can be formed by a flat partition.
• Said partition may extend along a radial plane oriented in the axial direction.
• the ring may include sealing means between the internal and external parts, said sealing means being able to allow a flow of cooling air leakage from the channel.
• the sealing means make it possible to limit and control the leakage rate, the air from this leak entering, for example, the hot gas flow stream or the primary stream.
• the sealing means may include at least one annular seal mounted radially between the internal and external parts.
• the sealing means may include a first annular seal and a second annular seal located respectively at a first axial end and at a second axial end of the channel.
• Each annular seal may be engaged in part in a groove formed in the internal part and / or in a groove formed in the external part.
• Each annular seal may have a polygonal section shape, for example square, or a rounded section, for example circular or oval.
• the grooves can have complementary shapes to the annular seals.
• the sealing means may include at least one labyrinth seal.
• the labyrinth seal may have one or more radial annular flanges extending from the inner part, interposed axially between one or more radial annular flanges extending from the outer part, or vice versa.
• the sealing means may include a first labyrinth seal and a second labyrinth located respectively at a first axial end and at a second axial end of the channel.
• the ring may have air inlet holes allowing cooling air to flow into the channel.
• the air inlets can extend radially.
• the air inlet openings can be made in the external support part.
• the air inlet openings can be evenly distributed around the periphery.
• the air inlet openings may have a polygonal section, or a rounded section, for example circular.
• Each segment may include a first circumferential end comprising an annular bearing flange extending circumferentially and able to come to bear on the radially outer surface of a second circumferential end of an adjacent segment.
• the support rim can thus be located on the side of the cooling air circulation channel.
• Each segment may include a first zone extending circumferentially between the first circumferential end of the segment and the connecting zone and a second zone extending circumferentially between the second circumferential end of the segment and the connecting zone, the circumferential dimension of the first zone being smaller than the circumferential dimension of the second zone.
• the ratio of the circumferential dimension of the first zone to the circumferential dimension of the second zone is for example between 1 and 10.
• Such a structure ensures that, in operation, the expansion effects press against the radially outer surface of the second circumferential end of each segment resting on the corresponding supporting rim of the adjacent segment.
• At least some of the air inlet ports may be provided at at least one bonding area.
• the outer part may have a thickness greater than the thickness of the inner part, for example 1, 2 to 3 times greater than the thickness of the inner part. This makes it possible to ensure better control of the clearances and better possible retention of the blades in the event of accidental release.
• the ring can be made by additive manufacturing.
• Such a method makes it possible to produce a ring of complex structure, in a single piece, not requiring numerous and expensive additional machining or assembly steps, so as to directly obtain a finished or almost finished ring, ready to be used. .
• the additive manufacturing process is, for example, sintering or selective melting of powder, for example using a laser beam or an electron beam.
• Such a method comprises a step during which is deposited, on a manufacturing platform, a first layer of powder of a metal or a metal alloy of controlled thickness, then a step consisting in heating with a heating means (a laser beam or an electron beam) a predefined zone of the powder layer, and to proceed by repeating these steps for each additional layer, until obtaining, slice by slice, the final part.
• a heating means a laser beam or an electron beam
• the invention also relates to a turbine, for example a high pressure turbine, a turbomachine or a turbine engine, or an aircraft comprising such a ring.
• a turbine for example a high pressure turbine, a turbomachine or a turbine engine, or an aircraft comprising such a ring.
• the turbomachine may be an aircraft turbomachine.
• the turbine engine may be a helicopter turbine engine.
• FIG. 1 is a perspective view with partial cut away, of part of a ring according to a first embodiment of the invention
• FIG. 2 is a view corresponding to Figure 1, in which the annular seals are not shown
• FIG. 3 is a schematic view showing a section along a radial plane, of part of the ring,
• FIG. 4 is a view corresponding to Figure 3, illustrating a second embodiment of the invention
• FIG. 5 is a perspective view of part of a ring according to a third embodiment of the invention.
• FIG. 6 is a perspective view of part of a ring according to a fourth embodiment of the invention.
• Figures 1 to 3 illustrate a ring 1 for a turbomachine or turbine engine turbine, for example a high pressure or low pressure turbine, according to a first embodiment of the invention.
• the ring 1 is intended to surround a bladed wheel 2 of a turbine rotor.
• the bladed wheel comprises vanes 3 regularly distributed around the circumference, each vane comprising a blade 4 and a radially internal platform 5, internally delimiting a flow passage 6 of a gas flow.
• the radially outer ends 7 of the vanes 3 are located near the ring 1.
• the ring 1 extending circumferentially around the axis of rotation of the rotor and comprises a continuous annular support part 9, radially outer, and a radially inner part 10 outwardly delimiting the vein 6.
• the outer part 9 comprises an axially median cylindrical zone 11 and at least one fixing zone 12 intended to be fixed to a stator of the turbomachine.
• Said internal part 10 comprises several angular segments 13 distributed over the periphery and located adjacent to each other so as to form an annular part delimiting the vein 6.
• Each segment 13 is connected to the support part 9 by the intermediate of a connecting zone 14 extending radially.
• the number of segments may vary depending on the applications and is for example between 3 and 30.
• An annular channel 15 for circulating cooling fluid is delimited radially between the external part 9 and the internal part 10 delimiting the vein 6.
• the cylindrical zone 11 of the radially outer part 9 comprises air inlet openings 16 regularly distributed over the circumference and opening radially into the channel 15.
• the air inlet openings 16 each have a rectangular or square section. Of course, other shapes can be used.
• Each segment 13 comprises a first circumferential end 17 comprising an annular bearing flange 18 extending circumferentially and able to come to bear, during operation of the turbomachine or of the turbine engine, on the radially outer surface of a second circumferential end 19 of an adjacent segment 13.
• the support rim 18 is thus located on the side of the cooling air circulation channel 15.
• Each segment 13 comprises a first zone 20 extending circumferentially between the first circumferential end 17 of the segment 13 and the connecting zone 14 and a second zone 21 extending circumferentially between the second circumferential end 19 of the segment 13 and the connecting zone 14.
• the circumferential dimension of the first zone 20 is smaller than the circumferential dimension of the second zone 21.
• the ratio of the circumferential dimension of the first zone 20 to the circumferential dimension of the second zone 21 is for example between 1 and 10.
• the external part 9 may have a thickness greater than the thickness of the internal part 10, for example 1, 2 to 3 times greater than the thickness of the internal part 10. This makes it possible so as to ensure better control of the clearances and better retention of the blades in the event of accidental release.
• the ring 1 further comprises sealing means comprising a first annular seal
• Each annular seal 22, 23 is engaged in part in a groove 24 formed in the internal part 10 and in a groove 25 formed in the external part 9.
• the grooves 24, 25 have complementary shapes to the annular seals 22, 23.
• the ring 1 can be produced by additive manufacturing, in particular by sintering or selective powder melting, for example using a laser beam or an electron beam.
• FIG. 4 illustrates a second embodiment in which some of the air inlet openings 16 are provided at the level of the connection zones 14, so as to effectively cool each connection zone 14 concerned.
• FIG. 5 illustrates a third embodiment in which the circumferential dimension of the first zone 20 is greater than the circumferential dimension of the second zone 21.
• the ratio of the circumferential dimension of the first zone 20 to the circumferential dimension of the second zone 21 is for example between 1 and 10.
• FIG. 6 illustrates a fourth embodiment in which the sealing means comprise a first labyrinth seal 26 and a second labyrinth 27 located respectively at the level of the first axial end and the second axial end of the channel 15.
• Each labyrinth seal 26, 27 comprises one or more radial annular flanges 27 extending from the inner part 10, interposed axially between one or more radial annular flanges 28 extending from the outer part 9, or vice versa.

Landscapes

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

Applications Claiming Priority (2)

Publications (2)

Family

ID=69375409

Family Applications (1)

Country Status (6)

Families Citing this family (2)

Family Cites Families (14)

• 2019
  • 2019-08-05 FR FR1908957A patent/FR3099787B1/fr active Active
• 2020
  • 2020-08-04 WO PCT/FR2020/051433 patent/WO2021023945A1/fr unknown
  • 2020-08-04 EP EP20760497.6A patent/EP4010565B1/de active Active
  • 2020-08-04 US US17/630,454 patent/US20220251963A1/en active Pending
  • 2020-08-04 CN CN202080056482.6A patent/CN114207254B/zh active Active
  • 2020-08-04 PL PL20760497.6T patent/PL4010565T3/pl unknown

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