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
  • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and 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
  • 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
• • 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
  • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
  • 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
  • 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
  • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
  • F05D2220/3212—Application in turbines in gas turbines for a special turbine stage the first stage of a turbine
• • 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
  • F05D2240/12—Fluid guiding means, e.g. vanes
  • F05D2240/126—Baffles or ribs
• • 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
  • F05D2240/12—Fluid guiding means, e.g. vanes
  • F05D2240/127—Vortex generators, turbulators, or the like, for mixing
• • 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
  • F05D2250/10—Two-dimensional
  • F05D2250/18—Two-dimensional patterned
  • F05D2250/185—Two-dimensional patterned serpentine-like

Definitions

• This description relates to a high-pressure gas turbine for a turbomachine. It also relates to a turbomachine comprising such a gas turbine.
• a turbomachine 10 of the turbofan turbojet type comprises, from upstream to downstream in the direction of the circulation of the gases inside the turbomachine 10, a fan 14, a low-pressure compressor 16, a high-pressure compressor 18, a combustion chamber 20, a high-pressure turbine 22, a low-pressure turbine 24 and an exhaust nozzle 26.
• the low-pressure compressor 16 , the high-pressure compressor 18, the combustion chamber 20, the high-pressure turbine 22, the low-pressure turbine 24 and the exhaust nozzle 26 are arranged radially inside a casing 12 which delimits, radially outwards, an annular stream 11 of the turbine engine 10 in which the gases flow from upstream to downstream.
• the high-pressure compressor 14 and the low-pressure compressor 18 are respectively connected to a high-pressure turbine 22 and a low-pressure turbine 24 by a respective shaft 15, 17 extending along the longitudinal axis X of rotation of the shafts of the turbomachine 10.
• orientation qualifiers such as “longitudinal”, “radial” and “circumferential” are defined with reference to the longitudinal axis.
• upstream and downstream are defined with respect to the direction of circulation of the gases within the turbomachine.
• the high-pressure turbine 22 comprises a plurality of stages, one of them being partially shown in Figure 2, each comprising a distributor 30 and a moving wheel 40 mounted downstream of the distributor 30.
• the distributor 30 comprises an internal annular platform 34 and an annular row of fixed vanes 32. Each fixed vane 32 extends radially in the annular vein 11 and is connected, radially inside to the internal annular platform 34
• the distributor 30 generally comprises an annular radial flange 36 for attachment to the casing 5.
• the moving wheel 40 comprises an annular row of moving blades 42 carried by a disc 41 comprising a plurality of cells on its outer periphery, each receiving a foot 46 of a blade 42.
• Each moving blade 42 further comprises a sector of internal annular platform 44 of the impeller 40 from which extends a blade 42' radially outwards through the annular vein 11.
• the internal annular platform 44 thus comprises a plurality of sectors arranged circumferentially end to end around the longitudinal axis X.
• the internal annular platform 34 of the distributor 30 and the internal annular platform 44 of the impeller 40 each delimit, radially inwards, the annular vein 11.
• the gases flowing in the annular stream 11 are introduced into a space formed longitudinally between the internal annular platform 34 of the distributor 30 and the internal annular platform 44 of the impeller 40, which reduces the performance of the turbomachine 10.
• a baffle is formed in the longitudinal space between the internal annular platform 34 of the distributor 30 and the internal annular platform 44 of the movable wheel 44, limiting the leak, radially inward, gases flowing in the annular vein 11.
• the annular part 50 has a cavity 51 in which is housed an elastic member 51'.
• a purge air flow taken from the low-pressure compressor 14 and/or the high-pressure compressor 16, is directed through an annular purge cavity 62 towards the space formed longitudinally between the internal annular platform 34 of the distributor 30 and the internal annular platform 44 of the impeller 4.
• This purge air flow thus makes it possible to redirect the gases that have entered the purge cavity 62 towards the annular vein 11.
• a high-pressure gas turbine is proposed for a turbomachine extending around a longitudinal axis, the turbine comprising:
• a distributor comprising an internal annular platform and an annular row of fixed vanes, each fixed vane being connected, radially inwards, to the internal annular platform,
• the upstream sealing part comprising an annular part from which a downstream annular spoiler extends longitudinally downstream, said annular part having a radially outer part comprising an upstream annular cavity, said upstream cavity being open at the level of a radially outer annular clearance, delimited between the downstream face of the distributor and the upstream sealing part,
• the downstream sealing part comprising a first upstream spoiler arranged, at least in part, radially inside the internal annular platform of the distributor and radially outside the downstream spoiler of the upstream sealing part, said part downstream sealing further comprising a second upstream spoiler arranged, at least in part, radially inside the downstream spoiler, the downstream spoiler extending, at least in part, radially opposite the first and second upstream spoilers, the first and second upstream spoilers and the downstream spoiler defining a double baffle.
• the double baffle generates a pressure drop limiting the rate of leakage of gas from the stream radially inwards, between the distributor and the annular row of blades, also limiting the air purge rate required . Furthermore, the upstream annular cavity also makes it possible to limit such a leak rate, by creating an additional pressure drop.
• a so-called annular part may comprise a plurality of sectors arranged circumferentially end to end around an axis, in particular at 360° around said axis.
• a so-called annular part can also be in one piece, that is to say formed from a single part and not from sectors.
• the first upstream spoiler, the second upstream spoiler and/or the downstream spoiler may be, at least in part, cylindrical.
• the first upstream spoiler may have a radially outer face which is of frustoconical shape with a section decreasing towards the upstream extending over at least a first longitudinal portion.
• Such a shape makes it easier to evacuate the purge air and the gases out of the cavity located between the distributor and the annular row of moving blades towards the annular passage. Moreover, such a characteristic makes it possible to adapt the direction in which the gases mixed in the annular vein are reintroduced into the annular vein to minimize the disturbances on the gases flowing in the annular vein.
• the annular space may extend between the first and second upstream spoilers is delimited by a radially inner surface of the first upstream spoiler, a radially outer surface of the second upstream spoiler and a concave upstream surface of the downstream sealing part .
• the radially inner surface of the second upstream spoiler can be connected to an upstream face of the downstream sealing part by a concave rounded portion.
• the upstream annular cavity of the upstream sealing part can be delimited longitudinally by a downstream radial face of the distributor and by a downstream radial wall of the upstream sealing part extending radially outwards from the annular part of the upstream sealing piece part, and delimited radially by an annular end surface located at the radially outer end of said annular part and by a longitudinal wall extending longitudinally upstream from the radially outer end of the downstream radial wall, said outer annular clearance being formed longitudinally between the downstream radial face of the distributor and the upstream end of said longitudinal wall.
• Said annular end surface may include a frustoconical zone widening downstream.
• the radially inner annular face of the inner annular platform of the dispenser may have at least one concave-shaped zone.
• the distributor may further comprise a radial annular flange extending radially inwards from the internal annular platform, the upstream sealing part being attached and fixed to the radial annular flange.
• the upstream sealing part can be made in one piece with the radial annular flange of the distributor.
• downstream sealing piece can be attached or fixed to a disk of the annular row of moving blades, or be integral with the disk.
• the annular row of moving blades may include an inner annular platform, said first upstream spoiler extending from an upstream end of the inner annular platform.
• Each moving blade of an annular row of moving blades may comprise a sector of the internal annular platform, said sectors being arranged circumferentially end to end.
• Each moving vane may include a blade extending radially outward from the respective sector of the inner annular platform.
• Each moving blade may include a blade root extending radially inward from the respective sector of the inner annular platform.
• Each blade root can be received in an associated cell formed on the outer periphery of the disc.
• each moving blade is formed in one piece with the respective sector of the internal annular platform.
• This document also relates to a turbomachine comprising a high-pressure gas turbine of the aforementioned type.
• FIG. 1 already described above, is a partial schematic sectional view of a prior art turbomachine
• FIG. 2 is a partial schematic sectional view of a high-pressure turbine of the turbomachine of FIG. 1;
• FIG. 3 is a partial schematic view in perspective and in section of a high-pressure turbine according to one embodiment of this document;
• FIG. 4 is a partial schematic sectional view of the turbine of FIG. 3;
• FIG. 3 and 4 represent, according to a first embodiment, partially a high-pressure turbine of a turbomachine of longitudinal axis X.
• the high-pressure turbine comprises a plurality of stages each comprising a distributor 30 and a movable wheel 40 mounted downstream of the distributor 30.
• the nozzle 30 comprises an annular row of fixed vanes 32.
• Each fixed vane 32 is connected, radially inwardly, to an internal annular platform 34 of the nozzle 30.
• Each fixed vane 32 extends radially towards the inside. exterior from the internal annular platform 34.
• Each fixed vane 32 is connected, radially outwards, to an external platform 34′ connected to an external casing of the high-pressure turbine.
• each fixed vane 32 extends radially inside the annular vein 11.
• the distributor 30 further comprises a radial annular flange 36 extending radially inward from the internal annular platform 34.
• the distributor 30 can be connected to an internal turbomachine casing via the radial annular flange 36.
• the rotor 40 comprises an annular row of rotor blades 42 carried by a disc 41.
• the mobile wheel 40 comprises an internal annular platform 44.
• Each mobile blade 42 of the mobile wheel 40 comprises a sector of the internal annular platform 44, the sectors being arranged circumferentially end to end around the longitudinal axis X.
• An annular face radially outer 44a of the inner annular platform 44 delimits, radially inwards, the annular vein 11 at the level of the moving wheel 40 of the turbine.
• Each moving blade 42 comprises a blade 42' extending radially outwards in the annular vein 11 from the respective sector of the internal annular platform 44.
• the impeller 40 also comprises a downstream sealing piece 43 attached and fixed to an upstream radial surface of the disc 41 and of the area comprising the platform 44.
• the downstream sealing piece 43 may be made of with disc 41 .
• the downstream sealing part 43 comprises a first upstream annular spoiler 47 which is annular and which extends longitudinally upstream at the level of the radially outer end of the downstream sealing part 43.
• the first upstream annular spoiler 47 is arranged, here in part, radially inside the internal annular platform 34 of the distributor 30.
• the first upstream annular spoiler 47 is arranged radially inside of the internal annular platform 34 of the distributor 30 and, in part, radially opposite the internal annular platform 34 of the distributor 30.
• the upstream end of the first upstream spoiler 47 is located longitudinally further upstream than the end downstream of the internal platform 34.
• the first upstream annular spoiler 47 has a radially outer annular face 47a which is of frustoconical shape with a section decreasing towards the upstream and which extends over a first longitudinal portion of the first upstream annular spoiler 47.
• the first portion of the spoiler upstream annular 47 is, here in part, radially opposite the internal annular platform 34 of the distributor 30.
• the radially outer annular face 47a of the first portion of the upstream annular spoiler 47 is here connected to the radially outer annular face 44a of the internal annular platform 44 of the mobile wheel 40, in particular by a rounding.
• downstream sealing part 43 comprises a second upstream annular spoiler 48, extending longitudinally downstream and located radially inside the first upstream spoiler 47.
• the annular space extending between the first and second upstream spoilers 47, 48 is delimited by a radially inner surface 47b of the first upstream spoiler 47, a radially outer surface 48a of the second upstream spoiler 48 and a concave upstream surface 43a of the downstream sealing piece 43.
• the second upstream spoiler 48 comprises a radially internal surface 48b which is connected to an upstream face of the downstream sealing part 43 by a concave rounded portion 49.
• the high-pressure turbine further comprises an upstream sealing piece 50, which here is annular, applied against a downstream face 36a of the distributor 30.
• the upstream sealing piece 50 is attached here and fixed to the annular flange 36.
• the upstream sealing part 50 comprises an annular part 52 applied against a downstream face 36a of the radial annular flange 36 of the distributor 30.
• the annular part 52 of the upstream sealing part 50 can be fixed , for example by bolting, to the radial annular flange 36 of the distributor 30.
• the upstream sealing part may be an integral part of the casing of the high-pressure turbine or of the flange 36.
• the upstream sealing part 50 comprises a cavity 51 in which is housed an elastic member 51'.
• the upstream sealing piece 50 includes a downstream spoiler 54 which is annular.
• the first downstream annular spoiler 54 is arranged, here in part, radially inside the first upstream annular spoiler 47 and radially outside the second upstream spoiler 48 of the downstream sealing part 43. Furthermore, the downstream end of the downstream spoiler 54 is located longitudinally further downstream than the upstream ends of the first and second upstream spoilers 47, 48.
• the spoilers 54, 47, 48 form a double baffle, and created pressure drops limiting the gas flow capable of flowing radially through said double baffle.
• the upstream sealing part 50 further comprises an upstream annular cavity 56, said upstream cavity 56 being open at the level of a radially outer annular clearance 58, delimited between the downstream face 36a of the distributor 30 and the part of upstream sealing 50.
• the upstream annular cavity 56 of the upstream sealing part 50 can be delimited longitudinally by the downstream radial face 36a of the distributor 30 and by a downstream radial wall 60 of the upstream sealing part 50 extending radially towards the outside from the annular part 52 of the upstream sealing piece part 50, and delimited radially by an annular end surface 52a located at the radially outer end of said annular part 52 and by a longitudinal wall 62 extending longitudinally upstream from the radially outer end of the downstream radial wall 60.
• the outer annular clearance 58 is formed longitudinally between the downstream radial face 36a of the distributor 30 and the upstream end of said longitudinal wall 62.
• Said annular end surface 52a may comprise a frustoconical zone 52b widening downstream.
• the upstream annular sealing part 50 can be made in one piece with the radial annular flange 36 of the distributor 30.
• the annular sealing part 50 may comprise a plurality of sectors arranged circumferentially end to end around the longitudinal axis X.
• the radially internal annular face 34a of the internal annular platform 34 of the distributor 30 may have a concave-shaped zone 34b which is arranged radially opposite the upstream annular spoiler 47 and/or the longitudinal wall 62.
• the turbine further comprises an annular purge cavity 62 located longitudinally between the upstream sealing part 50 and the downstream sealing part 43, or more generally between the distributor 30 and the impeller 40, and radially to the inside the second upstream spoiler 48.
• a free space 64 is formed, longitudinally, between the internal annular platform 34 of the distributor 30 and the internal annular platform 44 of the impeller 40.
• the internal annular platform 34 of the distributor 30 and the upstream annular spoiler 47 of the mobile wheel 40 together define a clearance or flow conduit between the annular vein 11 and the double baffle 47, 48, 54.
• the double baffle 47, 48, 54 and the upstream cavity 56 make it possible to generate pressure drops limiting the progression of the flow of hot gases from the stream 11 radially inwards, towards the annular purge cavity 62, also limiting the amount of purge air needed to prevent damage to the turbine.

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

Applications Claiming Priority (2)

Publications (2)

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ID=80122422

Family Applications (1)

Country Status (5)

Family Cites Families (7)

• 2021
  • 2021-09-27 FR FR2110131A patent/FR3127519B1/fr active Active
• 2022
  • 2022-09-02 WO PCT/FR2022/051662 patent/WO2023047033A1/fr not_active Ceased
  • 2022-09-02 CN CN202280061887.8A patent/CN117940652A/zh active Pending
  • 2022-09-02 US US18/694,555 patent/US12492644B2/en active Active
  • 2022-09-02 EP EP22786057.4A patent/EP4409113B1/de active Active

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