EP3351736B1 - Virole interne de compresseur de turbomachine axiale - Google Patents

Virole interne de compresseur de turbomachine axiale Download PDF

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Publication number
EP3351736B1
EP3351736B1 EP18159641.2A EP18159641A EP3351736B1 EP 3351736 B1 EP3351736 B1 EP 3351736B1 EP 18159641 A EP18159641 A EP 18159641A EP 3351736 B1 EP3351736 B1 EP 3351736B1
Authority
EP
European Patent Office
Prior art keywords
turbomachine
shroud
rotor
ferrule
roughness
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP18159641.2A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3351736A1 (fr
Inventor
Jean-François Cortequisse
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aero Boosters SA
Original Assignee
Safran Aero Boosters SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aero Boosters SA filed Critical Safran Aero Boosters SA
Publication of EP3351736A1 publication Critical patent/EP3351736A1/fr
Application granted granted Critical
Publication of EP3351736B1 publication Critical patent/EP3351736B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • 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
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2300/40—Organic materials
    • 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

Definitions

  • the field of the present invention is that of axial turbomachines. More particularly, the invention addresses the internal ferrules connected to a row of stator vanes.
  • An internal ferrule is known for making it possible to delimit the primary flow of an axial turbomachine, it forms an annular wall which delimits the interior of the fluid stream. Thanks to its external surface, it helps guide the flow during its expansion in a turbine, or its compression in a compressor.
  • an internal ferrule can be mounted on the internal ends of vanes arranged in an annular row, themselves linked to an external casing.
  • the ferrule has recesses for the introduction of the ferrule fixing ends.
  • the internal ferrule is also intended to ensure a seal with the rotor around which it is placed. To this end, it has a layer of abradable material cooperating by abrasion with wipers formed outside the rotor. In operation, the wipers come close to the abradable, possibly creating circular notches there, so that a dynamic seal is ensured.
  • each internal ferrule comprises a tubular wall in which are provided rows of openings. These allow the introduction of the blade roots used for fixing between the ferrule and the blades.
  • Each opening has a lip which extends radially around it, ribs join the lips of the neighboring openings, the assembly making it possible to stiffen the ferrule.
  • the bending stiffness of the shell; in particular of its segments remains limited.
  • the main efforts are taken up by the branches of the U shape of the ferrule.
  • the openings can open further around the seals surrounding the blades, which degrades the seal.
  • the document EP1419849A1 discloses a method of repairing a turbine segment.
  • the segment comprises a pair of blades, the ends of which are linked to an internal ferrule.
  • the latter has two openings linked to the blades, the opposite edges of the openings being joined by a flange.
  • the invention aims to solve at least one of the problems posed by the prior art. More specifically, the invention aims to improve the sealing of a ferrule or a segment of a ferrule. The invention also aims to improve the rigidity of an assembly comprising a ferrule and vanes linked in openings formed in the ferrule. Another object of the invention is to stiffen an internal ferrule or an internal ferrule segment linked to stator vanes.
  • the subject of the invention is a turbomachine comprising a rotor and an internal ferrule around the rotor or an internal ferrule segment matching the rotor, the ferrule or the ferrule segment comprising a circular or semi-circular wall whose profile mainly extends axially, and a circular or semi-circular radial flange extend radially from the wall towards the inside, the flange having a circular or semi-circular surface whose profile extends mainly radially, said surface having asperities.
  • the rotor has annular ribs cooperating sealingly with the ferrule or the ferrule segment, the annular ribs of the rotor are each axially spaced from each radial flange of the ferrule or the ferrule segment. Furthermore, at least one or each radial flange comprises asperities which are formed over the majority of the radial height of the profile of revolution of one of the annular ribs of the rotor disposed opposite the associated radial flange.
  • At least one or each radial flange comprises at least one surface with asperities, said surface being generally perpendicular to the axis of revolution of the ferrule or of the ferrule segment.
  • the asperities form a pattern repeated on substantially an entire face of the corresponding radial flange.
  • the radial flange makes it possible to form a bridge which spans each opening.
  • the flange thus makes it possible to link the opposite edges of the openings so as to connect the edges.
  • This mechanical seal makes it possible to link the opposite edges through each opening, so as to prevent them from moving apart or approaching despite the material vacuum of the openings.
  • the invention makes it possible to improve the seal between a ferrule or a segment of a ferrule with openings in which stator vanes are fixed.
  • the invention thus provides a ferrule or a segment of ferrule which is both light, rigid, and economical to produce.
  • the terms internal or internal and external or external refer to a positioning relative to the axis of rotation of an axial turbomachine.
  • the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
  • the lateral direction is according to the circumference.
  • the figure 1 represents in a simplified manner an axial turbomachine.
  • the turbojet engine 2 comprises a first level of compression, called a low-pressure compressor 5, a second level of compression, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • a first level of compression called a low-pressure compressor 5
  • a second level of compression called a high-pressure compressor 6
  • a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power from the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 5 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator blades.
  • the rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until the inlet of the combustion chamber 8.
  • Reduction means can increase the speed of rotation transmitted to the compressors.
  • An inlet fan commonly designated as a fan or blower 16 is coupled to the rotor 12 and generates an air flow which is divided into a primary flow 18 passing through the various above-mentioned levels of the turbomachine, and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the outlet of the turbine.
  • the secondary flow can be accelerated so as to generate a thrust reaction.
  • the primary 18 and secondary 20 flows are annular flows, they are channeled by the casing of the turbomachine.
  • the casing has cylindrical or ferrule walls which can be internal and external.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 .
  • the compressor can be a low-pressure compressor 5.
  • the rotor 12 comprises a drum with an external annular wall which supports several rows of rotor blades 24, in this case three rows.
  • the low-pressure compressor 5 comprises several rectifiers, in this case four, which each contain a row of stator vanes 26.
  • the rectifiers are associated with the fan or with a row of rotor vanes to straighten the air flow, so as to convert the velocity of the flow into static pressure.
  • the stator vanes 26 extend essentially radially from an external casing 22, and can be fixed to it using a pin.
  • the casing 22 then forms an external support for the different rows.
  • the compressor 5 also includes internal ferrules 28 which are fixed to the radially internal ends of the stator vanes 26.
  • the internal ferrules 28 make it possible to guide and delimit the primary flow 18. They also provide a seal with the rotor 12 to avoid recirculation d air reducing the compression ratio of the compressor 5, and limiting the efficiency of the turbomachine.
  • Each ferrule 28 can form a ring of a turn, or be segmented angularly.
  • the figure 3 represents a portion of the compressor such as that of the figure 2 .
  • the internal ferrule 28 could be segmented.
  • the ferrule 28 has a profile of revolution with a portion extending mainly axially and which generates an axial wall 32.
  • the axial wall 32 may be generally tubular, and be substantially inclined relative to the axis of rotation 14 of the turbomachine; the latter may coincide with the general axis of symmetry 14 of the shell 28.
  • the ferrule 28 has a series of openings 34 arranged in an annular row. These openings 34 are crossed by the ends 30 of the vanes 26 to suspend the ferrule 28 there. Each opening 34 has opposite edges 36 in the direction of the row of openings 34, these edges 36 being placed opposite the faces of the associated dawn 26. One is facing the lower surface of the dawn, the other facing the upper surface.
  • the edges 36 can generally be conjugates; one is concave, the other convex.
  • the ferrule 28 further comprises at least one radial flange 38 which extends radially inwards from the axial wall 32.
  • the ferrule 28 may comprise several radial flanges 38 which each cut the openings 34. These radial flanges may be parallel, and distributed axially through the openings.
  • the ferrule 28 may comprise at least three radial flanges, including an upstream radial flange 40, a downstream radial flange 42, and a through radial flange 38 which passes through the openings 34, or central radial flange 38.
  • the through radial flange 38 is disposed axially between the upstream 40 and downstream 42 flanges.
  • the ferrule may have an “E” or comb profile.
  • the rotor 12 in particular its wall has annular ribs 44, also called “wipers". They extend radially and cooperate with the shell 28 in a sealed manner. They can cooperate by abrasion with layers of abradable material 46 where they dig grooves in the event of contact.
  • abradable material is meant a friable material in the event of contact.
  • the abradable layers 46 can be applied to the ends of the blades 30, and / or to the axial wall 32.
  • the abradable layers 46 and the radial flanges (38; 40; 42) form an alternation.
  • the radial flanges (38; 40; 42) can be combined in pairs to frame each annular rib 44 of rotor 12, possibly individually.
  • Each radial flange (38; 40; 42) comprises a profile of revolution which extends essentially radially, each flange profile extends over the majority of the radial height of each profile of the flange neighboring radial.
  • Each rib profile (38; 40; 42) extends over the majority of the radial height of the profiles of the adjacent annular ribs 44.
  • the faces of radial flanges (38; 40; 42) facing annular ribs 44 are covered with roughness 48 which amplifies turbulence 50, or vortices 50 opposing recirculations 52.
  • the figure 4 represents a section of the ferrule 28 and the stator vanes 26 along the axis 4-4 traced on the figure 3 .
  • the cutting plane passes through the radial flange 38 which crosses the openings 34.
  • the ferrule could be formed by segments of ferrule which would be placed end to end so as to form a circle.
  • the blades 26 extend radially from the ferrule 28 and pass through the openings 34. Their radial ends 30 are in radial abutment against the radial flange 38. Each blade end 30 has a radial abutment surface which cooperates with a abutment surface niche correspondent. Seals 54 extend radially into the openings 34 and pass through them, they come into contact with the radial flange 38. The bottoms of notches, or abutment surfaces of the notches, are spaced from the seals 54 and / or the axial wall.
  • the radial flange 38 not only joins all the openings 34, but also connects all the opposite edges 36 to each other by crossing the openings 34. It forms a reinforcing bar which, in each opening 34, blocks the opposite edges 36
  • the radial flange 38 has an arcuate shape and a notched profile. It comprises a series of steps forming notches 56 in which the ends 30 of the blades 30 are placed. These notches 56 can be a place for fixing the blades 26, for example by gluing or using fixing plates (not shown). To this end, the ends 30 may include fixing orifices (not shown). Within each opening 34, the radial flange 38 links the opposite edges 36. This configuration stiffens the ferrule 28, and prevents it from bending at the openings, 38 so that the risk of detachment at the joints 54 is reduced.
  • the figure 5 represents a section along axis 5-5 drawn on the figure 3 .
  • the section shows a compressor section between the rotor 12 and an internal shroud, seen from the outside. The location of the blade ends 30 is shown.
  • the asperities 48 comprise grooves and ridges alternating with the grooves, They extend radially and are optionally perpendicular to the axis of rotation of the turbomachine.
  • the assembly can form a striated annular surface.
  • the asperities 48 may have triangular tooth shapes, and have a general sawtooth profile.
  • the asperities 48 are formed opposite the wipers 44, preferably on each side.
  • the pattern can be formed along, along the circumference, radial flanges (38; 40; 42); or all around. Thanks to the asperities 48, the radial flanges (38; 40; 42) cause vortices 50 in the air entrained by the rotor 12
  • the figure 6 shows a diagram of a method of assembling a stator vane on a ferrule, the ferrule being able to be segmented.
  • Step (b) supply 102 can comprise additive manufacturing of the shell or of the shell segment.
  • the ferrule or each segment may have come from a mantle and be made of polymer, for example a composite martial material with fibers, possibly of length less than 10 mm.
  • Positioning step (c) 104 can be carried out by fixing the blades to an external compressor casing. Then the ferrule is brought together radially so that the internal ends of the blades are found in the openings. Initially, the blade tips enter the openings, then pass through them. Finally, these ends abut against a radial flange. The stop is then axial and / or radial, which makes it possible to improve the relative position between the blade and the shell. Thus, the joint produced or implemented during step (e) implementation or production 108 is better positioned and / or better produced.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP18159641.2A 2014-11-18 2015-10-22 Virole interne de compresseur de turbomachine axiale Active EP3351736B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
BE2014/0820A BE1022513B1 (fr) 2014-11-18 2014-11-18 Virole interne de compresseur de turbomachine axiale
EP15190957.9A EP3023595B1 (fr) 2014-11-18 2015-10-22 Virole interne de compresseur de turbomachine axiale

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
EP15190957.9A Division-Into EP3023595B1 (fr) 2014-11-18 2015-10-22 Virole interne de compresseur de turbomachine axiale
EP15190957.9A Division EP3023595B1 (fr) 2014-11-18 2015-10-22 Virole interne de compresseur de turbomachine axiale

Publications (2)

Publication Number Publication Date
EP3351736A1 EP3351736A1 (fr) 2018-07-25
EP3351736B1 true EP3351736B1 (fr) 2020-01-29

Family

ID=52449883

Family Applications (2)

Application Number Title Priority Date Filing Date
EP18159641.2A Active EP3351736B1 (fr) 2014-11-18 2015-10-22 Virole interne de compresseur de turbomachine axiale
EP15190957.9A Active EP3023595B1 (fr) 2014-11-18 2015-10-22 Virole interne de compresseur de turbomachine axiale

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP15190957.9A Active EP3023595B1 (fr) 2014-11-18 2015-10-22 Virole interne de compresseur de turbomachine axiale

Country Status (6)

Country Link
US (1) US10113439B2 (ru)
EP (2) EP3351736B1 (ru)
CN (1) CN105604612B (ru)
BE (1) BE1022513B1 (ru)
CA (1) CA2909256A1 (ru)
RU (1) RU2719521C2 (ru)

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EP3056684B1 (de) * 2015-02-16 2018-05-16 MTU Aero Engines GmbH Axial geteilter Innenring für eine Strömungsmaschine, Leitschaufelkranz und Flugtriebwerk
EP3263909B1 (en) * 2015-02-27 2020-08-19 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Method of manufacturing turbocharger
FR3045716B1 (fr) * 2015-12-18 2018-01-26 Safran Aircraft Engines Ensemble d'anneau de turbine avec maintien elastique a froid
BE1025283B1 (fr) 2017-06-02 2019-01-11 Safran Aero Boosters S.A. Systeme d'etancheite pour compresseur de turbomachine
DE102017211316A1 (de) 2017-07-04 2019-01-10 MTU Aero Engines AG Turbomaschinen-Dichtring
FR3085993B1 (fr) * 2018-09-17 2020-12-25 Safran Aircraft Engines Aube mobile pour une roue d'une turbomachine
FR3087825B1 (fr) * 2018-10-29 2020-10-30 Safran Aircraft Engines Secteur d'anneau de turbine a languettes d'etancheite refroidies
FR3088671B1 (fr) * 2018-11-16 2021-01-29 Safran Aircraft Engines Etancheite entre une roue mobile et un distributeur d'une turbomachine
FR3091725B1 (fr) 2019-01-14 2022-07-15 Safran Aircraft Engines Ensemble pour une turbomachine
US10822987B1 (en) 2019-04-16 2020-11-03 Pratt & Whitney Canada Corp. Turbine stator outer shroud cooling fins
JP7370226B2 (ja) * 2019-11-19 2023-10-27 三菱重工業株式会社 蒸気タービン

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Also Published As

Publication number Publication date
EP3023595A1 (fr) 2016-05-25
CA2909256A1 (en) 2016-05-18
EP3023595B1 (fr) 2018-04-18
CN105604612A (zh) 2016-05-25
RU2015146074A (ru) 2017-05-16
CN105604612B (zh) 2018-08-28
EP3351736A1 (fr) 2018-07-25
BE1022513B1 (fr) 2016-05-19
RU2719521C2 (ru) 2020-04-21
US20160138413A1 (en) 2016-05-19
RU2015146074A3 (ru) 2019-05-20
US10113439B2 (en) 2018-10-30

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