EP2937517A1 - Stator einer axialen Turbomachine und zugehörige Turbomachine - Google Patents

Stator einer axialen Turbomachine und zugehörige Turbomachine Download PDF

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Publication number
EP2937517A1
EP2937517A1 EP14165800.5A EP14165800A EP2937517A1 EP 2937517 A1 EP2937517 A1 EP 2937517A1 EP 14165800 A EP14165800 A EP 14165800A EP 2937517 A1 EP2937517 A1 EP 2937517A1
Authority
EP
European Patent Office
Prior art keywords
rod
ferrule
stator
notches
stator according
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.)
Granted
Application number
EP14165800.5A
Other languages
English (en)
French (fr)
Other versions
EP2937517B1 (de
Inventor
Damien Verhelst
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
Techspace Aero 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 Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP14165800.5A priority Critical patent/EP2937517B1/de
Priority to CA2888531A priority patent/CA2888531A1/en
Priority to RU2015115261A priority patent/RU2614302C2/ru
Priority to CN201510201427.2A priority patent/CN105003467B/zh
Priority to US14/695,292 priority patent/US9995159B2/en
Publication of EP2937517A1 publication Critical patent/EP2937517A1/de
Application granted granted Critical
Publication of EP2937517B1 publication Critical patent/EP2937517B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • 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
    • 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
    • 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
    • F01D11/08—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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/005—Selecting particular materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/007—Axial-flow pumps multistage fans
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • 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
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/171—Steel alloys
    • 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
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • 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
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/437—Silicon polymers
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Definitions

  • the invention relates to an axial turbomachine compressor stator. More particularly, the invention relates to a stator with an axial turbomachine blade retaining rod. The invention also relates to an axial turbomachine.
  • the stator of an axial turbomachine is generally provided with coaxial shells delimiting the inside and the outside of the flow.
  • the stator also includes an annular array of vanes extending radially between the ferrules. The blades may be inserted into openings in a ferrule, and held individually on the ferrule in question.
  • Maintaining can be achieved by means of a retention rod which cooperates with notches formed in blade tips located beyond the ferrule, outside the flow.
  • the document GB 748.912 A discloses a blade assembly on an axial turbomachine compressor shell.
  • the ferrule comprises two annular walls with openings for the insertion of blade tips.
  • Each blade has a free end, extending radially outside the shell, which has a retention notch.
  • the notches of the blades have a squeezing outwards.
  • the notches are arranged in rows and receive blade retention rods whose transverse profile is arched. Thus arranged, the rods form corners that block the blades.
  • a blade may be subjected to significant tensile forces that can separate a blade from its wand. Indeed in case of traction, the inclined edges of a notch can crush the rod in the arching more, so that the stick can come out of the notch. The dawn concerned is then no longer maintained by his wand.
  • the object of the invention is to solve at least one of the problems posed by the prior art. More particularly, the object of the invention is to improve the retention between a blade and an arcuate transverse profile rod of an axial turbomachine. The invention also aims to increase the life of a rotor with vanes retained to a ferrule with a rod.
  • the subject of the invention is an axial turbomachine stator, in particular a compressor, the stator comprising: a ferrule with an annular row of openings, an annular row of stator vanes which extend essentially radially through the openings (36) each blade comprises a retention notch (38) and a blade intended to extend in a flow of the turbomachine, each retention notch has an inlet with a narrowing and is situated opposite the blade relative to the aperture traversed by the corresponding blade, at least one blade retention strip inserted into the notches, the strip-shaped strip with an arcuate transverse profile which contacts the constrictions so as to hold the strip in the notches , remarkable in that the ferrule comprises a layer of abradable material enveloping the transverse profile of the rod so as to block the curvature of the transverse profile. arched to prevent the rod from coming out of the narrowing of the notches by deforming.
  • the rod is bent circumferentially so as to be parallel to the ferrule, the rod being spaced radially from the openings of the ferrule.
  • the rod in the absence of the abradable layer, is configured to be introduced and / or extracted. notches flattening or arching further its arcuate profile; the deformation possibly being a plastic deformation of the rod.
  • the rod is a spring configured to be deformable elastically over at least 5%, preferably at least 10% of its axial length and / or its radial height, the rod being made of steel at spring, preferably steel 45S7, 55S7, 45SCD6, 60SC7, 45SW8, 45C4, 50CV4.
  • the radial majority of the abradable layer is disposed between the ferrule and the rod.
  • the thickness of the strip of the strip is less than 1 mm, preferably less than 0.25 mm, more preferably less than 0.1 mm.
  • the arcuate transverse profile of the rod described between a tenth of a circle and a semicircle, preferably between a sixth and a third of a circle, more preferably between a fifth and a quarter circle.
  • the arcuate transverse profile of the rod has a main elongation generally parallel to the axis of rotation of the axial turbomachine.
  • the abradable layer is an annular layer which covers both sides of the strip of the rod, and the rod is surrounded by the abradable layer all along the intervals between the blades, the abradable layer also closes the openings of the shell around the blades.
  • the notches are open radially, the radial depths of the notches being greater than the radial height of the rod.
  • each notch comprises two axially opposed hooks which close the passage of the notch, so as to allow radial retention of the rod.
  • the ferrule is an inner ferrule, the ferrule and the rod being segmented, each ferrule segment comprising at least three openings for the insertion of blades.
  • the rod comprises a curved surface facing the ferrule, preferably the rod comprises two radially projecting circular edges which are arranged radially on the side of the ferrule.
  • the abradable layer comprises optionally filled elastomer or silicone, and is intended to cooperate by abrasion with the rotor of the axial turbomachine.
  • the strip is a strip of constant thickness material arcuate and curved.
  • the slots of the notches approach one another radially inwards.
  • the width of the notches is reduced radially inwards.
  • the arcuate shape of the transverse profile forms a thickening of the strip, and / or forms a reduction in the transverse width of the strip.
  • the rod has a main elongation in the circumferential direction of the stator, the transverse direction being perpendicular to the circumferential direction.
  • the abradable layer is glued or glued to the rod.
  • the abradable layer envelops the blades.
  • the abradable layer forms a block of material around the transverse profile of the rod.
  • the abradable layer has a constant radial thickness and / or a constant axial length between the blades.
  • the notches are notches of radial retention.
  • the rod can be deformed axially in compression so as to further arcuate its arcuate profile to allow the introduction or disassembly of the rod in the absence of the abradable layer.
  • the shell is able to define an axial annular flow of the turbomachine, the blades being intended to extend radially in the annular flow, possibly by deviating.
  • the layer of abradable material prevents the rod from coming out of the narrowing of the notches by modifying the curvature of the arcuate transverse profile.
  • the invention also relates to an axial turbomachine comprising a stator, remarkable in that the stator is in accordance with the invention, preferably the turbomachine comprises a low-pressure compressor provided with a stator according to the invention.
  • the proposed stator architecture makes it possible to operate a synergy between the abradable layer and the rod.
  • the abradable layer improves the stability of the rod by locking its curvature which guarantees its retention.
  • the rod is better locked in position in the notches, against narrowing.
  • the rod improves the mechanical connection between the blades and the abradable layer.
  • the presence of the abradable layer between the ferrule and the rod promotes the distribution of forces, forming a cushion cushioning stress peaks in case of shocks. Thus, the radial retention of the blades to the shell is safer.
  • the blocking function of the abradable layer may be performed by any polymeric material, possibly a composite, the abradable function being optional.
  • inner or inner and outer or outer refer to a positioning relative to the axis of rotation of an axial turbomachine.
  • the figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6.
  • Reducing means can increase the speed of rotation transmitted to the compressors.
  • the different turbine stages can each be connected to the compressor stages via concentric shafts.
  • the latter comprise several rows of rotor blades associated with rows of stator vanes. The rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 10.
  • An inlet fan commonly referred to as fan or blower 16 is coupled to the rotor 12 and generates an air flow which splits into a primary flow 18 passing through the various aforementioned 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 turbine outlet.
  • the secondary stream can be accelerated to generate a push reaction.
  • the primary 18 and secondary 20 streams are annular flows, they are channeled by the casing of the turbomachine, and can flow axially.
  • the casing has cylindrical walls or ferrules which can be internal and external.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine 2 such as that of the figure 1 .
  • the compressor may be a low-pressure compressor 4.
  • the rotor 12 comprises several rows of rotor blades 24, in the occurrence three.
  • the low-pressure compressor 4 comprises a stator with several rectifiers, in this case four, which each contain an annular row of stator vanes 26.
  • the rectifiers are associated with the fan 16 or with a row of rotor vanes to straighten the flow. air, so as to convert the speed of the flow into pressure.
  • the stator vanes 26 extend substantially radially from an outer stator casing, and can be attached thereto by means of an axis, such as a stud, a lockbolt.
  • the stator housing may be an outer shell.
  • the stator comprises at least one ferrule 28, for example an inner ferrule 28, for guiding the primary flow 18.
  • the stator may comprise several ferrules, for example several inner ferrules.
  • Each ferrule 28 has an annular row of openings. These are distributed homogeneously around the inner rings and are crossed by the ends of the blades for anchoring.
  • Each ferrule may comprise an annular wall, generally tubular or substantially conical, and optionally one or two annular flanges disposed at the axial ends of the annular wall. Each annular flange extends radially inwards or outwards.
  • the rings 28 may be made of metal, for example titanium alloy, or composite material to reduce their mass. The ferrules form mechanical links between the blades.
  • the stator comprises at least one or more blade retention rods 26. Each rod 30 is inserted into notches formed at the ends of the blades, for example the inner ends located radially under the inner ferrules.
  • the stator may include a plurality of rods 30, each associated with an annular row of blades, for radially retaining the blades of the row at the associated ferrule.
  • the stator comprises at least one or more layers of material 32 associated with at least one ferrule. At least one or each layer of material may be a layer of abradable material 32, or layer of friable material, housed in the hollow of the inner ferrules 28. At least one or each layer may be annular.
  • the abradable layers 32 may be of substantially constant thickness so as to form a band. These abradable layers 32 are intended to cooperate by abrasion with rotor wipers, or circumferential fins, so as to ensure a seal, for example a dynamic seal.
  • the abradable layers 32 provide a waterproof filling and can be structuring. Each layer of abradable can provide cushioning.
  • Each abradable layer may adhere to a rod, and / or a shell, and / or a blade.
  • the rotor moves and deforms so that the radial ends of the wipers touch the associated abradable layers. They can dig annular furrows.
  • the or each ferrule 28 may be formed of a plurality of annular segments, which form angular sectors of circles.
  • the rod 30 may also be segmented, as is the abradable layer 32.
  • the annular segments have an arcuate shape. They each have a plurality of openings in which are introduced inner ends of the stator vanes 26.
  • each annular segment may be connected to at least three vanes, possibly four vanes.
  • the figure 3 represents an axial turbomachine stator with a series of stator vanes 26 connected to a ferrule 28 via a retention rod 30 and an abradable layer 32.
  • the stator is shown in a section along the axis 3-3 plotted on the figure 2 .
  • the present teaching can be applied to an inner shell as to an outer shell.
  • the ends 34 for example internal, blades 26 pass through the openings 36 of the shell 28.
  • Each opening 36 can marry the associated blade, or arrange a game around the blade 26.
  • the game can be filled by the layer of abradable 32, or by an additional silicone seal (not shown) to ensure a seal in the seal.
  • Each blade 26 may have continuity of profile on both sides of the ferrule 28. Beyond the profile continuities, the blade ends 34 comprise the retention notches 38. These notches 38 are engaged, for example by positive contact, to their associated wand 30.
  • the blades comprise blades disposed in the flow, and radially opposite ends of the blades relative to the ferrules. The ferrule separates the ends of the blades disposed in the flow.
  • the wand 30 may have a band shape with two faces. Each face may be covered with the abradable layer 32.
  • the wand 30 may be wrapped by the abradable layer 32 between each end 34 of blade 26, or all along the ferrule.
  • the rod 30 may be bent so as to follow the inner annular surface or the outer annular surface of the ferrule 28 associated. The rod 30 may remain radially away from the annular surface of the ferrule 28. In this way, part of the abradable layer 32 may be disposed between the shell 28 and the rod 30.
  • the majority of the radial thickness of the abradable layer is located between the ferrule and the rod.
  • the space between the rod 30 and the ferrule 28 is advantageously occupied by the abradable layer 32.
  • the abradable layer may be in contact with the ferrule and the rod.
  • the rod 30 can form a reinforcing core of the ferrule 28.
  • the ferrule 28 can form a support for the abradable layer 32, and / or a protective skin covering the abradable layer 32.
  • the abradable layer 32 may comprise elastomer, the viscoelastic nature of which, coupled with the presence of the rod 30, improves cushioning against vibrations in the stator.
  • the abradable layer 32 may stick to the blades 26, and / or to the ferrule 28, and / or to the rod 30. Glue may be applied to the rod 30 so that it sticks to its environment.
  • the abradable layer 32 may be silicone; possibly with spheres to improve friability.
  • the material of at least one or each rod may be a metal.
  • the metal may be manganese siliceous steel, for example with 1.5% to 2% silicon, for example with 0.6% to 0.7% manganese, 0.4% to 0.6% carbon.
  • the metal or steel may comprise chromium, and / or tungsten, and / or molybdenum and / or vanadium.
  • the steel may be of the type 45S7, 55S7, 45SCD6, 60SC7, 45SW8, or 45C4, 50CV4.
  • the metal may also be copper with 1% to 2% beryllium. Percentages are mass percentages.
  • the figure 4 represents a stator enlargement with a radial end 34 of blade joined to a ferrule 28 with a rod 30 embedded in an abradable layer 32 applied in the shell.
  • the end 34 of the blade 26 passes through the ferrule 28 and extends beyond the ferrule on the opposite side to the fluid vein.
  • the end 34 comprises a retention notch 38 or anchoring.
  • the notch 38 can be oriented axially or stiffly. By oriented one can hear open.
  • a notch may extend predominantly axially and be open radially.
  • the notch 38 may form a cutout in the end 34 of the blade 26.
  • the retention notch 38 delimits a space in which the rod 30 is integrated in order to ensure retention.
  • the notch 38 has an inlet through which can be introduced or output the rod, and a bottom 40 opposite the input.
  • the notch may have a narrowing or tightening.
  • the narrowing may be formed between the inlet and the bottom 40 and may be progressive. It forms a decrease in passage width with respect to the entrance.
  • the notch 38 may comprise two slices 42 joining the inlet and the bottom 40. The slices 42 may come together to form the constriction.
  • the end 34 of the blade may comprise two hooks 44 so as to form the narrowing. They can get closer to one another locally.
  • the narrowing is axial because the notch 38 is open radially. It may be radial in the case of an axially open slot.
  • the rod 30 has a band or ribbon shape, the main elongation of which follows the circumference of the shell 28.
  • the transverse profile of the band is arcuate, it has a curved shape.
  • the curved aspect makes it possible to reduce the transverse width of the rod 30 and / or to increase the thickness thereof; the thickness being perpendicular to the elongation and the transverse direction.
  • the profile of the rod 30 has a main elongation. This main elongation may be oriented radially or axially, for example depending on the orientation of the narrowing and its retention function.
  • the stick, or at least its band is essentially fine. Its thickness is less than 1.00 mm, possibly less than 0.25 mm.
  • the arcuate shape of the transverse profile describes a fraction of a circle, possibly more than one turn.
  • the profile may describe a portion of curve or circle between 180 ° and 30 °, preferably between 120 ° and 60 °, more preferably between 90 ° and 72 °.
  • the arcuate shape comes into contact with the narrowing so as to maintain the rod in the notch, and may also be in contact with the bottom of the notch.
  • the rod 30 may comprise a concave surface facing the ferrule, for confining a portion of the abradable layer with the ferrule.
  • the arched shape increases the size of the profile of the rod 30. Thus it can offer more support surface for a blade retention. Apart from its arched appearance, the band can have a constant thickness.
  • the arcuate transverse profile of the rod 30 offers a relative flexibility, which allows to introduce it into the notch 38 by crushing it. It can be crushed transversely or axially to enter the notch, for example by deforming plastically.
  • the wand may also be a spring that deforms elastically when it is in the notch. It deforms elastically radially or axially more than 5%, preferably more than 10% of the dimension concerned.
  • the rod 30 is held by the abradable layer 32.
  • the abradable layer 32 surrounds the profile, for example all around the transverse profile.
  • This abradable layer 32 may have a thickness greater than half the radial thickness of the shell 28. It can block the curvature of the profile to lock the rod 30 in the notch 38, to avoid what sort in case of pulling the rod out of the notch following its deformation. This deformation can then increase the curvature of the arc, or flatten it according to the orientation of the bend with respect to the narrowing.
  • each characteristic can be applied to all the ferrules and / or to all the rods, and / or to all the abradable layers, and / or to all the notches of the stator of the turbomachine; or a majority of them.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP14165800.5A 2014-04-24 2014-04-24 Stator einer axialen Turbomaschine und zugehörige Turbomaschine Active EP2937517B1 (de)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP14165800.5A EP2937517B1 (de) 2014-04-24 2014-04-24 Stator einer axialen Turbomaschine und zugehörige Turbomaschine
CA2888531A CA2888531A1 (en) 2014-04-24 2015-04-21 Blade retaining ring for an internal shroud of an axial-flow turbomachine compressor
RU2015115261A RU2614302C2 (ru) 2014-04-24 2015-04-23 Стопорное кольцо лопаток статора осевой турбомашины и осевая турбомашина
CN201510201427.2A CN105003467B (zh) 2014-04-24 2015-04-24 用于轴流式涡轮机压缩机内部护罩的叶片保持环
US14/695,292 US9995159B2 (en) 2014-04-24 2015-04-24 Blade retaining ring for an internal shroud of an axial-flow turbomachine compressor

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EP14165800.5A EP2937517B1 (de) 2014-04-24 2014-04-24 Stator einer axialen Turbomaschine und zugehörige Turbomaschine

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EP2937517A1 true EP2937517A1 (de) 2015-10-28
EP2937517B1 EP2937517B1 (de) 2019-03-06

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EP (1) EP2937517B1 (de)
CN (1) CN105003467B (de)
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US10253643B2 (en) 2017-02-07 2019-04-09 General Electric Company Airfoil fluid curtain to mitigate or prevent flow path leakage
US10378373B2 (en) 2017-02-23 2019-08-13 General Electric Company Flow path assembly with airfoils inserted through flow path boundary
US10385709B2 (en) 2017-02-23 2019-08-20 General Electric Company Methods and features for positioning a flow path assembly within a gas turbine engine
US10385776B2 (en) 2017-02-23 2019-08-20 General Electric Company Methods for assembling a unitary flow path structure
US10253641B2 (en) 2017-02-23 2019-04-09 General Electric Company Methods and assemblies for attaching airfoils within a flow path
US10247019B2 (en) 2017-02-23 2019-04-02 General Electric Company Methods and features for positioning a flow path inner boundary within a flow path assembly
US10370990B2 (en) 2017-02-23 2019-08-06 General Electric Company Flow path assembly with pin supported nozzle airfoils
US10385731B2 (en) 2017-06-12 2019-08-20 General Electric Company CTE matching hanger support for CMC structures
US10746035B2 (en) 2017-08-30 2020-08-18 General Electric Company Flow path assemblies for gas turbine engines and assembly methods therefore
US10669894B2 (en) * 2018-01-26 2020-06-02 Raytheon Technologies Corporation Annular retention strap
PL431184A1 (pl) * 2019-09-17 2021-03-22 General Electric Company Polska Spółka Z Ograniczoną Odpowiedzialnością Zespół silnika turbinowego
US11268394B2 (en) 2020-03-13 2022-03-08 General Electric Company Nozzle assembly with alternating inserted vanes for a turbine engine
CN113565799A (zh) * 2021-08-24 2021-10-29 中国航发湖南动力机械研究所 一种可拆装的轴流压气机

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Also Published As

Publication number Publication date
CN105003467A (zh) 2015-10-28
RU2614302C2 (ru) 2017-03-24
US9995159B2 (en) 2018-06-12
US20150308277A1 (en) 2015-10-29
CN105003467B (zh) 2019-07-09
CA2888531A1 (en) 2015-10-24
EP2937517B1 (de) 2019-03-06
RU2015115261A (ru) 2016-11-10

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