EP3724454B1 - Aube multipale de rotor de turbomachine et rotor la comprenant - Google Patents

Aube multipale de rotor de turbomachine et rotor la comprenant Download PDF

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Publication number
EP3724454B1
EP3724454B1 EP18829759.2A EP18829759A EP3724454B1 EP 3724454 B1 EP3724454 B1 EP 3724454B1 EP 18829759 A EP18829759 A EP 18829759A EP 3724454 B1 EP3724454 B1 EP 3724454B1
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EP
European Patent Office
Prior art keywords
platform
blade
blades
vane
radial
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
EP18829759.2A
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German (de)
English (en)
French (fr)
Other versions
EP3724454A1 (fr
Inventor
Arnaud Nicolas NEGRI
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 Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication date
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Publication of EP3724454A1 publication Critical patent/EP3724454A1/fr
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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2240/90—Mounting on supporting structures or systems
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the present invention relates to the field of bladed rotors in turbomachines, more particularly the case where the blades are made individually and fixed on a disc to form the bladed rotor.
  • a low pressure turbine rotor is generally made up of several tens or even hundreds of blades mounted on a disc.
  • Each blade is made up of at least one blade, an attachment for fitting into the rotor disc and a platform, placed between the two, so as to form the internal face of the stream in which the flow of gas crossed by the blades.
  • Such a rotor can be heavily loaded by a very high rotational speed. Maintaining the blades on the rotors and sealing vis-à-vis the flow of gas at the platforms are part of the problems to be solved during the design of these rotors and their blades.
  • a two-bladed vane 100 comprises two blades 101,102, extending in span along a radial direction R between an internal platform 103 and an external platform 104 delimiting the flow path of the gas flow.
  • the internal platform 103 also makes the connection between the blades 101, 102, and a one-piece attachment foot 105 which is inserted between the teeth 106 of the disc of a rotor 107 (shown only near dawn).
  • the dovetail-shaped attachment comprises a bulb 107 placed at the end of a stilt 108 in two parts, each of the two parts joining the base of a blade.
  • the manufacture of the blade being made by foundry, so as not to have a solid zone between the two parts of the stilt 108, a cavity 109 is made between the two parts of the stilt 108 using a core used in the foundry process.
  • the attachment foot 105 is substantially centered in the circumferential direction T between the two blades 101, 102, so as to balance the stresses to retain the blades under the centrifugal forces.
  • this requires the two parts of the stilt 108 to have a non-radial part to join the base of the blades.
  • the arrows on the figure 1 schematically show the path of the stresses due to centrifugal forces, along the stilt 108 and the blades 101, 102. In the part where the arrows are not aligned with the radial direction R this creates a moment in the stilt and therefore additional constraints.
  • the attachment foot 105 must hold two blades instead of one, resisting additional stresses due to the offset of the foot 105 relative to the blades.
  • the foot 105 being crossed by the core 109, it must be even wider than twice a single foot to hold a single blade.
  • the object of the invention is to propose a solution for minimizing the mass of the attachment of a two-bladed blade, in particular by reducing the level of the stresses to which the attachment of the blades must withstand during operation of the rotor.
  • Another object of the invention is to avoid too much hyperstatism between the disc and the blade, which would require expensive precision adjustments between the attachments of the blades and the fixing teeth on the disc.
  • Another object of the invention is to minimize the mass of the rotor assembly at the level of the connection with the blades.
  • the invention relates to a turbomachine rotor blade comprising a first blade and a second blade arranged to form two successive blades of a bladed rotor, a platform substantially forming an angular wall sector in an axial direction, said two blades being connected to the platform by one of their ends, extending substantially in a so-called radial direction substantially perpendicular to said axial direction, and fastening means connected to the platform which are intended to cooperate with fastening means on a disk of the rotor .
  • Said blade is characterized in that said attachment means comprise two separate stilts, each stilt extending from the platform, in the radial direction, in the extension of one of said two blades, and carrying an attachment element at a opposite end to the platform, said attachment element extending substantially parallel to said axial direction and comprising at least one surface facing the platform with a constant sectional profile perpendicular to said axial direction, so as to form a surface bearing intended to hold the blade in said radial direction oriented from the platform towards the blades.
  • each stilt extends parallel to the axial direction with a constant profile of the bearing surface makes it possible to mount the blade according to the invention by sliding the attachment element against teeth of the rotor disk in the axial direction.
  • each stilt in the extension of each blade makes it possible to better align the passage of the stresses to hold the blade between the blades and the stilts during the rotation of the rotor. There is therefore no extra thickness to be provided in the dimensioning of the stilts to resist significant twisting moments and this allows a weight saving on the blade compared to the state of the art of a two-bladed blade. with a central foot.
  • the disc when the disc is thus equipped with a succession of vanes such that the blades can be associated two by two with stilts which are in their extension, it may suffice to provide holding teeth only in one out of two circumferential intervals between the stilts. Indeed, if the attachment means are symmetrical, one interval out of two corresponds to the presence of the bearing surfaces and the other is empty of holding means.
  • the invention makes it possible to limit the hyperstatic nature of the radial support against centrifugal forces.
  • the blade according to the invention has only two contact planes instead of four. With four contact planes, it would be necessary to impose much tighter manufacturing tolerances than what is done in the state of the art to ensure that one or two of the bearing surfaces are not inoperative.
  • the greater spacing of the bearing surfaces is also advantageous for the positioning of the blades of the dawn relative to the disc and therefore their positioning in the engine.
  • these support surfaces define with the teeth of the disc contact surfaces which position the blades. The greater the distance between the two contact surfaces, the smaller the defects on these surfaces will have on the angular positioning defect of the blades.
  • the support surface of the attachment element carried by each stilt is located on one side of the outer attachment element relative to the two stilts in a circumferential direction perpendicular to said axial and radial directions.
  • the stilts with their attachment element can be slid during assembly between two successive teeth of the disc, leaving a gap between the two stilts.
  • the bearing surface is itself generally inclined with respect to the radial direction.
  • the placement of the bearing surfaces circumferentially outside the stilts contributes to the stability of the connection to the disc with respect to the forces exerted on the blade during operation. of the rotor.
  • each stilt comprises a veil substantially plane and parallel to the axial direction forming said end bearing the attachment element, said veil and the attachment element being arranged to have a side face facing in the direction opposite to the another stilt that is parallel to the axial direction with a constant profile.
  • part of the veil can also be engaged between the teeth of the disc and thus cooperate with the teeth to participate in the lateral retention of the blade.
  • the attachment element comprises a lug forming a lug with respect to said sail at the end of the stilt.
  • This embodiment minimizes the mass used to make the attachment of the blade.
  • the blades being offset by a given distance at their junction with the platform in a circumferential direction, perpendicular to said axial and radial directions, said ends of the two stilts carrying the attachment element are offset by a distance substantially equal to said given distance.
  • the attachments of several successive blades to the rotor create a repeating pattern which can cooperate with a uniform distribution of similar teeth on the periphery of the rotor disk.
  • each stilt is positioned in a circumferential direction, perpendicular to said axial and radial directions, on an average position of the end linked to the platform of the corresponding blade.
  • each stilt is shaped so that the junction of the stilt with the platform follows the junction with the platform of the corresponding blade in its evolution along the axial direction.
  • the blade can advantageously comprise at least one wall connecting the two stilts transversely to said axial direction.
  • Such a wall has a stiffening function. It will prevent deformation of the stilts under centrifugal forces and can make it possible to reduce the thickness of the stilts, and therefore their mass.
  • Said wall may extend radially between the stilts from the platform to a line joining radial ends of the attachment elements opposite the platform.
  • the invention also relates to a turbomachine rotor comprising blades as described above.
  • the disk of said rotor carries at its periphery a succession of similar teeth shaped to cooperate with the attachment means of the blades, two successive teeth being separated in the circumferential direction by a distance at least equal to the width of one tooth. following this direction.
  • a turbine blade 1 according to the invention comprises two blades 2, 3 extending spanwise in a radial direction R between an internal platform 4 and an external platform 5.
  • the blade 1 is fixed on a rotor disc 6 movable around an axis of direction X (shown in the figure 4 ), of which only a peripheral part is shown with the teeth 7 for holding the blade.
  • the axial and radial directions refer to the axis of the rotor, the terms internal and external refer to the radial direction.
  • the terms upstream and downstream in the axial direction refer to the direction of flow for which the blades were designed.
  • the internal 4 and external 5 platforms delimit an angular sector of the passage passage of the gas flow around said axis X.
  • the external platform 5 is not concerned by the invention and may possibly not exist, it is elsewhere generally the case for compressor blades. It is therefore not described further.
  • the internal platform 4 is delimited along the circumferential direction T between two axial planes, so as to fit with the platforms adjacent blades in order to ensure continuity of the wall of the vein.
  • the body 8 of the internal platform 4 delimiting the vein has a radial profile determined by the design of the turbine which can be inclined with respect to the radial direction R. In the example, this profile deviates from the axis X of the rotor from upstream to downstream.
  • the internal platform 4 here comprises an upstream radial web 9 and a downstream radial web 10 which extend radially so as to come into contact with the teeth 7 holding on the disc 6, at the same distance of the X axis.
  • the upstream veil 9 and the downstream veil 10 have a function of maintaining the blade 1, on the one hand to block its movement in the radial direction towards the X axis, on the other hand to block the rotation around a direction parallel to the axis X.
  • the internal platform 4 generally comprises devices fixed to the upstream 9 and downstream 10 sails, for example annular spoilers 11, to effect sealing with the stator elements of the turbine that surround the rotor in the axial direction.
  • the two blades 2, 3 have a curved and inclined profile with respect to the axial direction X which can evolve along their span in the radial direction R.
  • figure 4 shows the shape of this profile at the base of the blades 2, 3, at the level of their junction with the platform 4.
  • the geometries of the two blades 2, 3, are similar with an angular offset corresponding to the design of the rotor and the number of blades which must be installed there.
  • the bases of the blades 2, 3 are therefore offset by a distance D determined at the level of the internal platform 4.
  • the attachment of the blade 1 to the disc 6 here comprises two separate stilts 12, 13 which are connected to the body 8 of the platform 4 and extend from the latter in the radial extension of one of the blades 2, 3, having substantially the same extension as said blades 2, 3 in the axial direction X.
  • Each stilt 12, 13 ends here, on the side opposite the platform, with an axial web 14, 15, parallel to the radial direction R , which is connected to a leg 16, 17, parallel to the axial direction X and inclined with respect to the radial direction, which leg forms the free end of the stilt.
  • Said lug 16, 17 deviates laterally outwards starting from the axial web 14,15, forming, in cross section, an end lug, so that its outer lateral surface S1, S2 faces the platform 4.
  • the support surface S1, S2 is generally inclined with respect to the radial direction.
  • the angle of inclination depends on the design made by the person skilled in the art according to the geometry of the turbine and the operating constraints. Classically it takes values between 40 and 50°, but can be outside this range.
  • Each lug 16, 17 thus forms an attachment element for the blade 1 and the surfaces S1, S2 form support surfaces allowing the blade to be retained in the radial direction R oriented from the platform towards the blades.
  • the axial webs 14, 15 of the stilts 12, 13 and the end legs 16, 17 cooperate with the teeth 7 of the disc 6 to hold the blade 1 according to an operation which will be described later.
  • the axial sails 14, 15 of the ends of each stilt 12, 13 are centered on an average position of the bases of the blades 2, 3 on the platform 4 in the circumferential direction T and are therefore offset along this direction by a distance D′ substantially equal to the offset D between the bases of said blades 2, 3.
  • the assemblies formed of the axial sails 14, 15 and the end legs 16, 17, are substantially symmetrical with respect to an axial plane passing through the middle of the stilts 12, 13.
  • Each stilt 12, 13 has a three-dimensional shape between the axial web 14, 15, and the platform 4, to follow the profile of the base of the blade 2, 3 corresponding to the level of its junction with the body 8 of the platform 4.
  • the disc 6 of the rotor comprises at its periphery a crown of similar teeth 7 which are offset along the circumferential direction T by a distance substantially equal to twice the offset distance D between the bases of the blades 2, 3, of so that there are twice as many teeth 7 as blades 2, 3 on the rotor.
  • Each tooth 7 here extends parallel to the axis X over a distance substantially corresponding to the gap between the upstream 9 and downstream 10 webs of the platform, with a constant transverse profile.
  • the blade 1 described above can be installed between two successive teeth 7 by sliding, in the axial direction X, the axial webs 14, 15 of the stilts 12, 13 and the end legs 16, 17, between two teeth 7 successive.
  • Known devices, not described here, then make it possible to maintain the blade 1 in its axial position with respect to the rotor. These devices are not concerned by the invention.
  • each tooth 7 here has the shape of a bulb.
  • the tooth therefore comprises a part of constant given thickness followed by a widening.
  • the shape of this widening is defined so as to form, on one side of the tooth 7, a surface facing the disc 6 which is in contact with the support surface S1 connected to one of the stilts 12 of the blade 1 and to form on the other side of the tooth, another surface facing the disc 6 which is in contact with the support surface S2 linked to the other of the stilts 13 of an adjacent blade, similar to the blade 1.
  • the profile of the teeth 7 is symmetrical with respect to a median radial plane of the tooth.
  • tooth 7 has a substantially flat radially outer surface or forming a circular cylinder portion centered on axis X of the rotor.
  • each stilt 12, 13 The bearing surface S1, S2 of the end tab 16, 17, carried by each stilt 12, 13 is designed to absorb approximately half of the centrifugal forces applied to the blade 1, that is to say substantially those corresponding to one of said blades 2, 3.
  • a stilt 12, 13 with its end leg 16, 17 must therefore be sized substantially to withstand the stresses imposed by a blade.
  • the three-dimensional part of the stilt 12, 13 takes up these forces towards the base of the corresponding blade 2, 3 with a slight radial inclination since it is essentially a question here of compensating for the curved shape of the profile of the blade 2, 3 but not a circumferential offset of half an interval with said blade.
  • the blade 1 is held by the contacts of only two bearing surfaces S1 and S2, each extending in an inclined manner with respect to the radial direction, at the exterior of a stilt 12, 13 in the circumferential direction T.
  • said bearing surfaces S1, S2 are themselves spaced apart and located near the edges of the blade 1 in the circumferential direction T. This improves the stability of the assembly under the stress of the forces centrifugal, with respect to a single attachment gathered in the center of the blade.
  • the invention also allows a gain in mass on the disk 6. It can be seen on the figures 3 and 4 that the space between the two stilts 12, 13 of a two-bladed blade 1 is empty of teeth. On the other hand, by repeating from one blade 1 to another, each tooth 7 of the disc 6 occupies a space extending between two blades in the circumferential direction T, one belonging to a blade, the other belonging to adjacent dawn. Therefore, compared to the known solution of a two-bladed blade with a central root, the teeth 7 of a disk adapted to blades according to the invention are much narrower than for a disk adapted to two-bladed blades with a single root. , as can be seen by comparing the picture 3 and the figure 1 .
  • the figure 5 illustrates the mass saving obtained compared to the use of single-bladed blades or two-bladed blades with 2 attachments in accordance with the state of the art and which would therefore have 4 contact surfaces between the disc and the blade.
  • the teeth with the single-blade blades would have a lesser thickness along the circumferential direction T but would be twice as numerous since it would be necessary to add the tooth 7' indicated in dotted lines to retain each blade, which results in the fact that, overall, the invention makes it possible to gain on the mass of the teeth of the disc.
  • the blade 21 also comprises one or more transverse stiffening webs 18 which connect the two stilts 13, 14.
  • a stiffening web 18 extends radially from the body 8 of the platform 4. In the example presented in figure 6 , it only closes the space between the stilts 12, 13 at the level of the three-dimensional part, leaving the space between the axial sails 14,15 free.
  • such a realization leaves free an air passage zone under the platform 4 and the upstream 9 and downstream 10 sails, between the teeth 7 of the disc 6 of the rotor.
  • the blade 31 comprises at least one stiffening web 19 which extends as far as the radial end of the attachment lugs 16, 17 carried by the stilts 12, 13, following the periphery of the disc 6, so as to close the axial air passage between the teeth 7 under the platform 4 and the upstream 9 and downstream 10 sails.
  • the description of the embodiments of the invention given in this document is not limiting.
  • the blade described here is two-bladed but one can envisage blades comprising a succession of pairs of blades with their stilts in the extension. In this case, however, the mounting of the bearing surfaces on the teeth becomes hyperstatic for the blade, and therefore more difficult to adjust.
  • Other embodiments of the means of connection with the disk, not shown, can also be envisaged.
  • the radial blocking of the blade towards the axis can be ensured by an element carried by the stilts which presses on the disc 6 or on the radial apex of the teeth 7.
  • the internal platform 4 can then have no veil upstream or downstream having a holding function.
  • an attachment element at the end of the stilts 12, 13 other than a tab forming an elbow with respect to the axial web 14, 15, can be used to produce the bearing surfaces S1, S2. It can be achieved, for example, by spoilers deviating from the surface of the veil.
  • the shape of the teeth on the disk will then be adapted to the shape of the attachment elements used on the blade.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP18829759.2A 2017-12-13 2018-12-12 Aube multipale de rotor de turbomachine et rotor la comprenant Active EP3724454B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1762028A FR3074839B1 (fr) 2017-12-13 2017-12-13 Aube multipale de rotor de turbomachine et rotor la comprenant
PCT/EP2018/084462 WO2019115578A1 (fr) 2017-12-13 2018-12-12 Aube multipale de rotor de turbomachine et rotor la comprenant

Publications (2)

Publication Number Publication Date
EP3724454A1 EP3724454A1 (fr) 2020-10-21
EP3724454B1 true EP3724454B1 (fr) 2022-02-16

Family

ID=61224105

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18829759.2A Active EP3724454B1 (fr) 2017-12-13 2018-12-12 Aube multipale de rotor de turbomachine et rotor la comprenant

Country Status (5)

Country Link
US (1) US11156108B2 (zh)
EP (1) EP3724454B1 (zh)
CN (1) CN111448366B (zh)
FR (1) FR3074839B1 (zh)
WO (1) WO2019115578A1 (zh)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5735673A (en) * 1996-12-04 1998-04-07 United Technologies Corporation Turbine engine rotor blade pair
FR2851285B1 (fr) 2003-02-13 2007-03-16 Snecma Moteurs Realisation de turbines pour turbomachines ayant des aubes a frequences de resonance ajustees differentes et procede d'ajustement de la frequence de resonance d'une aube de turbine
EP1881163B1 (en) * 2006-07-18 2008-10-29 Industria de Turbo Propulsores S.A. Highly slenderness rotor
WO2014076407A1 (fr) * 2012-11-13 2014-05-22 Snecma Preforme et module d'aubes monobloc pour un carter intermediaire de turbomachine
CA2896753A1 (en) * 2013-03-05 2015-04-02 Rolls-Royce North American Technologies, Inc. Composite gas turbine engine blade having multiple airfoils

Also Published As

Publication number Publication date
EP3724454A1 (fr) 2020-10-21
US20200392855A1 (en) 2020-12-17
CN111448366A (zh) 2020-07-24
FR3074839B1 (fr) 2019-11-08
WO2019115578A1 (fr) 2019-06-20
CN111448366B (zh) 2022-09-16
FR3074839A1 (fr) 2019-06-14
US11156108B2 (en) 2021-10-26

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