EP3312384A1 - Rotationseinheit einer strömungsmaschine, die mit einem axialen haltesystem einer laufradschaufel ausgestattet ist - Google Patents

Rotationseinheit einer strömungsmaschine, die mit einem axialen haltesystem einer laufradschaufel ausgestattet ist Download PDF

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Publication number
EP3312384A1
EP3312384A1 EP17197598.0A EP17197598A EP3312384A1 EP 3312384 A1 EP3312384 A1 EP 3312384A1 EP 17197598 A EP17197598 A EP 17197598A EP 3312384 A1 EP3312384 A1 EP 3312384A1
Authority
EP
European Patent Office
Prior art keywords
teeth
disc
disk
latch
pin
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
EP17197598.0A
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English (en)
French (fr)
Other versions
EP3312384B1 (de
Inventor
Thomas Alain DE GAILLARD
Alexandre Bernard Marie Boisson
Gilles Pierre-Marie NOTARIANNI
Charles-Henri Claude Jacky SULLET
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
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 Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3312384A1 publication Critical patent/EP3312384A1/de
Application granted granted Critical
Publication of EP3312384B1 publication Critical patent/EP3312384B1/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
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the 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
    • 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
    • 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
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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

Definitions

  • the present invention relates to a rotary assembly of a turbomachine provided with a system for axially holding one or more of its blades, in particular blades of a rotor disc of a turbojet engine.
  • Such a rotary assembly generally comprises one or more rotors whose disc is connected to a rotor rotation shaft, which rotor disc has at its periphery a circumferential alternation of cells, also called grooves, and teeth, of substantially axial orientations, that is to say which extend in a direction parallel to the axis of the rotor shaft.
  • the rotor disc is provided with a plurality of vanes partially inserted in grooves and extend radially from the periphery of the disc, in a vein of fluid supplying the turbomachine.
  • the blades of the fan extend radially in a vein up to the inner wall of a fan casing connected to an annular pod to externally delimit the vein.
  • axial refers to the axis of rotation (longitudinal) of the rotor.
  • radial refers to a radius of the rotor disk, the latter extending by definition orthogonal to the axis of rotation of the rotor.
  • circumferential refers to the circumference of the rotor disk, and corresponds to the rotational path of the rotor disk.
  • upstream corresponds to a zone of origin of the fluid that passes through the turbomachine in operation
  • downstream corresponds to a departure zone of this fluid.
  • the fluid passes through the turbomachine, and in particular the rotor disc, from upstream to downstream.
  • the blades each have at their end a foot engaged axially in the grooves of the disc and retained radially by the teeth of the disc.
  • a wedge is typically inserted between each blade root and the bottom of the groove corresponding, for purposes of maintenance, a priori prestressing, these elements.
  • the blades are secured and retained upstream including an upstream cone connected to the disk. This cone constitutes the internal and upstream limit of the vein of gas circulation of the turbomachine.
  • the turbojet engine further comprises an upstream ferrule integral with the disk and the upstream cone, and located between the disk and the upstream cone along the axis of the turbomachine. The ferrule thus makes it possible to connect the upstream cone to the disk.
  • a lock can conventionally be provided to axially secure the blades in their grooves.
  • the lock is positioned in slots provided for this purpose in the teeth of the disk, the lock being in correspondence of a groove of the disk in which has been previously inserted the dawn foot.
  • the lock is immobilized via the upstream ferrule fixed on the disc, this ferrule axially blocking a shim interposed between each blade root and the bottom of the corresponding groove.
  • the latch is inserted into its slots by radial translation directed towards the outside of the disc.
  • the document US6634863 describes a lock of this type inserted into a groove. It more precisely describes a turbine engine assembly comprising a disk whose vanes are held axially by a retaining element (latch) inserted in a recess provided in the inner wall of the disc teeth, and extending perpendicular to the axis of the disc. groove welcoming the foot of dawn.
  • the retaining element is coupled to a spacing element positioned in the groove, resting on the lower surface of said groove, and prevents the blades from pivoting on themselves in the groove.
  • the need to provide such a space generates constraints for the manufacture of the rotor disk, and more particularly the placement constraints of the fastener element for connecting the disk to the upstream shell, the latter connecting the disk and upstream cone.
  • the fastening element for connecting the ferrule to the disc must necessarily be positioned under the space reserved for the radial displacement of the lock (that is to say, even closer to the center of the disc).
  • the radial space required for the insertion or removal of the latch by radial translation is unfavorable to reduce the diameter of the disc to its free end upstream at its teeth, to the detriment of the freedom of choice of the aerodynamic profile and the diameter of the upstream ferrule and the upstream cone.
  • the purpose of the invention is therefore to overcome the disadvantages of the prior art by proposing a rotary turbine engine assembly provided with an axial retention system of a blade, such a holding system comprising a latch closing the opening of the engine. a groove in which is inserted a blade, and whose establishment and / or withdrawal is not achieved by a radial translation of said lock in particular in / out of a notch provided for this purpose.
  • the holding system according to the invention must also, and therefore, make it possible to use the space usually provided to allow the insertion or withdrawal of the lock in its slot, in order to reduce certain manufacturing constraints of the disk, and particular manufacturing constraints related to the placement on the disc of the fastening between the ferrule and the disc.
  • another object of the invention is to provide a rotating turbomachine assembly provided with the previous holding system, wherein the attachment of the ferrule to the disc is positioned in the space usually required for insertion or removal. of the lock, so that the ferrule-disk attachment is positioned higher on the disk pin, at the periphery of the disk, that is to say more radially away from the center of the rotor disk.
  • Another object of the invention is to propose a turbojet engine comprising such a rotary assembly.
  • the invention also aims to propose a method of mounting the previous holding system to a rotating assembly of a turbomachine for axially holding one or more of its blades.
  • Another object of the invention relates to a turbomachine comprising one or more rotary assembly (s) comprising at least one axial retention system of a blade of the rotor disk described above.
  • the invention relates to a rotary assembly of a turbomachine, and in particular a turbojet, provided with a system for axially holding at least one blade of a rotor disk.
  • a disk of a blower of a turbojet engine said fan being positioned upstream of a compressor module, or a compressor stage, for example, with vanes reported on the disk.
  • turbomachine any type of turbomachine, and in particular to a turbojet, the latter being in particular simple flow or double flow.
  • turbojets are well known to those skilled in the art and therefore will not be detailed further in this text.
  • the rotor disk 1 is rotated about a longitudinal axis A by a fan shaft.
  • the disc comprises at its outer periphery a circumferential alternation of teeth 10 and grooves 20 which extend axially, that is to say in a direction substantially parallel to the axis A of the disc.
  • Blades 30 (shown on the Figures 2A, 2B, 2C ), whose feet 31 are adapted to be engaged axially in the grooves 20 of the disk and retained radially by the teeth 10, extend radially around the disk.
  • Plates 45 are generally provided on the disc 1, and extend circumferentially between each pair of adjacent blades.
  • the rotor disk 1 is of the pin-shaped type 2, in that it comprises a pin 2 of said disk having a curved profile at the head of the pin that moves radially away from the axis of the disk upstream .
  • This curved profile at the head of the pin is a substantially C-shaped profile comprising an outer axial branch which delimits the teeth 10 of the disc, an inner branch which extends at least on a component substantially axially closer to the motor axis. the outer branch, and a radially-connected connecting front branch, which conventionally comprises an advance 40.
  • the fastening element 41 of the ferrule 43 is generally in the form of a hook provided with an orifice 42 enabling the ferrule 43 to be fixed to the disk pin 2 1 by screwing.
  • the ferrule 43 is connected further upstream to an upstream cone 44 forming the internal and upstream boundary of a fluid circulation vein of the turbomachine.
  • FIGS. 2A, 2B, and 2C illustrate a portion of a rotary assembly, centered on a groove 20 of the disc 1, a blade 30 inserted in the groove 20 is held axially by the holding system according to the invention, and the mounting of such a system of maintaining on the upstream face of the rotor disc 1.
  • the holding system according to the invention, and the mounting of such a system of maintaining on the upstream face of the rotor disc 1.
  • axial retention means that the blade is immobilized axially thanks to the holding system, and that any displacement along the longitudinal axis A of the rotor disk is therefore made impossible.
  • a blade 30 is mounted on the rotor disc 1 by inserting its foot 31 into the corresponding groove 20 of the disc.
  • the groove has a flared shape, and is limited circumferentially by two consecutive teeth 10 of the disc. It extends axially along the rotor disc, and comprises a bottom 21, bordered by two edges 22 common with the teeth 10, and an opening 23 which constitutes the upstream axial end of the groove 20 and whose bottom 21 is located in the vicinity of the disk pin 2.
  • the blade root 31 has a flared shape substantially corresponding to the shape of the groove 20 into which it is inserted. It is formed by two sides 32 which extend axially facing the borders 22 of the groove 20, by an upstream front 33 connecting the two sides 32, and a base 34 which extends axially, facing the bottom 21 of the groove.
  • the blade root 31 is mounted in the groove so that its upstream edge 33 is located in the plane P of the rotor disk 1, orthogonal to the axis A of the disk, and containing the ends 13 of the teeth 10. In other words, the upstream front 33 of the blade root 31 and the ends 13 of the teeth 10 have substantially the same axial position.
  • a tooth 10 extends axially along the outer periphery of the disc 1 and comprises two side edges 11 common to the borders of the grooves 20 which it defines.
  • the edges 20 of the tooth are connected by an upper face 12 and terminate axially by an end 13.
  • the opening 23 of the groove is bordered by the ends 13 of the teeth 10.
  • the front 33 upstream of the foot dawn, the opening 23 of the groove, and the ends 13 of the teeth are located in the plane P of the rotor disk 1.
  • the ends 13 are upstream axial ends in the form of a surface on which the holding system is mountable in accordance with the following.
  • the teeth 10 advantageously comprise grooves 14 which extend along their upper face 12, serving to accommodate platforms 45. It will be understood that such grooves are optional, as well as the platforms they accommodate.
  • the latch 501 of the holding system is pressed against the ends 13 of the teeth of the disk 1 so as to close the opening 23 of the groove. In doing so, the lock 501 bears against the upstream front 33 of the blade root 31. The lock thus prevents the blade root from emerging from the groove through the opening by axial displacement. Note that the closure of the opening 23 by the latch 501 is at least partial, and must be sufficient to prohibit the crossing of the opening by the blade root.
  • the latch 501 is in the form of a part comprising a central portion 511 of which extend the edges 521.
  • the central portion 511 of the lock closes the opening 23 of the groove 20 and abuts against the upstream front 33 of the blade root, and the edges 521 of the lock bear against the ends 13 of the teeth 10.
  • removable parts 502 are mounted at the ends 13 of the teeth, bearing against the latch 501, to lock said latch.
  • the removable parts 502 are therefore the new ends of the teeth on which they are mounted.
  • the removable parts 502 project from the rotor disc 1.
  • the pieces are said to be “removable” in that they can be separated from the ends of the teeth or fixed to said ends of the teeth, by any means provided for this purpose.
  • the lock is said to be “locked” in that it is held stationary, clamped between the ends of the teeth and the removable parts.
  • the edges 521 of the lock 501 bear against both the ends 13 of the teeth, on the downstream surface side of the lock, and against the removable parts 502, on the upstream surface side of the lock.
  • the blade 30 is held axially, in position in its groove 20, by the holding system according to the invention.
  • the shape (or section) of the lock is not limited to the substantially pentagonal shape shown on the Figures 2B and 2C .
  • the shape and the dimensions of the lock will advantageously be chosen so as to allow a total closure of the opening 23 of the groove 20. It will be particularly ensured that the edges 521 of the lock are sufficiently pronounced in order to obtain a satisfactory stop and stable edges of the latch against the ends 13 of the teeth, so as to prevent the latch from pivoting or tilting on itself, and accidentally detaches from the disk 1.
  • the lock may optionally include a spout 541 to facilitate its gripping by a user and thus facilitating its introduction or removal, and may be provided with an orifice 551 to fix it to an underlying shim 60 described in the after.
  • a removable piece 502 when a removable piece 502 is mounted at the end 13 of a tooth, it completely eclipses said end of the tooth. More preferably, the shape (or section) of a removable piece corresponds to the shape of the end of the tooth on which it is mounted, so as to extend the tooth continuously.
  • the removable part 502 comprises in particular grooves 552 corresponding to those of the teeth 10.
  • the removable part 502 once mounted on one end 13 of a tooth 10, bears against said end 13 of the tooth.
  • the removable part 502 comprises two lateral edges 522, and a central portion 512 projecting on the downstream surface of the part, so as to form side recesses 532.
  • the central portion 512 of each removable piece bears against the end 13 of the corresponding tooth, and the lateral recesses 532 of the removable parts 502 abut against the edges 521 of the lock 501.
  • a shim 60 is inserted into the groove 20, between the bottom 21 of the groove and the base 34 of the root of the blade.
  • the shim 60 is located under the lock, that is to say between the periphery of the disk and the lock.
  • the wedge 60 makes it possible to exert a force directed radially towards the outside of the disc on the blade root 31, thus pushing the sides 32 of the blade root against the lateral edges 22 of the groove, which limits the movement of the blade. dawn with respect to the disk, and particularly the radial displacement of the blade and the rotation of the blade around the axis of its foot (circumferential movement).
  • the shim 60 may be provided with an orifice in order to be fixed to the spout 541 of the lock 501 by means of an orifice 551, by means of a rod for example.
  • the removable parts 502 and the ends 13 of the teeth advantageously comprise attachment means for connecting said removable parts to said ends of the teeth.
  • the attachment means respectively comprise a first axial orifice 542 provided on the removable parts 520 and a second axial orifice 15 provided in the ends 13 of the teeth.
  • the teeth 10 may further comprise a third orifice 16 on their upper face 12, in the vicinity of their end 13, said third orifice 16 being orthogonal to the second orifice 15, opening on the second orifice, and being adapted to for example, to receive a barrel nut.
  • a holding system adapted to prohibit the rotation of the removable parts 502 about the axis of the rod inserted in the orifice 542 which connects them to the end 13 of the teeth.
  • Any known means of angular indexing allowing to prohibit the rotation of the removable parts 502 can be envisaged. It is for example two additional orifices arranged respectively in the removable parts and in the ends of the teeth, parallel to the first orifice 542 and at the second port 15 above, and a rod housed in said additional holes. It may also be a pin or an indexing finger adapted to be housed in said additional holes.
  • the removable parts may also comprise a shoulder bearing against the upper face 12 of the teeth 10.
  • An advantage of the holding system according to the invention is that it makes it possible to use the space located at the periphery of the disk, on the disk pin 2 when the latter is of pin-shaped type, usually necessary for the inserting or removing the latch at the opening 23 of the groove 20.
  • the holding system makes it possible to relax the dimensioning constraints related to the positioning of the fixing element 41 of the ferrule on the disk 1 provided on the end 40 of the disk pin 2.
  • the ferrule-disk attachment element 41, and by extension the advanced 40 can indeed be positioned higher on the pin of the disk, at the periphery of the disk, that is to say be more distant from the center of the disc, as shown in arrow 46 of Figure 4 .
  • the advance 40 comprises a fixing element 41 which is advantageously in the form of a hook and which is provided with a hole 42 for fixing the ferrule to the disc 1.
  • the arrow 46 indicates that the hook of the fastener 41 is positioned higher on the disc pin 2, it is that is, more radially away from the center of the disc, compared to the existing one.
  • the holding system according to the invention thus makes it possible to reduce the overhang of the ferrule (or the "clearance” of the ferrule ") which corresponds to the part D of ferrule which extends from the fastening element. 41 (from advanced 40) to its outer periphery (on the Figure 4 it is the "high” part of the ferrule). This reduces the torque between the attachment of the shell and the outer periphery of the shell.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP17197598.0A 2016-10-21 2017-10-20 Rotationseinheit einer strömungsmaschine, die mit einem axialen haltesystem einer laufradschaufel ausgestattet ist Active EP3312384B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1660237A FR3057908B1 (fr) 2016-10-21 2016-10-21 Ensemble rotatif d'une turbomachine muni d'un systeme de maintien axial d'une aube

Publications (2)

Publication Number Publication Date
EP3312384A1 true EP3312384A1 (de) 2018-04-25
EP3312384B1 EP3312384B1 (de) 2020-03-11

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Application Number Title Priority Date Filing Date
EP17197598.0A Active EP3312384B1 (de) 2016-10-21 2017-10-20 Rotationseinheit einer strömungsmaschine, die mit einem axialen haltesystem einer laufradschaufel ausgestattet ist

Country Status (4)

Country Link
US (1) US10570757B2 (de)
EP (1) EP3312384B1 (de)
CN (1) CN107975389B (de)
FR (1) FR3057908B1 (de)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2571176B (en) * 2017-12-14 2022-07-20 Safran Aircraft Engines Damping device
US11306601B2 (en) 2018-10-18 2022-04-19 Raytheon Technologies Corporation Pinned airfoil for gas turbine engines
US10851841B1 (en) 2019-08-14 2020-12-01 Bell Helicopter Textron Inc. Integrated blade root bearing carrier assembly

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3936222A (en) * 1974-03-28 1976-02-03 United Technologies Corporation Gas turbine construction
US4502841A (en) * 1982-11-08 1985-03-05 S.N.E.C.M.A. Fan blade axial locking device
US5259728A (en) * 1992-05-08 1993-11-09 General Electric Company Bladed disk assembly
US6634863B1 (en) * 2000-11-27 2003-10-21 General Electric Company Circular arc multi-bore fan disk assembly
US20080226458A1 (en) * 2007-03-16 2008-09-18 Snecma Turbomachine fan
FR2974864A1 (fr) * 2011-05-04 2012-11-09 Snecma Rotor de turbomachine avec moyen de retenue axiale des aubes
FR3033180A1 (fr) * 2015-02-26 2016-09-02 Snecma Assemblage d'une plateforme rapportee d'aube de soufflante sur un disque de soufflante

Family Cites Families (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2949278A (en) * 1956-07-05 1960-08-16 Gen Motors Corp Turbine blade retention
US3501249A (en) * 1968-06-24 1970-03-17 Westinghouse Electric Corp Side plates for turbine blades
US3644058A (en) * 1970-05-18 1972-02-22 Westinghouse Electric Corp Axial positioner and seal for turbine blades
US3748060A (en) * 1971-09-14 1973-07-24 Westinghouse Electric Corp Sideplate for turbine blade
US4033705A (en) * 1976-04-26 1977-07-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Blade retainer assembly
FR2502690B1 (fr) * 1981-03-27 1985-09-13 Snecma Dispositif de verrouillage d'aubes de soufflante et de fixation de capot avant d'un turboreacteur
FR2535794A1 (fr) * 1982-11-08 1984-05-11 Snecma Dispositif de retenue axiale et radiale d'aubes de soufflante
US4659285A (en) * 1984-07-23 1987-04-21 United Technologies Corporation Turbine cover-seal assembly
US4778342A (en) * 1985-07-24 1988-10-18 Imo Delaval, Inc. Turbine blade retainer
US4872810A (en) * 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system
FR2679599A1 (fr) * 1991-07-24 1993-01-29 Snecma Perfectionnement aux roues a aubes de turbomachines.
US5161951A (en) * 1991-08-05 1992-11-10 Westinghouse Electric Corp. Apparatus and method for preventing axial movement of a disc along a shaft
US5282720A (en) * 1992-09-15 1994-02-01 General Electric Company Fan blade retainer
US5350279A (en) * 1993-07-02 1994-09-27 General Electric Company Gas turbine engine blade retainer sub-assembly
FR2716931B1 (fr) * 1994-03-03 1996-04-05 Snecma Système d'équilibrage et d'amortissement d'un dique de turbomachine.
US5993160A (en) * 1997-12-11 1999-11-30 Pratt & Whitney Canada Inc. Cover plate for gas turbine rotor
JP2003526039A (ja) * 1999-03-19 2003-09-02 シーメンス アクチエンゲゼルシヤフト 内部冷却式ガスタービン翼付きのガスタービンロータ
US6457942B1 (en) * 2000-11-27 2002-10-01 General Electric Company Fan blade retainer
FR2889264B1 (fr) * 2005-07-29 2007-11-02 Snecma Verrouillage des aubes dans un rotor de soufflante
US7901187B2 (en) * 2006-06-23 2011-03-08 Siemens Energy, Inc. Turbine rotor blade groove entry slot lock structure
EP1892380A1 (de) * 2006-08-25 2008-02-27 Siemens Aktiengesellschaft Schaufelbefestigung einer Turbine
FR2945329B1 (fr) * 2009-05-06 2011-06-03 Snecma Rotor de soufflante d'un turboracteur d'avion
FR2961847B1 (fr) * 2010-06-25 2012-08-17 Snecma Roue mobile a aubes en materiau composite pour moteur a turbine a gaz a liaison pied d'aube/disque par serrage
US9249676B2 (en) * 2012-06-05 2016-02-02 United Technologies Corporation Turbine rotor cover plate lock
US9376926B2 (en) * 2012-11-15 2016-06-28 United Technologies Corporation Gas turbine engine fan blade lock assembly
EP2767678A1 (de) * 2013-02-19 2014-08-20 Siemens Aktiengesellschaft Schaufelrad und Verfahren zum Herstellen einer Schaufel
JP5999845B2 (ja) * 2013-11-20 2016-09-28 三菱重工業株式会社 タービンロータ組立体およびタービンロータ組立体における翼止板並びに翼止板の組付け方法
EP2884051A1 (de) * 2013-12-13 2015-06-17 Siemens Aktiengesellschaft Rotor für eine Strömungsmaschine, Strömungsmaschine, Axialverdichter, Gasturbine und Verfahren zum Herstellen eines Rotors einer Strömungsmaschine
EP2937517B1 (de) * 2014-04-24 2019-03-06 Safran Aero Boosters SA Stator einer axialen Turbomaschine und zugehörige Turbomaschine
CN204225928U (zh) * 2014-11-28 2015-03-25 哈尔滨广瀚燃气轮机有限公司 新型涡轮机动叶与轮盘固定结构
US10018065B2 (en) * 2015-09-04 2018-07-10 Ansaldo Energia Ip Uk Limited Flow control device for rotating flow supply system
US10371163B2 (en) * 2016-02-02 2019-08-06 General Electric Company Load absorption systems and methods
KR101882109B1 (ko) * 2016-12-23 2018-07-25 두산중공업 주식회사 가스 터빈
US10876420B2 (en) * 2017-09-14 2020-12-29 DOOSAN Heavy Industries Construction Co., LTD Turbine blade axial retention and sealing system

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3936222A (en) * 1974-03-28 1976-02-03 United Technologies Corporation Gas turbine construction
US4502841A (en) * 1982-11-08 1985-03-05 S.N.E.C.M.A. Fan blade axial locking device
US5259728A (en) * 1992-05-08 1993-11-09 General Electric Company Bladed disk assembly
US6634863B1 (en) * 2000-11-27 2003-10-21 General Electric Company Circular arc multi-bore fan disk assembly
US20080226458A1 (en) * 2007-03-16 2008-09-18 Snecma Turbomachine fan
FR2974864A1 (fr) * 2011-05-04 2012-11-09 Snecma Rotor de turbomachine avec moyen de retenue axiale des aubes
FR3033180A1 (fr) * 2015-02-26 2016-09-02 Snecma Assemblage d'une plateforme rapportee d'aube de soufflante sur un disque de soufflante

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Publication number Publication date
EP3312384B1 (de) 2020-03-11
FR3057908B1 (fr) 2019-11-22
CN107975389B (zh) 2022-02-22
FR3057908A1 (fr) 2018-04-27
US10570757B2 (en) 2020-02-25
CN107975389A (zh) 2018-05-01
US20180112545A1 (en) 2018-04-26

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