EP0091865A1 - Axialfesthalter des Schaufelfusses in einem Turbinenrotor - Google Patents

Axialfesthalter des Schaufelfusses in einem Turbinenrotor Download PDF

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Publication number
EP0091865A1
EP0091865A1 EP83400696A EP83400696A EP0091865A1 EP 0091865 A1 EP0091865 A1 EP 0091865A1 EP 83400696 A EP83400696 A EP 83400696A EP 83400696 A EP83400696 A EP 83400696A EP 0091865 A1 EP0091865 A1 EP 0091865A1
Authority
EP
European Patent Office
Prior art keywords
groove
cover
blade
circumferential groove
locking means
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
EP83400696A
Other languages
English (en)
French (fr)
Other versions
EP0091865B1 (de
Inventor
Marcel Louis Antoine Rigo
Gilbert Sourdeval
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
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA 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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0091865A1 publication Critical patent/EP0091865A1/de
Application granted granted Critical
Publication of EP0091865B1 publication Critical patent/EP0091865B1/de
Expired legal-status Critical Current

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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

Definitions

  • the invention relates to a device for axially retaining blade roots in a turbomachine rotor disk, for example a compressor disk to which a front cover is capable of being fixed, the blade roots being retained radially in axial grooves provided in the rim of the disc, the feet carrying a projecting part relative to the upstream face of the disc directed radially towards the center of the disc, the disc having on its upstream face a rim carrying a circumferential groove open radially outward receiving at least part of the axial locking means of the blade roots.
  • French patent 2,028,539 describes a blade blocking and sealing system allowing the cooling of the blade roots.
  • the rotor disc carries at its periphery axial grooves in which the blade roots are retained.
  • a rim of diameter smaller than that determined by the bottoms of the grooves is provided on the upstream face of the disc and has a circumferential groove directed radially outwards.
  • the blade roots are provided at their upper part with a spoiler in which is provided a transverse groove whose opening is directed towards the center of the disc.
  • Plates are engaged radially in the circumferential groove of the disc and in the groove of the blade roots and are held temporarily by pliers. When all the plates are placed, they are positioned by circumferential displacement in front of threaded orifices, provided in the edge of the groove, which receive bolts intended to immobilize the plates. Each plate holds several blade feet and forms with them an annular channel in which the coolant circulates.
  • French patent 2,090,105 presents a system having functions similar to the previous one.
  • the rotor disc carries on its downstream face a rim whose circumferential groove opens radially outwards.
  • the blade roots have at their lower part a shoulder which presses against the branches of L-shaped sealing segments housed in the groove.
  • Locking segments are placed inside the L-shaped segments.
  • a locking screw is fixed in the edge of the groove and keeps the L-shaped segments and the locking segments in position.
  • Clamping screws, cooperating with threads provided in the locking segments act on the sealing segments.
  • the device according to the invention aims to provide a 3 device for axially retaining the feet of the blade comprising a limited number of elements held by the means carried at least in part by the front cover.
  • Figure 1 shows an axial section of part of a rotor.
  • the rim of the rotor disc 1 carries axial grooves in which the feet 2 of the blades 3 are retained radially.
  • a front cover 4 is fixed on the upstream face of the disc in the extension of the platforms 5 of the blade.
  • the blade roots bear on their upstream end, a part 6 or spoiler, projecting with respect to the face of the disc and directed radially towards its center.
  • the purpose of this spoiler is to directly or indirectly prevent the axial movement of the blade.
  • the spoiler 6 extends over the height of the foot and its lower end is at the same radius as the lower part of the blade root or at a slightly larger radius.
  • This spoiler has in a radial plane a transverse groove 7 whose downstream edge is in the plane of the face 8 of the disc when the blade is in place. This spoiler shape allows the blade to be put in place by the downstream or upstream face of the disc.
  • the spoiler 9 extends below the plane of the lower part of the foot and engages against the upstream face 8 of the disc preventing axial movement of the blade from upstream to downstream.
  • the upstream face 8 of the disc (FIG. 1) has a rim 10 in which is provided a circumferential groove 11 open radially towards the outside receiving at least part of the means of axial locking of the blade roots.
  • the front cover 4 carries an internally fixed element in the form of a cylindrical shell 12 to the free end of which is provided at least one other part of the locking means cooperating directly or indirectly with the spoilers 6 of the blade roots.
  • the part of the locking means cooperating with the groove 11 consists of at least two ring portions 13, 14.
  • the length of the annular segment formed by the ring portions placed end to end is less than at least one width axial groove with respect to the circumference length of a complete ring.
  • the opening thus obtained, between the ends of the portions or ring segments 13, 14 when the other ends or the ends of the intermediate segments are in contact, can, by circumferential sliding of the assembly, be brought before any axial groove whose blade is to be changed.
  • Figures 1 to 3 show a particular embodiment of the ring segments 13 and 14 in the form of cylindrical ring portions limited by two radial flanges.
  • the section affects the appearance of a U with unequal branches whose width corresponds to that of the circumferential groove 11.
  • the bottom of the groove has a bearing 16, circular on which the cylindrical inner wall 17 rests ring portions.
  • the longest branch of the U-shaped section corresponds to the widest flange 18. Its dimensions are approximately equal to the depth and width of the groove 7 formed in the spoiler 6, so that it can be placed between the upstream face 8 of the disc and in the groove 7 of the spoiler.
  • the shortest branch corresponds to the narrowest collar 19 and its height is at most equal to the depth of the circumferential groove 11 limited to the surface of the bearing surface 16.
  • the locking means carried by the cover 4 are formed by a cylindrical ferrule 12, coaxial with the rotor disc, the free edge 20 of which carries two fingers 21 arranged diametrically. Preferably, these fingers have the same width, approximately equal to half a width of the axial groove.
  • the height of the fingers 21 is such that each comes to be placed between the edges of the segments 13, 14, and more precisely between the edges of the flanges 18 of two segments neighbors. In this position, the segments 13 and 14 leave at each end a clearance 15 (see fig. 3) equal (or slightly greater) to half the peripheral length of the blade root.
  • Figure 3 shows in section on III-III of Figure 1 a finger 21 in place between the segments 13, 14 circumferentially locking thereof.
  • the coaxial ferrule can be replaced by an inner radial flange as indicated, for example, at 27 and 34 in FIGS. 5 and 7.
  • FIG. 4 shows another embodiment of the ends of the segments 13, 14, having in their upper edge a rectangular notch 23.
  • the dimensions of this notch are such that, when the two segments 13, 14 are brought end to end in the circumferential groove 11, the notches of the two nonadjacent ends completely disengage the lower part of the axial radial retaining groove of a blade, or allow at least the passage of the spoiler 6.
  • This embodiment allows, between the ends from the lower edge of the segments 13, 14, an opening 15 of width half by compared to straight edges with the result that the segments in the groove are better held.
  • FIGS. 5 and 6 Another embodiment of the segments 13, 14 is shown in FIGS. 5 and 6.
  • the segments form a roughly closed ring.
  • the widest collar 18 is cut so as to have teeth 24 on its outer edge.
  • the distance between two neighboring teeth corresponds to the distance between two axial grooves.
  • the teeth 24 are brought either into the groove 7 of the spoilers 6, or in front of the teeth 25 of the rotor rim.
  • These positions allow respectively to lock or unlock all the blades.
  • they are provided with positioning means formed by bosses or pins 26 which cooperate with part of the locking means carried by the cover 4 and, more particularly, by a ferrule. coaxial or a radial flange 27 provided in the cover, and whose free edge has housings or notches 28 in which the bosses or the pins are placed. Attaching the cover to the rotor disc locks the segments in the circumferential direction.
  • the locking of the segments can also be obtained as in the example of FIG. 1 by fingers, carried by the cover, coming to be placed between two or more teeth of the segments or in housings provided in the narrower flange 19.
  • a third embodiment, shown in FIGS. 7 to 9, is more particularly suited to blades whose protruding part of the foot or spoiler 29 extends radially towards the center below the plane of the part lower of the blade root.
  • This arrangement makes it possible to prevent the axial movement of the blade, from upstream to downstream in the groove by pressing the downstream face of the spoiler against the upstream face 8 of the rotor disc and does not allow the disassembly of the dawn only upstream.
  • teeth 32 are formed in the upstream edge 30 of the circumferential groove 11 and opposite the axial grooves.
  • the other part of the locking means carried by the cover also consists of teeth 33 of dimensions and shape such that they can pass through the indentations 31 of the edge of the groove 11 and be placed between the teeth 32 of said edge and the upstream face of the blade spoilers 29.
  • the teeth 33 are formed in the free edge of a cylindrical shell or of a radial flange 34 provided in the cover.
  • the locking or unlocking of the blades is obtained during the fitting of the cover by rotation of the latter by a half-step corresponding to the distance between an axial groove and the adjacent tooth of the rotor disc.
  • the teeth 32 form intermediate flange elements, which take up the forces without having thicknesses which are too penalizing for the mass.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP83400696A 1982-04-08 1983-04-06 Axialfesthalter des Schaufelfusses in einem Turbinenrotor Expired EP0091865B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8206118 1982-04-08
FR8206118A FR2524932A1 (fr) 1982-04-08 1982-04-08 Dispositif de retenue axiale de pieds d'aube dans un disque de turbomachine

Publications (2)

Publication Number Publication Date
EP0091865A1 true EP0091865A1 (de) 1983-10-19
EP0091865B1 EP0091865B1 (de) 1985-06-19

Family

ID=9272877

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83400696A Expired EP0091865B1 (de) 1982-04-08 1983-04-06 Axialfesthalter des Schaufelfusses in einem Turbinenrotor

Country Status (5)

Country Link
US (1) US4470756A (de)
EP (1) EP0091865B1 (de)
JP (1) JPS58187503A (de)
DE (1) DE3360301D1 (de)
FR (1) FR2524932A1 (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4701105A (en) * 1986-03-10 1987-10-20 United Technologies Corporation Anti-rotation feature for a turbine rotor faceplate
FR2641325A1 (fr) * 1988-12-30 1990-07-06 Gen Electric Dispositif de retenue des aubes d'un rotor exempt de boulons et procede de maintien des aubes sur un disque de rotor
EP0463955A1 (de) * 1990-06-27 1992-01-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Befestigung eines Kranzes an einem Turbinenlaufrad
FR2729709A1 (fr) * 1995-01-25 1996-07-26 Snecma Dispositif d'etancheite et de retention des aubes de rotor de turbomachine
EP2011969A1 (de) * 2007-07-03 2009-01-07 Siemens Aktiengesellschaft Turbinenanordnung sowie Verfahren zur Befestigung eines Einbauelements
FR2971822A1 (fr) * 2011-02-21 2012-08-24 Snecma Rotor de soufflante, en particulier pour une turbomachine
EP2599966A3 (de) * 2011-11-29 2014-06-11 General Electric Company Schaufelrandleiste
US9411016B2 (en) 2010-12-17 2016-08-09 Ge Aviation Systems Limited Testing of a transient voltage protection device

Families Citing this family (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4558988A (en) * 1983-12-22 1985-12-17 United Technologies Corporation Rotor disk cover plate attachment
FR2566061B1 (fr) * 1984-06-14 1988-09-02 Snecma Dispositif de verrouillage axial d'une aube de turbomachine
US4669959A (en) * 1984-07-23 1987-06-02 United Technologies Corporation Breach lock anti-rotation key
FR2585069B1 (fr) * 1985-07-16 1989-06-09 Snecma Dispositif de limitation du debattement angulaire d'aubes montees sur un disque de rotor de turbomachine
DE3743253A1 (de) * 1987-12-19 1989-06-29 Mtu Muenchen Gmbh Axial durchstroemtes laufschaufelgitter fuer verdichter oder turbinen
US4836750A (en) * 1988-06-15 1989-06-06 Pratt & Whitney Canada Inc. Rotor assembly
US4846628A (en) * 1988-12-23 1989-07-11 United Technologies Corporation Rotor assembly for a turbomachine
JPH0471957A (ja) * 1990-07-10 1992-03-06 Isuzu Motors Ltd リターダのトルク制御装置
US5067877A (en) * 1990-09-11 1991-11-26 United Technologies Corporation Fan blade axial retention device
US5112193A (en) * 1990-09-11 1992-05-12 Pratt & Whitney Canada Fan blade axial retention device
US5151013A (en) * 1990-12-27 1992-09-29 United Technologies Corporation Blade lock for a rotor disk and rotor blade assembly
US5281098A (en) * 1992-10-28 1994-01-25 General Electric Company Single ring blade retaining assembly
US5338154A (en) * 1993-03-17 1994-08-16 General Electric Company Turbine disk interstage seal axial retaining ring
US5318405A (en) * 1993-03-17 1994-06-07 General Electric Company Turbine disk interstage seal anti-rotation key through disk dovetail slot
FR2715975B1 (fr) * 1994-02-10 1996-03-29 Snecma Rotor de turbomachine à rainures d'aube débouchantes axiales ou inclinées.
US6174129B1 (en) 1999-01-07 2001-01-16 Siemens Westinghouse Power Corporation Turbine vane clocking mechanism and method of assembling a turbine having such a mechanism
DE19960896A1 (de) * 1999-12-17 2001-06-28 Rolls Royce Deutschland Rückhaltevorrichtung für Rotorschaufeln einer Axialturbomaschine
US7252481B2 (en) * 2004-05-14 2007-08-07 Pratt & Whitney Canada Corp. Natural frequency tuning of gas turbine engine blades
JP2007247407A (ja) * 2006-03-13 2007-09-27 Ihi Corp ファンブレードの保持構造
JP2007247406A (ja) * 2006-03-13 2007-09-27 Ihi Corp ファンブレードの保持構造
EP1916389A1 (de) * 2006-10-26 2008-04-30 Siemens Aktiengesellschaft Turbinenschaufel Anordnung
FR2930595B1 (fr) * 2008-04-24 2011-10-14 Snecma Rotor de soufflante d'une turbomachine ou d'un moteur d'essai
US8439635B2 (en) * 2009-05-11 2013-05-14 Rolls-Royce Corporation Apparatus and method for locking a composite component
US8435006B2 (en) * 2009-09-30 2013-05-07 Rolls-Royce Corporation Fan
US8491267B2 (en) 2010-08-27 2013-07-23 Pratt & Whitney Canada Corp. Retaining ring arrangement for a rotary assembly
US8905717B2 (en) 2010-10-06 2014-12-09 General Electric Company Turbine bucket lockwire rotation prevention
FR2974863B1 (fr) * 2011-05-06 2015-10-23 Snecma Disque de soufflante de turbomachine
US9112383B2 (en) 2011-10-31 2015-08-18 General Electric Company System and method for Var injection at a distributed power generation source
FR2982635B1 (fr) * 2011-11-15 2013-11-15 Snecma Roue a aubes pour une turbomachine
FR3011032B1 (fr) * 2013-09-25 2017-12-29 Snecma Ensemble rotatif pour turbomachine
FR3025553B1 (fr) * 2014-09-08 2019-11-29 Safran Aircraft Engines Aube a becquet amont
US10428661B2 (en) * 2016-10-26 2019-10-01 Roll-Royce North American Technologies Inc. Turbine wheel assembly with ceramic matrix composite components
KR101877170B1 (ko) * 2017-04-11 2018-08-07 두산중공업 주식회사 로터 디스크 실링장치와 이를 구비하는 로터 조립체 및 가스터빈

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1158880A (fr) * 1955-09-26 1958-06-20 Rolls Royce Perfectionnements aux machines à fluide pourvues de rotors à aubes
US3023998A (en) * 1959-03-13 1962-03-06 Jr Walter H Sanderson Rotor blade retaining device
US3397865A (en) * 1966-09-13 1968-08-20 Rolls Royce Bladed rotor for a fluid flow machine such as a gas turbine engine
GB2038959A (en) * 1979-01-02 1980-07-30 Gen Electric Turbomachinery blade retaining assembly
GB2058945A (en) * 1979-09-28 1981-04-15 United Technologies Corp Rotor assembly

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB928349A (en) * 1960-12-06 1963-06-12 Rolls Royce Improvements in or relating to bladed rotors of fluid flow machines
GB1259750A (en) * 1970-07-23 1972-01-12 Rolls Royce Rotor for a fluid flow machine
US3936234A (en) * 1975-02-10 1976-02-03 General Electric Company Device for locking turbomachinery blades
FR2358545A1 (fr) * 1976-07-16 1978-02-10 Snecma Perfectionnements aux dispositifs d'equilibrage de rotors
US4349318A (en) * 1980-01-04 1982-09-14 Avco Corporation Boltless blade retainer for a turbine wheel
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

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1158880A (fr) * 1955-09-26 1958-06-20 Rolls Royce Perfectionnements aux machines à fluide pourvues de rotors à aubes
US3023998A (en) * 1959-03-13 1962-03-06 Jr Walter H Sanderson Rotor blade retaining device
US3397865A (en) * 1966-09-13 1968-08-20 Rolls Royce Bladed rotor for a fluid flow machine such as a gas turbine engine
GB2038959A (en) * 1979-01-02 1980-07-30 Gen Electric Turbomachinery blade retaining assembly
GB2058945A (en) * 1979-09-28 1981-04-15 United Technologies Corp Rotor assembly

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4701105A (en) * 1986-03-10 1987-10-20 United Technologies Corporation Anti-rotation feature for a turbine rotor faceplate
FR2641325A1 (fr) * 1988-12-30 1990-07-06 Gen Electric Dispositif de retenue des aubes d'un rotor exempt de boulons et procede de maintien des aubes sur un disque de rotor
GB2226856A (en) * 1988-12-30 1990-07-11 Gen Electric A boltless rotor blade retainer
GB2226856B (en) * 1988-12-30 1993-09-01 Gen Electric Boltless rotor blade retainer
EP0463955A1 (de) * 1990-06-27 1992-01-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Befestigung eines Kranzes an einem Turbinenlaufrad
FR2663997A1 (fr) * 1990-06-27 1992-01-03 Snecma Dispositif de fixation d'une couronne de revolution sur un disque de turbomachine.
US5173024A (en) * 1990-06-27 1992-12-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Fixing arrangement for mounting an annular member on a disk of a turboshaft engine
FR2729709A1 (fr) * 1995-01-25 1996-07-26 Snecma Dispositif d'etancheite et de retention des aubes de rotor de turbomachine
EP2011969A1 (de) * 2007-07-03 2009-01-07 Siemens Aktiengesellschaft Turbinenanordnung sowie Verfahren zur Befestigung eines Einbauelements
US9411016B2 (en) 2010-12-17 2016-08-09 Ge Aviation Systems Limited Testing of a transient voltage protection device
FR2971822A1 (fr) * 2011-02-21 2012-08-24 Snecma Rotor de soufflante, en particulier pour une turbomachine
WO2012114032A1 (fr) * 2011-02-21 2012-08-30 Snecma Rotor de soufflante et turboréacteur associé
RU2594037C2 (ru) * 2011-02-21 2016-08-10 Снекма Ротор вентилятора и турбореактивный двигатель
US9540935B2 (en) 2011-02-21 2017-01-10 Snecma Fan rotor and associated turbojet engine
EP2599966A3 (de) * 2011-11-29 2014-06-11 General Electric Company Schaufelrandleiste
US9039382B2 (en) 2011-11-29 2015-05-26 General Electric Company Blade skirt

Also Published As

Publication number Publication date
DE3360301D1 (en) 1985-07-25
EP0091865B1 (de) 1985-06-19
FR2524932B1 (de) 1984-07-20
JPS58187503A (ja) 1983-11-01
FR2524932A1 (fr) 1983-10-14
JPH0116961B2 (de) 1989-03-28
US4470756A (en) 1984-09-11

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