EP0083289B1 - Rotorrad eines Turbostrahltriebwerkes mit einer Vorrichtung zum axialen und radialen Befesten der Rotorschaufeln am Rotorrad - Google Patents

Rotorrad eines Turbostrahltriebwerkes mit einer Vorrichtung zum axialen und radialen Befesten der Rotorschaufeln am Rotorrad Download PDF

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Publication number
EP0083289B1
EP0083289B1 EP82402387A EP82402387A EP0083289B1 EP 0083289 B1 EP0083289 B1 EP 0083289B1 EP 82402387 A EP82402387 A EP 82402387A EP 82402387 A EP82402387 A EP 82402387A EP 0083289 B1 EP0083289 B1 EP 0083289B1
Authority
EP
European Patent Office
Prior art keywords
blade
groove
root
disc
rotor
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.)
Expired
Application number
EP82402387A
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English (en)
French (fr)
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EP0083289A1 (de
Inventor
Jean-Claude Dhuic
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
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Filing date
Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0083289A1 publication Critical patent/EP0083289A1/de
Application granted granted Critical
Publication of EP0083289B1 publication Critical patent/EP0083289B1/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
    • F01D5/32—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

Definitions

  • the invention relates to a turbomachine rotor wheel provided with an axial and radial blade retaining device on the disc, capable of preventing the blade root and the airfoils from matting, and more particularly a wedge wedge. between the foot of the blade and the bottom of the groove provided in the rim of the rotor disc, according to the first part of claim 1.
  • Axial and radial blade retaining devices are known, such as that described in French Patent No. 2,345,605 and which consists of a shim which is placed between the blade root and the bottom of the groove. so as to press the upper part of the dovetail root against the lateral teeth of the groove, the wedge being held in the axial direction by a U-bolt which cooperates with corresponding notches provided in the foot blade and in the teeth of the groove; the system is simple and efficient.
  • To facilitate, or even make possible the assembly and disassembly of the assembly there are however between the wedge, the blade root and the bottom of the groove of the games (at least for most of the blades) which prove harmful in use. Indeed, during autorotation or low-speed rotation of the rotor, the centrifugal force exerted on the blades is no longer sufficient to keep the blade roots pressed against both the oblique faces of the grooves.
  • the wedge described by the first cited patent consists of three longitudinal pieces, independent, two lateral and a central.
  • the two lateral pieces bear at the ends of two adjacent faces of the heels provided so as to be able to be applied against the front and rear face of the disc, on either side of the groove and against the radial ends of the blade roots.
  • These two symmetrical parts are introduced into the space between the blade root and the bottom of the groove and are separated by the central part in a shape approximately complementary to the remaining space.
  • This part comprises a housing receiving an elastic member bearing against the bottom of the groove.
  • the three parts are, after installation, secured by a bolt.
  • the second patent cited describes a wedge having two side pieces identical to those of the previous patent, but a central piece consisting of two elements and an additional blocking wedge.
  • One of the elements forms a spacer, capable of being elastically deformed in the axial plane, and cooperates with a housing provided in the bar forming the other element and intended to be placed against the bottom of the groove.
  • the installation of the device is done, as before, by introduction of the lateral parts, of the bar, then of the spacer. Is then placed between the ends of the bar and the spacer blocking block which maintains the spacer in pressure against the bar and the blade root.
  • a bolt holds the different parts together and ensures locking.
  • the subject of the invention is a turbomachine rotor wheel provided with a retaining device of the same kind as those previously described, but comprising only a lower number of parts and above all forming an assembly capable of being put in place. or removed in one operation.
  • FIG. 1 shows an exploded view of a device for retaining a rotor blade.
  • Figure 2 is an exploded view of a wedge according to the invention.
  • Figure 3 is a longitudinal sectional view of an element forming the wedge.
  • Figure 4 is a sectional view through the radial plane passing through the middle of the groove of the retaining device according to the invention.
  • Figure 1 shows an exploded view of an axial and radial retaining device of a rotor blade.
  • the rotor disc 1 has in its rim axial grooves 2 having a dovetail section.
  • teeth 3 provided between the grooves bear grooves 4 facing each other, the bottom of which is parallel to the radial plane passing through the middle of the groove.
  • the blade 5, the foot 6 of which has a dovetail shape corresponding to that of the groove, comprises upstream a heel-shaped extension 7, carrying grooves laterally 8.
  • a U-shaped lock 11 of thickness equal to the distance separating the lateral edges of the grooves 4 of the teeth, carries a cutout 12 whose upper part, close to the horizontal branch of the U, has a slot.
  • the cross section of this slot corresponding to the part of the heel 7 between the grooves 8.
  • the central part of the cut has a cross section corresponding to the cross section of the wedge 13.
  • the assembly is carried out as follows: after having slid the blade root 6 into the groove 2, the lock 11 is introduced between the grooves 4 and 8 of the teeth and of the blade root. The lock is then in abutment against the heel 7. The shim 13 is then introduced into the central part of the cutout 12 and between the blade root 6 and the bottom 14 of the groove 2. The shim applies the tail part d dovetail of the blade root against the corresponding parts of the cell constituting the groove 2 of the disc 1.
  • the wedge 13 (FIG. 2) consists of three assembled elements: an elongated part 15, a flexible blade 16 and an axis 17, the mode of cooperation of which will be described later.
  • the elongated part 15 carries, in its longitudinal plane of symmetry, a slot 18 extending over almost its entire length.
  • Two bridges 190 and 200 are provided at the front 19 and rear 20 ends of the part.
  • the bridge 200 formed at the rear end carries a groove 21 the bottom of which has a part, approximately parallel to the lower plane of the part which can be connected to another part 22, inclined towards the inside of the slot and joining the lower shot.
  • the part has at the front end 19 a cross section of height less than that of the rear end 20.
  • the longitudinal sides 181 and 182 of the part 15 are pierced by two coaxial orifices 23 with an axis perpendicular to the plane of longitudinal symmetry of the part.
  • the flexible blade 16 has a thickness less than that of the slot 18 and a length approximately equal to that of the slot and is pierced perpendicular to its longitudinal plane of symmetry with an orifice 24.
  • the blade is formed on either side of this orifice by two branches 25 and 26 whose upper and lower sides are designated respectively by the references 251, 261, 252, 262 respectively form obtuse angles.
  • the branch 25 carries at its upstream free end 27 a cutout 28 in the form of a right-angled dihedral whose planes are connected by a rounded 28 ′ and the end of the branch 26 has a flat bearing 29.
  • a cutout 28 in the form of a right-angled dihedral whose planes are connected by a rounded 28 ′ and the end of the branch 26 has a flat bearing 29. The function of these cutting and bearing will later specified.
  • the wedge 13 is formed by introducing the flexible blade 16 into the slot 18 of the part 15, the bearing 29 of the branch 26 resting on the horizontal bottom of the groove 21, then by connecting them via the axis 17 passing through the orifices 23 of the wedge and 24 of the blade. Therefore the three parts 15, 16, 17 form the shim 13 itself. It should be noted that the angle which the branches of the blade make between them, causes the end 27 to protrude from the lower plane of the wedge when the part 29 rests on the bottom of the groove 21.
  • the shim 13 is introduced, as previously described, into the central cutout 12 of the latch 11 between the blade root 6 and the bottom 14 of the groove of the disc.
  • the cutout 28 of the end of the flexible blade then comes, through the groove 2, to cover the upstream face of the rotor disc.
  • the tool is then dismantled maintaining the stress exerted between the part 15 and the blade 16, which places the horizontal face of the dihedron 28 in abutment on the bottom 14 of the groove 2 and the vertical face of the dihedron 28 in abutment on the face upstream of the disc 1.
  • the shim 13 is thus locked in the axial direction of upstream downstream. Locking in the opposite direction, from downstream to upstream, can be ensured in a known manner by a flange of the front cover coming to bear against the end 19 of the wedge.
  • the elasticity of the blade 16 supports (directly upstream, indirectly via the bridge 200 towards the rear) the wedge 13 on the bottom of the groove.
  • the upper middle of the blade 16 comes into abutment by a bearing 31 on the lower middle part of the blade root, which avoids rattling.
  • the force then exerted is of the order of 200 daN, sufficient to prevent the blade from clicking when the rotor turns in autorotation.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (4)

1. Rotorrad eines Turbostrahltriebwerkes mit einer Vorrichtung zum axialen und radialen Befestigen der Rotorschaufel am Rotorrad, wobei jede Schaufel einen schwalbenschwanzförmigen Fuß besitzt, der in einer entsprechenden Nut des Rotorradkranzes aufgenommen ist, und wobei dieser Rotorradkranz an seinem Umfang und senkrecht zu seiner Stirnseite angeordnete Zähne besitzt, in deren Rändern annähernd radiale Kehlen vorgesehen sind, die ähnlichen in dem Schaft der Schaufel vorgesehenen Kehlen gegenüberliegen und entsprechen, mit einem U-förmigen Riegel, dessen Außenteil mit den Kehlen der Zähne zusammenwirkt und der in seinem zentralen Bereich einen Ausschnitt besitzt, welcher dem Querschnitt eines Keils (13) entspricht, der zwischen dem Schaufelfuß und dem Boden der schwalbenschwanzförmigen Nut aufgenommen ist, wobei der genannte Ausschnitt sich in Richtung auf den horizontalen Steg des U-förmigen Riegels in einen Schlitz verlängert, dessen Ränder mit den Kehlen des Schaufelfußes zusammenarbeiten, dadurch gekennzeichnet,
- daß der Keil (13) einen Aufbau hat, der folgende Teile umfaßt : ein langgestrecktes Teil
(15) mit einem Längsschlitz (18), der sich über fast die gesamte Länge erstreckt, wobei die Längsseiten (181, 182) des Teils (15) koaxiale Bohrungen (23) besitzen,
- eine durch diese Bohrungen (23) hindurchgehenden Achse (17),
- eine von der Achse (17) gehaltene elastische Zunge (16), die in dem Längsschlitz (18) aufgenommen ist und die in Bezug auf die Achse (17) zwei Arme (25, 26) aufweist, deren Oberseiten (251, 261) untereinander und deren Unterseiten (252, 262) untereinander einen stumpfen Winkel bilden, wobei das freie Ende eines Arms (26) sich über eine Auflagefläche (29) auf dem Boden einer an einem der Enden (20) des langgestreckten Teils (15) vorgesehenen Nut (21) abstützt, und das Ende (27) des anderen Arms (25) ein rechteckig abgewinkeltes Teil (28) aufweist, das sich auf dem von dem Boden der Nut gebildeten hochdruckseitigen Rand und der hochdruckseitigen Stirnfläche des Rotorrads abstützt, wobei die genannte elastische Zunge (16) außerdem in der Nähe des Lots der Bohrung (23) der Achse (17) an der Außenseite eine Auflagefläche (31) aufweist, die sich unter dem Schaufelfuß (6) abstützt.
2. Rotorrad nach Anspruch 1, dadurch gekennzeichnet, daß die elastische Zunge (16) an der Unterseite ihres vorderen Endes (27) eine Kerbe (30) für den Eingriff eines Werkzeugs besitzt, das sich auf der Oberseite (190) des vorderen Endes (19) des langgestreckten Teils (15) abstützt, um das vordere Ende der Zunge (16) teilweise in das Innere des Schlitzes (18) zu versenken, wenn der Keil (13) zwischen dem Schaufelfuß (6) und dem Boden (14) der Nut (2) eingeführt wird.
EP82402387A 1981-12-29 1982-12-28 Rotorrad eines Turbostrahltriebwerkes mit einer Vorrichtung zum axialen und radialen Befesten der Rotorschaufeln am Rotorrad Expired EP0083289B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8124355 1981-12-29
FR8124355A FR2519072B1 (fr) 1981-12-29 1981-12-29 Dispositif de retenue axiale et radiale d'aube de rotor de turboreacteur

Publications (2)

Publication Number Publication Date
EP0083289A1 EP0083289A1 (de) 1983-07-06
EP0083289B1 true EP0083289B1 (de) 1985-10-30

Family

ID=9265456

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82402387A Expired EP0083289B1 (de) 1981-12-29 1982-12-28 Rotorrad eines Turbostrahltriebwerkes mit einer Vorrichtung zum axialen und radialen Befesten der Rotorschaufeln am Rotorrad

Country Status (5)

Country Link
US (1) US4474535A (de)
EP (1) EP0083289B1 (de)
JP (1) JPS58119904A (de)
DE (1) DE3267199D1 (de)
FR (1) FR2519072B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3139597A1 (fr) * 2022-09-12 2024-03-15 Safran Aircraft Engines Ensemble de turbomachine

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2566061B1 (fr) * 1984-06-14 1988-09-02 Snecma Dispositif de verrouillage axial d'une aube de turbomachine
US4711007A (en) * 1986-09-29 1987-12-08 Westinghouse Electric Corp. Method and apparatus for installing free standing turbine blades
US5205714A (en) * 1990-07-30 1993-04-27 General Electric Company Aircraft fan blade damping apparatus
GB2262139A (en) * 1991-12-04 1993-06-09 Rolls Royce Plc Fan blade retainer
US5282720A (en) * 1992-09-15 1994-02-01 General Electric Company Fan blade retainer
FR2697285B1 (fr) * 1992-10-28 1994-11-25 Snecma Système de verrouillage d'extrémités d'aubes.
GB9223593D0 (en) * 1992-11-11 1992-12-23 Rolls Royce Plc Gas turbine engine fan blade assembly
US5318405A (en) * 1993-03-17 1994-06-07 General Electric Company Turbine disk interstage seal anti-rotation key through disk dovetail slot
GB9412963D0 (en) * 1994-06-28 1994-09-28 Rolls Royce Plc Gas turbine engine fan blade assembly
FR2728299B1 (fr) * 1994-12-14 1997-01-24 Snecma Dispositif de fixation axiale d'aubes de rotor de turboreacteur
US5720596A (en) * 1997-01-03 1998-02-24 Westinghouse Electric Corporation Apparatus and method for locking blades into a rotor
FR2807096B1 (fr) * 2000-03-30 2002-05-31 Abb Alstom Power Nv Disque rotorique de turbine equipe d'ailettes a pied de sapin et procede de montage d'une ailette sur un disque
US6520742B1 (en) * 2000-11-27 2003-02-18 General Electric Company Circular arc multi-bore fan disk
US6457942B1 (en) * 2000-11-27 2002-10-01 General Electric Company Fan blade retainer
US6481971B1 (en) * 2000-11-27 2002-11-19 General Electric Company Blade spacer
US6739837B2 (en) 2002-04-16 2004-05-25 United Technologies Corporation Bladed rotor with a tiered blade to hub interface
US6786696B2 (en) 2002-05-06 2004-09-07 General Electric Company Root notched turbine blade
GB0216951D0 (en) * 2002-07-20 2002-08-28 Rolls Royce Plc A fan blade assembly
US6736602B2 (en) * 2002-07-31 2004-05-18 United Technologies Corporation Hollow fan hub under blade bumper
FR2911632B1 (fr) * 2007-01-18 2009-08-21 Snecma Sa Disque de rotor de soufflante de turbomachine
US20080273982A1 (en) * 2007-03-12 2008-11-06 Honeywell International, Inc. Blade attachment retention device
US8485785B2 (en) 2007-07-19 2013-07-16 Siemens Energy, Inc. Wear prevention spring for turbine blade
EP2946080B1 (de) * 2013-01-17 2018-05-30 United Technologies Corporation Rotorblatt-wurzel-zwischenstück mit einem griffelement
GB201503303D0 (en) * 2015-02-27 2015-04-15 Rolls Royce Plc Retention device

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3383095A (en) * 1967-09-12 1968-05-14 Gen Electric Lock for turbomachinery blades
US3936234A (en) * 1975-02-10 1976-02-03 General Electric Company Device for locking turbomachinery blades
FR2345605A1 (fr) * 1976-03-25 1977-10-21 Snecma Dispositif de retenue pour aubes de soufflantes
DE2639200A1 (de) * 1976-08-31 1978-03-09 Volkswagenwerk Ag Laufrad fuer axialturbinen, insbesondere fuer gasturbinen
US4208170A (en) * 1978-05-18 1980-06-17 General Electric Company Blade retainer
US4265595A (en) * 1979-01-02 1981-05-05 General Electric Company Turbomachinery blade retaining assembly

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3139597A1 (fr) * 2022-09-12 2024-03-15 Safran Aircraft Engines Ensemble de turbomachine

Also Published As

Publication number Publication date
FR2519072A1 (fr) 1983-07-01
US4474535A (en) 1984-10-02
EP0083289A1 (de) 1983-07-06
JPS58119904A (ja) 1983-07-16
DE3267199D1 (en) 1985-12-05
JPH0131002B2 (de) 1989-06-22
FR2519072B1 (fr) 1986-05-30

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