EP0084491B1 - Verrouillage axial d'aubes de turbines et de compresseurs - Google Patents

Verrouillage axial d'aubes de turbines et de compresseurs Download PDF

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Publication number
EP0084491B1
EP0084491B1 EP83400080A EP83400080A EP0084491B1 EP 0084491 B1 EP0084491 B1 EP 0084491B1 EP 83400080 A EP83400080 A EP 83400080A EP 83400080 A EP83400080 A EP 83400080A EP 0084491 B1 EP0084491 B1 EP 0084491B1
Authority
EP
European Patent Office
Prior art keywords
locking
locking means
notch
blade
blade root
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
EP83400080A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0084491A1 (fr
Inventor
André A. M. L. Camboulives
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
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 filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0084491A1 publication Critical patent/EP0084491A1/fr
Application granted granted Critical
Publication of EP0084491B1 publication Critical patent/EP0084491B1/fr
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
    • F01D5/326—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

Definitions

  • the invention relates to a turbomachine rotor wheel comprising vanes locked radially by their foot in axial grooves provided in the rim of the rotor disc, and axially by first and second locking means cooperating with the blade feet and the rotor disc.
  • French patent 1 037 572 describes a relatively simple device, in which the blade root is extended upstream by a heel in the sole of which is machined, parallel to the face of the disc, an asymmetrical triangular groove.
  • the rotor disc has an axial flange on its upstream face.
  • the upper lateral surface of the strap has an asymmetrical triangular groove, opposite to that provided in the heel.
  • This device uses heel vanes and a flange rotor disc, costly elements both from the point of view of machining and weight.
  • the locking element itself expensive, must be considered as a consumable part, because, to remove a blade, it is mandatory to unfold at least one of the folded parts of the assembly.
  • the elongations outside the elastic range due to the successive folding and unfolding of at least one part make it dangerous for a new machining to use the locking parts described in French patent 1 037 572.
  • the invention proposes to make from blades without heel and a conventional rotor disc, that is to say having no complicated appendix other than that necessary for the axial maintenance of the blades, means of locking using simple machining surfaces, and less costly in spare parts for maintenance.
  • each first axial locking means comprises a conical bearing provided on the edge of the rim of the rotor disc, the largest radius of the bearing being at least equal to the radius of the circumference passing through the bottom of the grooves.
  • axial blade retention a notch provided in the lower part and at one end of the blade root located on the side of the conical seat and overhanging at least part of it, the axis of the notch being parallel to the plane of the disc, and locking means comprising a locking piece shaped so as to cooperate, on the one hand, with the notch of the blade root and, on the other hand, with the conical bearing, said locking piece being held by an immobilizing element.
  • the second axial locking means is advantageously identical to the first.
  • a disc 1 of a turbine rotor or of a compressor comprises (fig. 1 in a known manner, in its rim 2, axial retaining grooves 3, in dovetail.
  • the blade 4 has a foot 5 of shape substantially complementary to that of the reinforcement 3.
  • a conical surface 6 is machined on the edges of the rim 2 making, for example, with respect to the plane of the rotor disc an angle of the order of 40 to 45 °
  • the largest radius 61 of the bearing surface is at least equal to the radius 62 of the circumference passing through the bottoms of the axial grooves for retaining the blades
  • the upstream and downstream ends of the blade roots are released from the groove 3 and at least partially overhang the conical bearing.
  • the lower part of the blade root 5 (fig. 2) carries, at at least one of its ends, a notch 7, 8 with an axis parallel to the plane of the rotor disk at the periphery of which it is fixed.
  • This notch has a cross section in the form of an isosceles right triangle, one of the sides of the right angle of which is parallel to a generatrix of the conical bearing 6.
  • a locking piece 9 a rectangular parallelepiped, is inserted between the bearing surface 6 and the corresponding notch 7, 8 and is held longitudinally by an immobilizing element constituted by tongues 10, 11 which are folded against the blade root .
  • the tongues are formed by the ends of a blade 12 of length greater than that of the locking piece, held in a longitudinal slot of the locking piece 9.
  • the blade has a width greater than the depth of the slot, and, therefore, the blade portion projecting longitudinally, is received in a corresponding slot 13 provided in the side of the notch parallel to the bearing 6.
  • These blades have a double function: to prevent longitudinal movements of the locking part and to hold this part in place against the blade and the blade root when it is no longer subjected to centrifugal force.
  • a recess 14 has been provided between the edge of the conical surface 6 and the radial faces 15 and 16 of the rim, in order to prevent contact corrosion from making an imprint on the rim of the disk.
  • the blade root 5 is slid axially in the groove 3, leaving the foot portion carrying the notch 7 or 8 protruding widely from one of the faces of the disc and the bearing surface.
  • the locking piece 9 is introduced into the notch so that the blade 12 enters the slot 13.
  • the blade root is then pushed into the groove until the locking piece presses against the bearing surface 6.
  • a second locking piece provided with its blade 12 is introduced into the other notch and the assembly is slid against the bearing. Finally, the assembly is immobilized in place in the notch, by folding the ends against the blade root.
  • the device provided with two removable locking parts allows the blade to be put in place or dismantled from one side or the other of the disc.
  • the locking piece 9 can be reused several times. Only the blade 12 must be changed for a new assembly. The only part to be discarded is a piece of low value, since it is a piece of flat rectangular sheet metal.
  • one of the locking pieces is placed in the notch of the blade root and is held by the blade 12.
  • the blade root is then pushed into the groove 3.
  • the blade must then be introduced from a defined face of the rotor disc.
  • the locking piece can be fixed permanently and of origin in the notch or can be constituted by a projecting part provided during the machining of the blade root.
  • the locking means no longer have a single removable locking piece.

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)
EP83400080A 1982-01-14 1983-01-13 Verrouillage axial d'aubes de turbines et de compresseurs Expired EP0084491B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8200496 1982-01-14
FR8200496A FR2519692B1 (fr) 1982-01-14 1982-01-14 Dispositif de verrouillage axial d'aubes de turbines et de compresseurs

Publications (2)

Publication Number Publication Date
EP0084491A1 EP0084491A1 (fr) 1983-07-27
EP0084491B1 true EP0084491B1 (fr) 1986-01-08

Family

ID=9269966

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83400080A Expired EP0084491B1 (fr) 1982-01-14 1983-01-13 Verrouillage axial d'aubes de turbines et de compresseurs

Country Status (5)

Country Link
US (1) US4466776A (enrdf_load_stackoverflow)
EP (1) EP0084491B1 (enrdf_load_stackoverflow)
JP (1) JPS58124007A (enrdf_load_stackoverflow)
DE (1) DE3361730D1 (enrdf_load_stackoverflow)
FR (1) FR2519692B1 (enrdf_load_stackoverflow)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9127563B2 (en) 2011-04-05 2015-09-08 General Electric Company Locking device arrangement for a rotating bladed stage
FR3139596A1 (fr) * 2022-09-12 2024-03-15 Safran Aircraft Engines Ensemble de turbomachine

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4711007A (en) * 1986-09-29 1987-12-08 Westinghouse Electric Corp. Method and apparatus for installing free standing turbine blades
US4915587A (en) * 1988-10-24 1990-04-10 Westinghouse Electric Corp. Apparatus for locking side entry blades into a rotor
US5310317A (en) * 1992-08-11 1994-05-10 General Electric Company Quadra-tang dovetail blade
GB9412963D0 (en) * 1994-06-28 1994-09-28 Rolls Royce Plc Gas turbine engine fan blade assembly
US5720596A (en) * 1997-01-03 1998-02-24 Westinghouse Electric Corporation Apparatus and method for locking blades into a rotor
US8496439B2 (en) * 2010-03-17 2013-07-30 Siemens Energy, Inc. Turbomachine blade locking structure including shape memory alloy
FR2963383B1 (fr) * 2010-07-27 2016-09-09 Snecma Aube de turbomachine, rotor, turbine basse pression et turbomachine equipes d'une telle aube
DE102011077501A1 (de) * 2011-06-14 2012-12-20 Rolls-Royce Deutschland Ltd & Co Kg Rotorvorrichtung für ein Strahltriebwerk mit einem Scheibenrad und mehreren Laufschaufeln
US10703452B2 (en) 2016-10-17 2020-07-07 General Electric Company Apparatus and system for propeller blade aft retention
US10689073B2 (en) 2016-10-17 2020-06-23 General Electric Company Apparatus and system for marine propeller blade dovetail stress reduction
US11052982B2 (en) 2016-10-17 2021-07-06 General Electric Company Apparatus for dovetail chord relief for marine propeller
US10633067B2 (en) 2016-10-17 2020-04-28 General Electric Company Method and system for improving flow characteristics in marine propellers
US10486785B2 (en) 2016-10-17 2019-11-26 General Electric Company Propeller assembly and method of assembling
US9682756B1 (en) 2016-10-17 2017-06-20 General Electric Company System for composite marine propellers
US10738626B2 (en) 2017-10-24 2020-08-11 General Electric Company Connection assemblies between turbine rotor blades and rotor wheels
US11555407B2 (en) 2020-05-19 2023-01-17 General Electric Company Turbomachine rotor assembly

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE17350C (de) * F. X. POZNANSKI in Paris Dintenbehälter für Füllfedern
FR375059A (fr) * 1906-05-02 1907-06-29 Piguet Et Cie Ets Perfectionnements à la construction des roues de turbines
NL70887C (enrdf_load_stackoverflow) * 1944-12-22 1900-01-01
CH250728A (de) * 1945-12-14 1947-09-15 Sulzer Ag Trommelläufer für Turbomaschinen.
BE501031A (enrdf_load_stackoverflow) * 1950-02-03
US2667327A (en) * 1950-06-14 1954-01-26 Westinghouse Electric Corp Rotor construction
US2807436A (en) * 1952-03-25 1957-09-24 Gen Motors Corp Turbine wheel and bucket assembly
US2873088A (en) * 1953-05-21 1959-02-10 Gen Electric Lightweight rotor construction
NL99070C (enrdf_load_stackoverflow) * 1953-07-28
US3023998A (en) * 1959-03-13 1962-03-06 Jr Walter H Sanderson Rotor blade retaining device
GB894704A (en) * 1960-03-30 1962-04-26 Gen Electric Improvements in reusable locking means for turbine or compressor rotor assemblies
CH410016A (de) * 1961-10-18 1966-03-31 Daimler Benz Ag Verfahren zum Sichern der Schaufeln von Strömungsmaschinen
US3297302A (en) * 1965-10-24 1967-01-10 Gen Motors Corp Blade pin retention
US3341174A (en) * 1967-02-27 1967-09-12 United Aircraft Corp Blade lock
US3508844A (en) * 1968-07-25 1970-04-28 United Aircraft Corp Blade lock
US4349318A (en) * 1980-01-04 1982-09-14 Avco Corporation Boltless blade retainer for a turbine wheel
US4389161A (en) * 1980-12-19 1983-06-21 United Technologies Corporation Locking of rotor blades on a rotor disk

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9127563B2 (en) 2011-04-05 2015-09-08 General Electric Company Locking device arrangement for a rotating bladed stage
FR3139596A1 (fr) * 2022-09-12 2024-03-15 Safran Aircraft Engines Ensemble de turbomachine

Also Published As

Publication number Publication date
FR2519692B1 (fr) 1986-08-22
DE3361730D1 (en) 1986-02-20
US4466776A (en) 1984-08-21
FR2519692A1 (fr) 1983-07-18
JPS58124007A (ja) 1983-07-23
JPH0152561B2 (enrdf_load_stackoverflow) 1989-11-09
EP0084491A1 (fr) 1983-07-27

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