EP0429353A1 - Axiale Turbomaschine - Google Patents

Axiale Turbomaschine Download PDF

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Publication number
EP0429353A1
EP0429353A1 EP90403275A EP90403275A EP0429353A1 EP 0429353 A1 EP0429353 A1 EP 0429353A1 EP 90403275 A EP90403275 A EP 90403275A EP 90403275 A EP90403275 A EP 90403275A EP 0429353 A1 EP0429353 A1 EP 0429353A1
Authority
EP
European Patent Office
Prior art keywords
disc
blade
pins
rotor
platform
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
EP90403275A
Other languages
English (en)
French (fr)
Other versions
EP0429353B1 (de
Inventor
Pierre Antoine Glowacki
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 EP0429353A1 publication Critical patent/EP0429353A1/de
Application granted granted Critical
Publication of EP0429353B1 publication Critical patent/EP0429353B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins

Definitions

  • the present invention relates to a turbomachine rotor with axial flow of the type comprising a disc having a plurality of ribs extending radially outward from its periphery, so as to delimit a plurality of annular grooves between the front annular rib located on the upstream side of the flow and the rear annular rib located on the downstream side flow, a plurality of blades, regularly arranged at the periphery of the disc and extending radially outward, each blade having a foot notched at its end adjacent to the disc so as to define heels, each being received by a corresponding groove and each blade being fixed to the disc by fixing means, and a plurality of added platforms fixed to the disc so as to be, each, arranged between two adjacent blades to delimit, on the side of the disc, the vein of the fluid circulating from upstream to downstream through said plurality of blades during operation of said rotor.
  • US Pat. No. 3,694,104 describes a blade made of composite material, the foot of which is notched and has heels each having a bore delimited by a metal sleeve intended to cooperate with a spindle.
  • the foot of dawn is fixed on the disc ribs by two axially offset pins, one located on the upstream side of the blade and the other on the downstream side respectively in the plane of the leading edge and in the plane of the trailing edge.
  • This arrangement does not allow the spindles to take up all the forces applied to the blades.
  • the added platforms interposed between the blades are requested for the recovery of the tangential components of the forces, and they must be rigid and firmly fixed to the disc by fixing screws, which results in an increase in the weight of the rotor.
  • the object of the present invention is to overcome these drawbacks, and to propose a turbomachine rotor of the type mentioned in which the means for fixing the blade on the disc allow all the forces exerted on the blades to be taken up.
  • the fixing means comprise, for each blade, two substantially parallel pins, equidistant from the periphery of the disc and arranged in corresponding bores passing right through the plurality of annular ribs and the heels of the blade, said pins extending at least between the front annular rib and the rear annular rib and each comprising at one of their ends a spindle head fixed to the disc, and in that each platform is extended at its front and rear ends by plates extending towards the axis of the disc and provided with openings for the passage of the two adjacent pins each retaining a neighboring blade.
  • the parallel and circumferentially offset pins ensure the recovery of forces in all directions.
  • the added platforms are no longer subjected to tangential forces and they can be lighter.
  • the number of parts for fixing the blades and the added platforms is limited compared to the prior art.
  • the bores of the heels of the blade root and of the annular ribs are parallel to the axis of the disc. This facilitates the drilling of the annular ribs.
  • the annular ribs advantageously include notches between two adjacent blade roots.
  • the blades are made of composite material and the bores of each heel are delimited by sockets which are bypassed at their lower part by the fibers of the composite which then leave towards the outer end of the blade.
  • the axial flow turbomachine rotor 1 shown in the drawing, comprises a rotor disc 10, having the shape of a rim, on the circumference of which is fixed, in a regularly distributed manner, a plurality of blades 11 comprising, each , a foot 12 for fixing to the disk 10 and a payroll 13 which extends radially outwards from the periphery of the disk 10.
  • Reported platforms 14, intended to delimit, on the side of the axis of the rotor 1, the vein of the gas flow flowing from upstream to downstream through the blades 11 of the rotor 1 when the latter is in operation, are arranged between the blades 11.
  • the latter comprises a plurality of annular ribs 15 which extend radially outward from its periphery.
  • the blade root 12 has, at its end, radial notches adapted to the annular ribs 15, so as to have heels 16 interposed in correspondence between the annular ribs 15.
  • the number of annular ribs 15 is equal to the number of heels 16 blades 11 increased by one, such that the blade roots 12 are arranged between a front rib 15a located on the upstream side of the flow and a rear rib 15b located on the downstream side.
  • each heel 16 is equal to the distance separating the adjacent annular ribs so as to prevent axial displacement of the blades 11.
  • a space 17 is provided between the rear face 18 of the blade root 12 and the front face 19 of the rear annular rib 15b.
  • Each attached platform 14 has a wall 20 which is inclined relative to the axis of the rotor 1, which extends between the facing faces of two consecutive blades 11a and 11b, and which is extended at its front and rear ends by plates 21 and 22 which extend radially towards the axis of the rotor 1.
  • the front plate 21 is disposed against the front face 23 of the rib annular front 14a and the rear plate 22 has its end portion which accommodates in the space 17 provided between the rear face 18 of the blade root 12 and the front face 19 of the rear annular rib 15b, so as to prevent any axial movement of the platform 14.
  • the wall 20 rests by its longitudinal edges on support fins 20a and 20b provided on the faces of the blade 11 and which extend in the direction of the flow of gas.
  • Each blade 11 is fixed to the disc 10 by two pins 25a and 25b which are introduced by the front face of the rotor 1 into two conduits 26a and 26b parallel and equidistant from the axis of the rotor 1.
  • the conduits 26a and 26b are delimited by aligned bores provided in correspondence in the annular ribs 15 and the heels 16 of the blade root 12.
  • the front plates 21 and rear 22 of each platform also have openings for the passage of the two adjacent pins 25a and 25b which fix , each one of the two neighboring blades 11a and 11b.
  • the pins 25a and 25b for fixing a blade 11 thus hold the blade 11 on the disc 10 and take up the radial and tangential components of the forces exerted on the blade 11.
  • the blade 11 is produced in a composite material, and each heel 16 has two parallel sockets 27a and 27b partially delimiting the conduits 26a and 26b.
  • the fibers of the composite constituting the pay 13 bypass the sockets 27a and 27b at their lower part in the direction of the lower surface towards the upper surface and ensure the continuity of the centrifugal loads.
  • the pins 25a and 25b extend at least between the front rib 15a and the rear rib 15b and they respectively comprise pin heads 32a and 32b which are in abutment against the front face of the front plate 21 of the attached platform 14.
  • the openings of the front plate 21 of the platform 14 through which the pins 25a and 25b pass are replaced by parallel notches 28a and 28h opening onto the end edge 29 of the front plate 21 situated on the side of the axis of the rotor, and this end edge 29 is extended towards the front of the rotor 1 by a flange 30 whose external radial face 31 is intended to cooperate with the edges of the heads 32a and 32b of the pins 25a and 25b, located on the side of the axis of the rotor 1 so as to radially lock the platform 14.
  • the heads 32a and 32b of the two consecutive pins 25a and 25b fixing a platform 14 have a 'trapezoidal shape and each have, on the side of the other pin, a lateral protrusion 33 comprising a notch intended to accommodate the lateral protrusion 33 of the other spindle, so that said protuberances 33 are superimposed on the right of the median zone of the front plate 21 of the platform 14.
  • the two pins 25a and 25b are fixed together and fixed to the platform. form 14 using a fixing screw 34 accommodating in a bore passing through the superimposed lateral protrusions 33 and there the front plate 21 and cooperating with a nut 35 previously fixed on the rear face of the front plate 21.
  • notches 36 are advantageously provided on the annular ribs 15 in the vicinity of the median planes of the platforms 14 between two adjacent blade roots 12.
  • each blade 11 is first placed on the disc 10 so that the bores of the blade roots 12 are aligned with the bores of the annular ribs 15 and the pins 25a and 25b through the front face of the disc 10 in the holes 26a and 26b to immobilize the blade 11.
  • each platform 14 is positioned and fixed by completely introducing the corresponding pins 25a and 25b in the holes 26a and 26b so that the pin heads 32a, 32b cooperate with the flange 30 to radially hold the platform 14.
  • the two pin heads 32a, 32b of the two pins 25a and are then fixed 25b retaining each platform 14, between them and to the front plate 21 of the corresponding platform, using the fixing screw 34.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP90403275A 1989-11-22 1990-11-21 Axiale Turbomaschine Expired - Lifetime EP0429353B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8915301 1989-11-22
FR8915301A FR2654773B1 (fr) 1989-11-22 1989-11-22 Rotor de turbomachine a flux axial.

Publications (2)

Publication Number Publication Date
EP0429353A1 true EP0429353A1 (de) 1991-05-29
EP0429353B1 EP0429353B1 (de) 1993-05-26

Family

ID=9387632

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90403275A Expired - Lifetime EP0429353B1 (de) 1989-11-22 1990-11-21 Axiale Turbomaschine

Country Status (4)

Country Link
US (1) US5145319A (de)
EP (1) EP0429353B1 (de)
DE (1) DE69001745T2 (de)
FR (1) FR2654773B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5244345A (en) * 1991-01-15 1993-09-14 Rolls-Royce Plc Rotor
FR2700362A1 (fr) * 1993-01-14 1994-07-13 Snecma Rotor de turbomachine à attaches d'aubes par broches.
EP2070819A1 (de) 2007-12-14 2009-06-17 Eurocopter Blatt eines Drehflügelflugzeugs, mit einem solchen Blatt ausgestatteter Rotor eines Drehflügelflugzeugs und Herstellungsverfahren dieses Blatts

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5494404A (en) * 1993-12-22 1996-02-27 Alliedsignal Inc. Insertable stator vane assembly
US9470092B2 (en) * 2013-01-02 2016-10-18 General Electric Company System and method for attaching a rotating blade in a turbine
US10557361B1 (en) 2018-10-16 2020-02-11 United Technologies Corporation Platform for an airfoil of a gas turbine engine
US11306601B2 (en) * 2018-10-18 2022-04-19 Raytheon Technologies Corporation Pinned airfoil for gas turbine engines
FR3091722B1 (fr) * 2019-01-11 2020-12-25 Safran Aircraft Engines Rotor, turbine équipée d’un tel rotor et turbomachine équipée d’une telle turbine

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB242977A (en) * 1924-11-14 1926-01-21 Rateau Soc Improvements in or relating to the blades of rotary fans
US2326145A (en) * 1941-03-18 1943-08-10 Westinghouse Electric & Mfg Co Turbine blade fastening
FR958441A (de) * 1950-03-10
US2514408A (en) * 1948-04-19 1950-07-11 Westinghouse Electric Corp Gas turbine apparatus
US2928653A (en) * 1955-12-22 1960-03-15 Gen Electric Variable angle blade for fluid flow machines
FR1234275A (fr) * 1959-05-14 1960-10-17 Westinghouse Electric Corp Appareil utilisant un fluide élastique
FR1457941A (fr) * 1965-12-10 1966-11-04 Lister & Co Ltd R A Rotor pour soufflerie à écoulement axial
GB1331209A (en) * 1969-10-28 1973-09-26 Secr Defence Bladed rotors for fluid flow machines
FR2283308A1 (fr) * 1974-08-28 1976-03-26 Mtu Muenchen Gmbh Roue motrice axiale pour turbo-machines rapides
US4460316A (en) * 1982-12-29 1984-07-17 Westinghouse Electric Corp. Blade group with pinned root

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR955013A (de) * 1946-11-20 1950-01-07
FR989556A (fr) * 1949-06-25 1951-09-11 Cem Comp Electro Mec Perfectionnement aux aubes de turbo-machines
US2999668A (en) * 1958-08-28 1961-09-12 Curtiss Wright Corp Self-balanced rotor blade
US3694104A (en) * 1970-10-07 1972-09-26 Garrett Corp Turbomachinery blade
GB1430596A (en) * 1972-07-06 1976-03-31 Rolls Royce Multi-bladed fans
DE2915286A1 (de) * 1979-04-14 1980-10-23 Motoren Turbinen Union Laufrad fuer axialstroemungs-turbomaschinen
US4621979A (en) * 1979-11-30 1986-11-11 United Technologies Corporation Fan rotor blades of turbofan engines
FR2574752B1 (fr) * 1984-12-19 1987-02-20 Aerospatiale Pale pour rotor d'helicoptere en materiau composite multilongeron a caissons de torsion et son procede de fabrication

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR958441A (de) * 1950-03-10
GB242977A (en) * 1924-11-14 1926-01-21 Rateau Soc Improvements in or relating to the blades of rotary fans
US2326145A (en) * 1941-03-18 1943-08-10 Westinghouse Electric & Mfg Co Turbine blade fastening
US2514408A (en) * 1948-04-19 1950-07-11 Westinghouse Electric Corp Gas turbine apparatus
US2928653A (en) * 1955-12-22 1960-03-15 Gen Electric Variable angle blade for fluid flow machines
FR1234275A (fr) * 1959-05-14 1960-10-17 Westinghouse Electric Corp Appareil utilisant un fluide élastique
FR1457941A (fr) * 1965-12-10 1966-11-04 Lister & Co Ltd R A Rotor pour soufflerie à écoulement axial
GB1331209A (en) * 1969-10-28 1973-09-26 Secr Defence Bladed rotors for fluid flow machines
FR2283308A1 (fr) * 1974-08-28 1976-03-26 Mtu Muenchen Gmbh Roue motrice axiale pour turbo-machines rapides
US4460316A (en) * 1982-12-29 1984-07-17 Westinghouse Electric Corp. Blade group with pinned root

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5244345A (en) * 1991-01-15 1993-09-14 Rolls-Royce Plc Rotor
FR2700362A1 (fr) * 1993-01-14 1994-07-13 Snecma Rotor de turbomachine à attaches d'aubes par broches.
EP0607082A1 (de) * 1993-01-14 1994-07-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbomaschinenrotor mit Schaufelnbefestigung durch Stifte
US5409353A (en) * 1993-01-14 1995-04-25 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbomachine rotor with blades secured by pins
EP2070819A1 (de) 2007-12-14 2009-06-17 Eurocopter Blatt eines Drehflügelflugzeugs, mit einem solchen Blatt ausgestatteter Rotor eines Drehflügelflugzeugs und Herstellungsverfahren dieses Blatts
FR2925015A1 (fr) * 2007-12-14 2009-06-19 Eurocopter France Pale de giravion, rotor de giravion muni de ladite pale, et procede de fabrication de cette pale
US8061994B2 (en) 2007-12-14 2011-11-22 Eurocopter Rotorcraft blade, a rotorcraft rotor provided with said blade, and a method of fabricating said blade

Also Published As

Publication number Publication date
US5145319A (en) 1992-09-08
DE69001745T2 (de) 1993-10-07
DE69001745D1 (de) 1993-07-01
FR2654773A1 (fr) 1991-05-24
FR2654773B1 (fr) 1992-02-14
EP0429353B1 (de) 1993-05-26

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