EP0370899B1 - Schaufelplatte einer Turbine - Google Patents

Schaufelplatte einer Turbine Download PDF

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Publication number
EP0370899B1
EP0370899B1 EP89403217A EP89403217A EP0370899B1 EP 0370899 B1 EP0370899 B1 EP 0370899B1 EP 89403217 A EP89403217 A EP 89403217A EP 89403217 A EP89403217 A EP 89403217A EP 0370899 B1 EP0370899 B1 EP 0370899B1
Authority
EP
European Patent Office
Prior art keywords
disc
platform
foot
plate
bladed 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 - Lifetime
Application number
EP89403217A
Other languages
English (en)
French (fr)
Other versions
EP0370899A1 (de
Inventor
François Marie Paul Marlin
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 EP0370899A1 publication Critical patent/EP0370899A1/de
Application granted granted Critical
Publication of EP0370899B1 publication Critical patent/EP0370899B1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations

Definitions

  • the present invention relates to a finned disc equipped with blades and separate platforms, intended in particular for a turbojet fan or for an aircraft engine compression stage.
  • GB-A- 2 171 151 thus describes a rotor comprising quine blades comprising a blade and a foot, separate inter-blade platforms being mounted by a bulbous foot in an intermediate cell housed on the rim of the disc between two cells carrying the blade roots. This method of fixing imposing additional cells on the blade support disc does not however give complete satisfaction for all applications.
  • GB-A-2006883 also describes a rotor comprising, between the blades, separate platforms, each platform comprising a plate delimiting the internal wall of the gas circulation stream and each axial end of which has a fixing hook connected to the disc .
  • the object of the invention described according to the terms of claim 1 is therefore to produce separate inter-blade platforms for turbomachine rotors, associated with improved means of attachment to a disc ensuring retention both in the in the radial direction and in the axial direction while taking into account the weight reduction requirements, the benefit of which is obvious for rotating parts and which is also an important criterion in the aeronautical applications targeted by the invention.
  • a finned turbomachine rotor disc of the type envisaged above, responding to these problems, is characterized in that that each foot for fixing the platform to the disc, cooperates with a cylindrical seat formed on the rim of said disc, at least one of said platform feet being associated with a rider having a C-shaped section and joining said foot with a tooth-shaped element of the disk, a flange of an element adjacent to the rotor and fixed to the disk being in abutment on said jumper so as to ensure axial locking.
  • FIGS. 1 to 4b relate to a turbojet fan and in particular in the case where the mobile rotor stage comprises large-rope blades associated with separate inter-blade platforms.
  • a fan disc 1 has axially oriented grooves, regularly distributed on the rim, at the periphery of the disc and forming cells 2 in which the feet are held of complementary shape to the fan blades 3.
  • Said rim of the disc 1 is extended on its front face, front and rear being defined with respect to the normal direction of gas flow in the turbomachine, by elements forming teeth 4, spaced from the front face 5 of the disc 1.
  • an annular ring 6 for axially locking the blades 3.
  • the front part of the rim of the disc 1 has a cylindrical bearing surface 7. On the rear part of said rim, a cylindrical bearing surface 8 surmounted by is also provided. an annular spoiler 9, thus creating an annular groove 10.
  • the disc 1 is also equipped with platforms 11 separate from the blades 3.
  • said platforms 11 are metallic and are, for example in the case described of an application to a turbojet fan, of a light metal such than titanium or one of its alloys.
  • Each platform 11, arranged between two consecutive blades 3 consists of an upper plate 12 which delimits the internal wall of the gas circulation stream, on the one hand peripherally between the two blades 3 and on the other hand longitudinally where the front edge 13 of the plate 12 is connected with the rear edge 14 of a support 15 of the inlet cone of the blower and the rear edge 16 comprises, for example, a connection groove at the front external edge 17 of a flange intermediate 18 fixed on the rear face 19 of the disc 1, for example by screw 20 at a fixing flange 21.
  • Said plate 12 is supported by legs, on each side, respectively 22 at the front and 23 at the rear, which are terminated by flanges forming fixing feet, respectively 24 at the front and 25 at the rear.
  • a reinforcing rib 26 is disposed under the internal face of the plate 12, in its middle, oriented in the axial direction, between the two legs 22 and 23.
  • Said foot 25 cooperates with said annular groove 10 of the disc 1 and rests on the bearing cylindrical 8 while the foot 24, at the front, rests on the cylindrical surface 7 of the disc 1.
  • a jumper-shaped element 27, arranged vertically so as to have in section a general shape of C keeps said front foot in place 24, the upper branch 28 of the rider cooperating with the upper surface of the foot 24 and the lower branch 29 cooperating with the internal faces of the disc tooth 4 and of the rod 6.
  • a flange 30 of the support 15 of the inlet cone, in support on the jumpers 27, ensures the axial locking of the assembly.
  • Each rider 27 and the disc tooth 4 further comprising respectively a corresponding bore in which is placed a pin 31 for positioning.
  • the method of mounting the platforms 11 which have just been described is as follows.
  • the rear foot 25 of the platform is introduced into the groove 10 of the disc 1 and the front foot 24 is supported on the front cylindrical surface 7 of the disc 1 then the rider 27 is positioned by placing the pin 31 on the tooth 4 disc.
  • the support 15 of the inlet cone is put in place, the flange 30 of its rear part coming to bear on the jumper 27 and finally, a fixing flange 32 of said support 15 is fixed by bolts at 33 on a flange 34 integral with the front of the disc 1.
  • each platform 111 comprises two box-shaped elements, respectively 111a and 111b, having a generally triangular or trapezoidal cross-section and joined along one side, thus constituting a central rib 126.
  • box elements 111a and 111b can be obtained by winding or by stripping of fabrics of composite material and after assembly, they are joined together by a winding or stripping of fabrics also of composite material, creating an outer skin 111c and also constituting an upper plate 112.
  • the platform 111 also comprises on each edge, a reinforcement element, respectively 35 at the front and 36 at the rear and these reinforcements also form the feet of platform mounting, 124 front and 125 rear respectively.
  • FIG. 4b shows the detail of embodiment of the reinforcement 35.
  • the peripheral lateral edges of the platform 111 each receive a seal, respectively 37 and 38 which provide the seal and the connection between the platform 111 and the blade 3 adjacent, on each side.
  • the other elements of the embodiment described with reference to FIGS. 1 and 2 are kept identical, in particular the fixing of the rear foot 125 engaging in the annular groove 10 of the disc 1 and at the front, the fixing of the front foot 124 by means of a jumper 27, axially blocked by the flange 30 of the support 15 of the fan inlet cone.
  • the assembly method previously described with reference to FIGS. 1 and 2 is also kept identical in the variant embodiment according to FIG. 3.
  • the means for fixing the platform can be provided at the rear identical to those which have been described for the front, namely by using jumpers such as 27.

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)

Claims (6)

1. Beschaufelte Turbomaschinen-Rotorscheibe, die zusammengesetzt ist aus einer lediglich aus einem Schaufelblatt und einem Befestigungsfuß bestehenden Schaufeln (3) ausgestatteten Scheibe (1) und aus separaten Plattformen, wobei jede Plattform (11; 111) eine die Innenwandung der Gaszirkulationsströmung begrenzende Platte (12; 112) besitzt und mit jedem ihrer axialen Endbereiche mit einem Element verbunden ist, das einen Fuß (24, 25; 124, 125) zur Befestigung an der Scheibe (1) bildet, dadurch gekennzeichnet, daß jeder Fuß (24, 25; 124, 125) mit jeweils einer an dem Kranz der Scheibe angebrachten zylindrischen Tragfläche (7, 8) zusammenwirkt, wobei wenigtens einer der Füße (24; 124) der Plattform (11; 111) ein Reiter (27) mit C-förmigen Querschnitt zugeordnet ist, der diesen Fuß (24; 124) fest mit einem zahnförmigen Element der Scheibe (1) verbindet, und wobei sich ein Flansch (30) eines benachbarten und an der Scheibe (1) fixierten Elements des Rotors gegen den genannten Reiter (27) abstützt und dadurch dessen axiale Verriegelung gewährleistet.
2. Beschaufelte Turbomaschinen-Rotorscheibe nach Anspruch 1, bei der dem Fuß (24, 25; 124, 125) der Plattform (11, 111) an der Vorderseite und an der Rückseite einer der genannten Reiter (27) zugeordnet ist.
3. Beschaufelte Turbomaschinen-Rotorscheibe nach Anspruch 1, bei der der an der Vorderseite der Scheibe (1) vorgesehene Reiter (27) auf der Oberseite mit einem Fuß (24, 124) einer Plattform (11, 111) und auf der Unterseite mit einem Zahn (4) der Scheibe (1) und einem zwischen diesem Zahn (4) und der Stirnfläche (5) der Scheibe (1) angeordneten Blockierring (6) verbunden ist, und bei der an der Rückseite der Scheibe (1) der Fuß (25; 125) der Plattform (11, 111) in einer Ringnut (10) angeordnet ist, die an dem hinteren Tell des Kranzes der Scheibe (1) eine Verhakung bildet.
4. Beschaufelte Turbomaschinen-Rotorscheibe nach einem der Ansprüche 1 bis 3, bei der die Stirnfläche des Kranzes der Scheibe (1) und der zugeordnete Reiter (27) jeweils mit einer Bohrung zur Aufnahme eines Positionierungsstiftes (31) ausgestattet sind.
5. Beschaufelte Turbomaschinen-Rotorscheibe nach einem der Ansprüche 1 bis 4, bei der die Plattformen (11) aus Metall bestehen und die genannte Platte (12) jeder Plattform mit jedem Fuß (24, 25) über einen Verbindungsschenkel (22, 23) verbunden ist, wobei eine mit der Innenseite der Platte (12) Pest verbundene Verstärkungsrippe (26) vorgesehen ist, die von dem einen zu dem anderen Verbindungsschenkel (22, 23) verläuft, und wobei jeder axiale Rand (13, 16) der Platte (12) der Plattform (11) mit dem angrenzenden Rand (14, 17) des benachbarten Rotorelements (15, 18) so zusammenwirkt, daß sie die Dichtigkeit und die Kontinuität der Innenwand des Strömungskanals gewährleisten.
6. Beschaufelte Turbomaschinen-Rotorscheibe nach einem der Ansprüche 1 bis 4, bei der die Plattformen (111) aus einem Verbundwerkstoff bestehen und jeweils aus zwei Elementen (111a, 111b) mit dreieckförmigem Querschnitt zusammengesetzt sind, die verklebt und durch eine die Platte (112) der Plattform bildende Außenhaut (111c) miteinander fest verbunden sind, wobei die Befestigungsfüße (124, 125) an jedem axialen Ende aus einer Verstärkung (35, 36) bestehen, und wobei an jedem peripheren Rand der Platte (112) der Plattform (111) eine Dichtung (37, 38) vorgesehen ist, die die Verbindung zwischen Plattformen (111) und Schaufelblättern (3) gewährleistet.
EP89403217A 1988-11-23 1989-11-22 Schaufelplatte einer Turbine Expired - Lifetime EP0370899B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8815234A FR2639402B1 (fr) 1988-11-23 1988-11-23 Disque ailete de rotor de turbomachine
FR8815234 1988-11-23

Publications (2)

Publication Number Publication Date
EP0370899A1 EP0370899A1 (de) 1990-05-30
EP0370899B1 true EP0370899B1 (de) 1992-01-02

Family

ID=9372135

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89403217A Expired - Lifetime EP0370899B1 (de) 1988-11-23 1989-11-22 Schaufelplatte einer Turbine

Country Status (4)

Country Link
US (1) US5049035A (de)
EP (1) EP0370899B1 (de)
DE (1) DE68900646D1 (de)
FR (1) FR2639402B1 (de)

Families Citing this family (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2669686B1 (fr) * 1990-11-28 1994-09-02 Snecma Rotor de soufflante avec aubes sans plates-formes et sabots reconstituant le profil de veine.
US5151013A (en) * 1990-12-27 1992-09-29 United Technologies Corporation Blade lock for a rotor disk and rotor blade assembly
FR2679296B1 (fr) * 1991-07-17 1993-10-15 Snecma Plate-forme separee inter-aube pour disque ailete de rotor de turbomachine.
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
GB9208409D0 (en) * 1992-04-16 1992-06-03 Rolls Royce Plc Rotors for gas turbine engines
GB9209895D0 (en) * 1992-05-07 1992-06-24 Rolls Royce Plc Rotors for gas turbine engines
US5232346A (en) * 1992-08-11 1993-08-03 General Electric Company Rotor assembly and platform spacer therefor
US5281096A (en) * 1992-09-10 1994-01-25 General Electric Company Fan assembly having lightweight platforms
FR2706528B1 (fr) * 1993-06-10 1995-09-01 Snecma Plate-forme séparée inter-aube de disque ailette de rotor de turbomachine.
US6217283B1 (en) * 1999-04-20 2001-04-17 General Electric Company Composite fan platform
US6435820B1 (en) * 1999-08-25 2002-08-20 General Electric Company Shroud assembly having C-clip retainer
US6447250B1 (en) * 2000-11-27 2002-09-10 General Electric Company Non-integral fan platform
US6520742B1 (en) * 2000-11-27 2003-02-18 General Electric Company Circular arc multi-bore fan disk
GB0614640D0 (en) * 2006-07-22 2006-08-30 Rolls Royce Plc An annulus filler seal
US8616849B2 (en) * 2009-02-18 2013-12-31 Pratt & Whitney Canada Corp. Fan blade platform
US8568102B2 (en) * 2009-02-18 2013-10-29 Pratt & Whitney Canada Corp. Fan blade anti-fretting insert
FR2960589B1 (fr) * 2010-05-28 2014-05-02 Snecma Roue a aubes pour une turbomachine, telle qu'un turboreacteur ou un turbopropulseur d'avion
FR2963383B1 (fr) * 2010-07-27 2016-09-09 Snecma Aube de turbomachine, rotor, turbine basse pression et turbomachine equipes d'une telle aube
FR2965843B1 (fr) * 2010-10-06 2012-11-09 Snecma Rotor pour turbomachine
FR2973434A1 (fr) * 2011-03-30 2012-10-05 Snecma Distributeur de turbine en cmc adapte au support d'un carter interne de turbine metallique par un contact radial
FR2974864B1 (fr) * 2011-05-04 2016-05-27 Snecma Rotor de turbomachine avec moyen de retenue axiale des aubes
FR2974863B1 (fr) * 2011-05-06 2015-10-23 Snecma Disque de soufflante de turbomachine
US8777576B2 (en) 2011-08-22 2014-07-15 General Electric Company Metallic fan blade platform
FR2982635B1 (fr) 2011-11-15 2013-11-15 Snecma Roue a aubes pour une turbomachine
US9845699B2 (en) * 2013-03-15 2017-12-19 Gkn Aerospace Services Structures Corp. Fan spacer having unitary over molded feature
US20160053636A1 (en) * 2013-03-15 2016-02-25 United Technologies Corporation Injection Molded Composite Fan Platform
FR3010442B1 (fr) * 2013-09-09 2015-10-09 Snecma Disque aubage monobloc a contraintes reduites en pied d'aube, de preference pour soufflante de turbomachine d'aeronef
FR3022944B1 (fr) 2014-06-26 2020-02-14 Safran Aircraft Engines Ensemble rotatif pour turbomachine
US10024234B2 (en) * 2014-09-08 2018-07-17 Rolls-Royce Deutschland Ltd & Co Kg Panels of a fan of a gas turbine
FR3035678B1 (fr) * 2015-04-29 2017-05-12 Snecma Aube munie de plateformes possedant une jambe de retenue
FR3038653B1 (fr) * 2015-07-08 2017-08-04 Snecma Assemblage d'une plateforme rapportee d'aube de soufflante sur un disque de soufflante
US9976426B2 (en) * 2015-07-21 2018-05-22 United Technologies Corporation Fan platform with stiffening feature
US10215046B2 (en) * 2015-11-23 2019-02-26 United Technologies Corporation Airfoil platform having dual pin apertures and a vertical stiffener
US10584592B2 (en) * 2015-11-23 2020-03-10 United Technologies Corporation Platform for an airfoil having bowed sidewalls
FR3073907B1 (fr) * 2017-11-17 2020-12-11 Safran Aircraft Engines Organe de retention pour plateforme de turbomachine
US12012857B2 (en) * 2022-10-14 2024-06-18 Rtx Corporation Platform for an airfoil of a gas turbine engine
US12410719B2 (en) 2023-02-20 2025-09-09 General Electric Company Turbine engine with composite airfoils

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US2873088A (en) * 1953-05-21 1959-02-10 Gen Electric Lightweight rotor construction
BE540433A (de) * 1954-08-12
NL222612A (de) * 1956-11-30
US3294364A (en) * 1962-01-02 1966-12-27 Gen Electric Rotor assembly
GB1093568A (en) * 1965-11-23 1967-12-06 Rolls Royce Improvements in or relating to bladed rotors such as compressor rotors
GB1232506A (de) * 1969-10-28 1971-05-19
GB1318654A (en) * 1970-12-05 1973-05-31 Secr Defence Bladed rotors
US3888601A (en) * 1974-05-23 1975-06-10 Gen Electric Turbomachine with balancing means
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
GB2006883B (en) * 1977-10-27 1982-02-24 Rolls Royce Fan or compressor stage for a gas turbine engine
US4171930A (en) * 1977-12-28 1979-10-23 General Electric Company U-clip for boltless blade retainer
GB2171151B (en) * 1985-02-20 1988-05-18 Rolls Royce Rotors for gas turbine engines

Also Published As

Publication number Publication date
FR2639402B1 (fr) 1990-12-28
EP0370899A1 (de) 1990-05-30
US5049035A (en) 1991-09-17
DE68900646D1 (de) 1992-02-13
FR2639402A1 (fr) 1990-05-25

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