EP0524876A1 - Roues à aubes de turbomachines - Google Patents

Roues à aubes de turbomachines Download PDF

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Publication number
EP0524876A1
EP0524876A1 EP92402110A EP92402110A EP0524876A1 EP 0524876 A1 EP0524876 A1 EP 0524876A1 EP 92402110 A EP92402110 A EP 92402110A EP 92402110 A EP92402110 A EP 92402110A EP 0524876 A1 EP0524876 A1 EP 0524876A1
Authority
EP
European Patent Office
Prior art keywords
disc
blades
crown
ferrule
vanes
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.)
Withdrawn
Application number
EP92402110A
Other languages
German (de)
English (en)
French (fr)
Inventor
Maurice Jean Cabaret
Christophe Champenois
Christophe Gilbert Jacques Gourio
Gérard Ernest André Jourdain
Gilles Albert Le Rumeur
Didier Merville
Jean-Pierre Poitevin
Bruno Tournaire
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 EP0524876A1 publication Critical patent/EP0524876A1/fr
Withdrawn legal-status Critical Current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
    • 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

Definitions

  • the invention relates to improvements to the impellers of turbomachinery and in particular to the wheels of turbines and compressors used in aeronautics.
  • turbomachine wheel of the type comprising a disc or drum, a plurality of profiled blades extending radially outward from the periphery of said disc and the feet of which are locked on said disc, and a crown. coaxial with said disc and independent of said vanes, said crown forming between said vanes platforms delimiting the internal wall of the aerodynamic gas circulation stream.
  • the blades are mounted on discs having diameters which can be relatively small. These blades are also produced from composite or other materials which resist high temperatures and high centrifugal forces. For reasons of manufacturing cost, these composite material blades are produced without platforms and have an aerodynamic profile from their foot to their head.
  • the high volume of gases circulating in the aerodynamic annular vein means that this annular vein has to be given an internal diameter greater than the diameter of the discs carrying the blades, so as to avoid excessive turbulence in the vicinity of the internal wall delimiting the aerodynamic vein. This is why we create around the disc, a crown with platforms between the blades.
  • This independent crown of the blades also allows the disc to be moved away from high temperature zones.
  • the crown is produced by added elements, distinct from the blades and fixed to the disc, the number of these added elements being equal to the number of blades.
  • US Patent 2,834,573 shows a rotor in which a ring fills the peripheral space existing between the blades.
  • This ring consists of elementary segments, shown in Figure 6, which leaves between them a housing corresponding to the profile of the blade.
  • French patent 1,501,492 relates to a compressor wheel, equipped with blades without platform, and comprising an annular ring having multiple recesses angularly spaced to accommodate the respective heels of the blades.
  • the crown also includes multiple segments. Each segment is made integral with the wheel on which it is mounted by a fastener fixed in a peripheral groove.
  • French patent 2,073,854 describes a rotor in which the intermediate pieces play the role of platforms with respect to the flow, the primary purpose of these intermediate pieces being a mechanical role of shock absorber. These intermediate pieces are maintained, between the blade roots and the edges of the cells, by corner systems.
  • French patent 2,608,674 relates to a turbine wheel which comprises vanes having a bulbous-shaped foot, the lateral planar sides of which have a small convergence angle and are held in the cells by wedge-shaped elements associated with elements distinct forming platforms to form a continuous ring of internal wall of the aerodynamic gas stream.
  • the object of the present invention is to propose a new type of crown which appreciably reduces the number of parts present.
  • said crown consists of an annular ferrule having indentations for the passage of the blades.
  • said crown is made of composite materials.
  • This new structure of the crown makes it possible to lighten the means for fixing the crown to the disc. It can be applied to discs provided with grooves for attachments of so-called "hammer” blades, and to discs on which the blades are pinned.
  • impressions are preferably made by piercing the shell by a specific process. According to a construction variant, they are produced in the form of open slots on an edge of said ferrule.
  • the drawing shows a crown 2 made in one part and made of composite materials and in the form of an annular ferrule capable of being arranged coaxially on a disc 3 of a turbomachine, not shown in the drawing, so as to constitute the internal wall of the aerodynamic circulation stream gases through the turbomachine.
  • This ferrule 2 has a plurality of indentations 4 intended for the passage of the vanes 5, the feet 6 of which are fixed to the periphery 7 of the disc 3.
  • These indentations 4 may be in the form of holes made during the manufacture of the crown. 2, as seen in Figures 1 and 2.
  • the blades 5 have an aerodynamic profile over their entire length.
  • FIG. 1 shows an exploded view of a turbomachine wheel in which the attachment of the blades 5 to the disc 3 is of the "hammer attachment" type.
  • the disc 3 has, in known manner, on its periphery 7, annular grooves 8 forming cells intended to receive the feet 6 of the blades 5, and an introduction window 9 for mounting and dismounting the blades 5.
  • the mounting of the first dawn 5 is done as follows: the ferrule 2 is positioned on the disc 3 by placing an imprint 4 opposite the introduction window 9; the foot 6 of the first blade 5 is introduced from the outside of the ferrule into said introduction window 9 by passing it through the cavity 4 in correspondence and; the assembly constituted by the ferrule 2 and the first blade 5 is subjected to rotation about the axis of the disc 3 by an angle corresponding to the angular spacing of two consecutive indentations 4; the following blades 5 are assembled by introducing a blade root 6 into the introduction window 9 and rotating a step of the crown 2.
  • FIG. 2 shows an exploded view of a turbomachine wheel in which the attachment of the blades 5 to the disc 3 is of the brocaded type.
  • the disc 3 has on its periphery 7 axial cells 10 in which the feet 6 of the blades 5 are introduced.
  • the heads of all the vanes 6 are passed through the interior of the ferrule 2 through the cavities 4, then all the vanes 5 are assembled at the same time. translation of the assembly constituted by the crown 2 and the assembly of all the blades 5, coaxially with the disc 3.
  • FIGS 3 and 4 show an alternative embodiment of the crown 2 of the invention.
  • the ferrule is notched and the imprints 4 is in the form of slots 11 open on an edge 12 of the ferrule 2.
  • the blades 5 are first introduced into the cells of the disc 3, then the ferrule 2 is positioned.
  • the assembly is secured to the disc 3 by a segment 13 disposed downstream of the disc 3 and cooperating with the edge 12 of the ferrule 2 .
  • FIGS. 1 and 2 can be extended to several stages of wheels depending on the taper of the aerodynamic stream.
  • the ferrule 2 can be secured to the disc 3 by screws, not shown in the drawing, cooperating with bores 14 and 15 provided in correspondence on the shell 2 and the disc 3.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP92402110A 1991-07-24 1992-07-22 Roues à aubes de turbomachines Withdrawn EP0524876A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9109368 1991-07-24
FR9109368A FR2679599A1 (fr) 1991-07-24 1991-07-24 Perfectionnement aux roues a aubes de turbomachines.

Publications (1)

Publication Number Publication Date
EP0524876A1 true EP0524876A1 (fr) 1993-01-27

Family

ID=9415486

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92402110A Withdrawn EP0524876A1 (fr) 1991-07-24 1992-07-22 Roues à aubes de turbomachines

Country Status (3)

Country Link
US (1) US5263823A (enExample)
EP (1) EP0524876A1 (enExample)
FR (1) FR2679599A1 (enExample)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2075417A1 (fr) 2007-12-27 2009-07-01 Techspace aero Plateforme et aube pour une roue aubagée de turbomachine, roue aubagée et compresseur ou turbomachine comportant une telle roue aubagée
FR2940353A1 (fr) * 2008-12-23 2010-06-25 Snecma Roue mobile de turbomachine a aubes en materiau composite.
FR2940350A1 (fr) * 2008-12-23 2010-06-25 Snecma Roue mobile de turbomachine a aubes en materiau composite munie d'un anneau ressort.
EP3683450A1 (fr) * 2019-01-18 2020-07-22 Safran Aero Boosters S.A. Ensemble rotatif de turbomachine

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GB9405473D0 (en) * 1994-03-19 1994-05-04 Rolls Royce Plc A gas turbine engine fan blade assembly
US5609471A (en) * 1995-12-07 1997-03-11 Allison Advanced Development Company, Inc. Multiproperty rotor disk and method of manufacture
US5597290A (en) * 1996-05-01 1997-01-28 Tuthill Corporation Multi-component fan assembly
FR2772096B1 (fr) 1997-12-09 2000-03-10 Bosch Syst Freinage Frein a tambour combinant le point fixe et la commande du frein de stationnement
US6139277A (en) * 1998-12-22 2000-10-31 Air Concepts, Inc. Motorized fan
US6991428B2 (en) 2003-06-12 2006-01-31 Pratt & Whitney Canada Corp. Fan blade platform feature for improved blade-off performance
DE10358421A1 (de) * 2003-12-13 2005-07-07 Mtu Aero Engines Gmbh Rotor für eine Turbomaschine
IT1394295B1 (it) 2009-05-08 2012-06-06 Nuovo Pignone Spa Girante centrifuga del tipo chiuso per turbomacchine, componente per tale girante, turbomacchina provvista di tale girante e metodo di realizzazione di tale girante
DE102009023840A1 (de) * 2009-06-04 2010-12-09 Mtu Aero Engines Gmbh Rotor einer Strömungsmaschine mit separatem Deckband
DE102009023841A1 (de) * 2009-06-04 2010-12-09 Mtu Aero Engines Gmbh Integraler Rotor einer Strömungsmaschine mit separatem Deckband
IT1397057B1 (it) 2009-11-23 2012-12-28 Nuovo Pignone Spa Girante centrifuga e turbomacchina
IT1397058B1 (it) 2009-11-23 2012-12-28 Nuovo Pignone Spa Stampo per girante centrifuga, inserti per stampo e metodo per costruire una girante centrifuga
DE102010015404B4 (de) * 2010-04-19 2012-02-16 Mtu Aero Engines Gmbh Verfahren zur Reparatur einer Rotoranordnung einer Turbomaschine, Ringelement für eine Rotoranordnung einer Turbomaschine sowie Rotoranordnung für eine Turbomaschine
FR2961847B1 (fr) * 2010-06-25 2012-08-17 Snecma Roue mobile a aubes en materiau composite pour moteur a turbine a gaz a liaison pied d'aube/disque par serrage
US8491267B2 (en) 2010-08-27 2013-07-23 Pratt & Whitney Canada Corp. Retaining ring arrangement for a rotary assembly
ITCO20110064A1 (it) 2011-12-14 2013-06-15 Nuovo Pignone Spa Macchina rotante comprendente un rotore con una girante composita ed un albero metallico
US9376926B2 (en) * 2012-11-15 2016-06-28 United Technologies Corporation Gas turbine engine fan blade lock assembly
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
WO2015108592A2 (en) 2013-11-22 2015-07-23 United Technologies Corporation Multi-material turbine airfoil
ITCO20130067A1 (it) 2013-12-17 2015-06-18 Nuovo Pignone Srl Girante con elementi di protezione e compressore centrifugo
EP2933436A1 (de) * 2014-04-15 2015-10-21 Siemens Aktiengesellschaft Radscheibe mit wenigstens einem Dichtblech
US10280768B2 (en) 2014-11-12 2019-05-07 Rolls-Royce North American Technologies Inc. Turbine blisk including ceramic matrix composite blades and methods of manufacture
US9909430B2 (en) 2014-11-13 2018-03-06 Rolls-Royce North American Technologies Inc. Turbine disk assembly including seperable platforms for blade attachment
US10047763B2 (en) 2015-12-14 2018-08-14 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling
FR3057908B1 (fr) * 2016-10-21 2019-11-22 Safran Aircraft Engines Ensemble rotatif d'une turbomachine muni d'un systeme de maintien axial d'une aube
US10294954B2 (en) 2016-11-09 2019-05-21 Rolls-Royce North American Technologies Inc. Composite blisk
US10563665B2 (en) 2017-01-30 2020-02-18 Rolls-Royce North American Technologies, Inc. Turbomachine stage and method of making same
GB201718600D0 (en) * 2017-11-10 2017-12-27 Rolls Royce Plc Annulus filler
US10738630B2 (en) * 2018-02-19 2020-08-11 General Electric Company Platform apparatus for propulsion rotor
US10934859B2 (en) * 2018-08-24 2021-03-02 Rolls-Royce North American Technologies Inc. Turbine blade comprising ceramic matrix composite materials
CN117178111A (zh) * 2021-03-03 2023-12-05 耳语航空公司 螺旋桨翼尾缘排气区域控制
US11802485B2 (en) 2021-03-03 2023-10-31 Whisper Aero Inc. Propulsor fan array
AU2022231432A1 (en) 2021-03-03 2023-10-12 Whisper Aero Inc. Propulsor wing trailing edge exhaust area control
CN114986078B (zh) * 2022-07-20 2023-05-05 华能国际电力股份有限公司 一种用于修复t型叶根轮盘损伤的装置及装配方法
CN115178962A (zh) * 2022-07-20 2022-10-14 华能国际电力股份有限公司 一种用于修复枞树型叶根轮盘损伤的装置及装配方法
CN115106715B (zh) * 2022-07-20 2023-05-05 华能国际电力股份有限公司 一种用于修复叉型叶根轮盘损伤的装置及装配方法
CN115194402A (zh) * 2022-07-20 2022-10-18 华能国际电力股份有限公司 一种轮盘部件修复方法
CN115213627B (zh) * 2022-07-20 2023-05-05 华能国际电力股份有限公司 一种用于修复菌型叶根轮盘损伤的装置及装配方法
US12012857B2 (en) * 2022-10-14 2024-06-18 Rtx Corporation Platform for an airfoil of a gas turbine engine
US12071861B1 (en) * 2023-09-22 2024-08-27 Rolls-Royce American Technologies Inc. Multi-piece radial turbine rotor

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Publication number Priority date Publication date Assignee Title
FR319370A (fr) * 1902-03-07 1902-11-11 Fullagar Perfectionnements apportés aux turbines à fluide sous pression et aux turbo-pompes
US2918253A (en) * 1956-05-18 1959-12-22 Orenda Engines Ltd Rotor assemblies for turbines
US2948505A (en) * 1956-12-26 1960-08-09 Gen Electric Gas turbine rotor

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US2834573A (en) * 1953-06-23 1958-05-13 Stalker Dev Company Rotor construction for fluid machines
US2988324A (en) * 1957-06-14 1961-06-13 Napier & Son Ltd Rotors for multi-stage axial flow compressors or turbines
GB1093568A (en) * 1965-11-23 1967-12-06 Rolls Royce Improvements in or relating to bladed rotors such as compressor rotors
US3554668A (en) * 1969-05-12 1971-01-12 Gen Motors Corp Turbomachine rotor
GB1276106A (en) * 1969-12-19 1972-06-01 Rolls Royce FLUID FLOW MACHINE, e.g. GAS TURBINE ENGINE COMPRESSOR
FR2608674B1 (fr) * 1986-12-17 1991-04-19 Snecma Roue de turbine a aubes ceramique
US5030063A (en) * 1990-02-08 1991-07-09 General Motors Corporation Turbomachine rotor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR319370A (fr) * 1902-03-07 1902-11-11 Fullagar Perfectionnements apportés aux turbines à fluide sous pression et aux turbo-pompes
US2918253A (en) * 1956-05-18 1959-12-22 Orenda Engines Ltd Rotor assemblies for turbines
US2948505A (en) * 1956-12-26 1960-08-09 Gen Electric Gas turbine rotor

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2075417A1 (fr) 2007-12-27 2009-07-01 Techspace aero Plateforme et aube pour une roue aubagée de turbomachine, roue aubagée et compresseur ou turbomachine comportant une telle roue aubagée
US8348619B2 (en) 2007-12-27 2013-01-08 Techspace Aero Platform and blade for a bladed wheel of a turbomachine, bladed wheel and compressor or turbomachine comprising such a bladed wheel
FR2940353A1 (fr) * 2008-12-23 2010-06-25 Snecma Roue mobile de turbomachine a aubes en materiau composite.
FR2940350A1 (fr) * 2008-12-23 2010-06-25 Snecma Roue mobile de turbomachine a aubes en materiau composite munie d'un anneau ressort.
WO2010072968A1 (fr) * 2008-12-23 2010-07-01 Snecma Roue mobile de turbomachine a aubes en materiau composite munie d'un anneau ressort
US8282355B2 (en) 2008-12-23 2012-10-09 Snecma Turbomachine rotor wheel having composite material blades
US8905710B2 (en) 2008-12-23 2014-12-09 Snecma Turbine engine rotor wheel with blades made of a composite material provided with a spring ring
EP3683450A1 (fr) * 2019-01-18 2020-07-22 Safran Aero Boosters S.A. Ensemble rotatif de turbomachine
BE1026984B1 (fr) * 2019-01-18 2020-08-25 Safran Aero Boosters Sa Ensemble rotatif de turbomachine

Also Published As

Publication number Publication date
FR2679599B1 (enExample) 1995-01-20
FR2679599A1 (fr) 1993-01-29
US5263823A (en) 1993-11-23

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