EP2009245A1 - Gebläserotor - Google Patents

Gebläserotor Download PDF

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Publication number
EP2009245A1
EP2009245A1 EP08159121A EP08159121A EP2009245A1 EP 2009245 A1 EP2009245 A1 EP 2009245A1 EP 08159121 A EP08159121 A EP 08159121A EP 08159121 A EP08159121 A EP 08159121A EP 2009245 A1 EP2009245 A1 EP 2009245A1
Authority
EP
European Patent Office
Prior art keywords
wedge
cell
blade root
rotor according
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.)
Granted
Application number
EP08159121A
Other languages
English (en)
French (fr)
Other versions
EP2009245B1 (de
EP2009245B2 (de
Inventor
Olivier Belmonte
Jean-Luc Christina Yvon Goga
Jean-Noël Mahieu
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
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
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Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP2009245A1 publication Critical patent/EP2009245A1/de
Publication of EP2009245B1 publication Critical patent/EP2009245B1/de
Application granted granted Critical
Publication of EP2009245B2 publication Critical patent/EP2009245B2/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • 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
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations

Definitions

  • the invention generally relates to a turbomachine rotor more particularly a fan rotor comprising a disc provided with cells at its periphery and blades respectively attached to said rotor, each blade having a blade root engaged in a corresponding cell.
  • the invention relates to an improvement to an elongate wedge which is interposed between the blade root and the bottom of the cell.
  • the invention is particularly applicable to the assembly of blades made of 3D woven composite material, which are increasingly used in blowers. It relates to a wedge well adapted to this type of blade (although not exclusively), the wedge may itself be made of the same material or a similar material.
  • One of the aims of the invention is to improve the behavior of the vanes of a rotor, particularly a fan rotor, in the event of a serious incident resulting for example from the ingestion of a bird.
  • French Patent No. 2,841,609 illustrates a wedge having metal parts and semi-rigid elastomer parts.
  • the shape of this wedge allows to take into account the movements of the foot of the dawn during a critical event mentioned above. In such circumstances, the fan blade pivots under the impact, so the blade root rotates in the disk cavity.
  • the dawn in addition to the rotational movement, is plunged forward and backward in response.
  • the front, central and rear parts of the dawn undergo torsional movements and axial dive, of different amplitude for each of them.
  • the invention proposes a new type of wedge whose shape has been defined to reduce the shock during the contact between the blade and the cell, absorb some of the energy generated by the impact and reduce the risk of damage. of dawn.
  • the invention relates first of all to a fan rotor comprising a disk provided with cells at its periphery and blades respectively attached to said rotor, each blade comprising a blade root engaged in a corresponding cell and each cell containing an elongated shim interposed between the blade root and the bottom of the cell, characterized in that said shim is of elastically deformable material, in that at least one longitudinal section of this shim has a transverse profile in the form of arc to define two lateral zones in contact with corresponding lateral zones of the blade root and remote from the bottom of the cell and a central zone facing the corresponding central zone of the cell bottom.
  • the central zone of said section is remote from the corresponding central zone of the blade root. In other words, a slight gap remains between the central zone of the section of the hold and the central area facing the blade root.
  • the wedge consists of several aforementioned sections joined by narrower junctions.
  • the wedge has a wavy profile along its own longitudinal direction.
  • said wedge may longitudinally have a central region in contact with the bottom of the cell and two end regions (on either side of the central region, longitudinally) in contact with the blade root.
  • the section of the hold in normal operation, is adapted to the shape of the surrounding parts (blower disk and fan blade) and the assembly is done with a slight constraint between the blade root and the bottom. of the cell.
  • the dawn foot is plated on its bearing, bearing on the bottom of the cell (in the central part) and below the blade root on the lateral surfaces of it.
  • the wavy profile mentioned above optimizes the contacts between the ends and the center of the wedge on the one hand and between the blade and the disk, on the other hand.
  • the wedge by its flexibility follows the combined movement of torsion-diving when a critical event occurs. It comes to interpose to limit the shock between the dawn foot and the alveolus of the disc.
  • the contact zone between the wedge and the underside of the blade root is curved so as to allow relative sliding of the two parts together, during pivoting of the blade.
  • the wedge is divided into three sections which react separately to the combined movements of the blade root and make it possible to better accompany the movements and deformations specific to each part of the blade root.
  • a polyurethane film-like coating or the like is disposed on and / or under the shim to help dissipate some of the energy of the impact and therefore limit the risk of breakage of the wedge and cracking of the blade root.
  • the wedge is made of a one-piece elastic composite material and preferably of 3D woven composite material.
  • the invention also relates to a wedge intended to be inserted in a blower rotor cell, characterized in that it consists of an elastically deformable material and in that it comprises at least one longitudinal profile section. cross-shaped arc.
  • a shim 11 intended to be inserted into a cavity 13 of a fan rotor disc 15. Such a disk is partially represented on the Figures 2 to 4 .
  • the shim 11 consists of a single block of elastically deformable material and more particularly here a composite woven 3D known per se. It is recalled that the 3-dimensional weave defining the core of the piece is coated with resin.
  • the shim comprises at least one longitudinal section arcuate cross section.
  • Such shim is intended to be inserted into a tangential cavity 13 made at the periphery of the rotor disc 15.
  • it is a fan rotor disk to which blades 20 are attached.
  • Each blade comprises a blade root 21 engaged in a corresponding cell 13.
  • a hold such as that shown in Figures 1 and 2 is housed in each cell 13 being interposed between the blade root 21 and the bottom 13a of the cell 13.
  • the shim 11 is preferably made of 3D woven composite material.
  • the wedge is of elastically deformable material.
  • the or each longitudinal section 17a-17c of this wedge has a transverse profile in the form of an arc to define two lateral zones 25a, 25b in contact with corresponding lateral zones 26a, 26b of the foot of dawn 20 while being away from the bottom of the cell. Furthermore, a central zone 29 of the wedge section is located opposite the corresponding central zone 30 of the cell bottom. This central zone of the wedge section may be in contact with the bottom of the cell, as is visible on the figure 3 .
  • the central zone of said section may be remote from the corresponding central area of the blade root, leaving a slight gap 32 between them.
  • the wedge 11 has a wavy profile in its longitudinal direction.
  • the wedge longitudinally has a central region 11a in contact with the bottom of the cell and two end regions 11b in contact with the blade root but remote from the bottom of the cell.
  • the wedge is shown mounted under stress between the blade root and the bottom of the cell, so that its longitudinal curvature between the center and the ends is less than it is in the unconstrained state, before mounting.
  • a polyurethane film-like coating or the like is disposed on and / or under the shim. This makes it possible to dissipate part of the energy of the shock, in the event of an incident, and consequently to limit the risks of breakage of the wedge or cracking of the blade root.
  • this type of shim is well adapted to maintain a blade of 3D woven composite material in its cell, at rest or in normal operation.
  • Oblong holes 35 are furthermore made in the central zones of at least some sections, to further improve the flexibility and the deformability of the different parts of the hold.
  • the shape of the wedge combined with the classic shape of the blade root optimizes the contacts between the ends and the center of the wedge on the one hand and the contact between the blade root and the walls of the blade. cell on the other hand.
  • the wedge section has two further thinning 36 between the side portions in contact with the blade root and the middle portion facing the bottom of the cell.
  • each junction 18 connecting two adjacent sections 17a-17c is substantially in the extension and continuity of the central zones of these two sections, it joins.
  • said junction has a transverse profile substantially identical to that of the central zone of a aforementioned section.
  • the proposed solution which consists in giving a form adapted to the wedge and preferably in making it in a flexible material identical to the material of the composite blade makes it possible to eliminate the risk of cracking the blade root.
  • the preload assembly allows to properly press the blade root on its bearing, bearing on the bottom of the cavity of the disc.
  • the wavy shape of the wedge in the axial direction, optimizes the contacts between the ends and the center of the wedge on the one hand and between the blade and the disk on the other hand.
  • the wedge by its flexibility, follows the combined movement of torsion / diving of the foot of dawn, during a critical event.
  • the wedge is interposed to limit the impact between the blade root and the disk cavity.
  • the area in contact between the wedge and the underside of the blade root is of curved shape, which allows a relative sliding of the two parts during a large pivot.
  • the three sections of the hold react separately to the movement of the dawn, which allows to better accompany the movement of each part of the foot of the dawn.

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)
  • Wind Motors (AREA)
EP08159121.6A 2007-06-26 2008-06-26 Gebläserotor Active EP2009245B2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0756015A FR2918129B1 (fr) 2007-06-26 2007-06-26 Perfectionnement a une cale intercalee entre un pied d'aube et le fond de l'alveole du disque dans laquelle il est monte

Publications (3)

Publication Number Publication Date
EP2009245A1 true EP2009245A1 (de) 2008-12-31
EP2009245B1 EP2009245B1 (de) 2017-10-04
EP2009245B2 EP2009245B2 (de) 2020-12-16

Family

ID=39154378

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08159121.6A Active EP2009245B2 (de) 2007-06-26 2008-06-26 Gebläserotor

Country Status (6)

Country Link
US (2) US8529209B2 (de)
EP (1) EP2009245B2 (de)
JP (1) JP5496476B2 (de)
CA (1) CA2634942C (de)
FR (1) FR2918129B1 (de)
RU (1) RU2479724C2 (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2455588A1 (de) * 2010-11-15 2012-05-23 MTU Aero Engines GmbH Sicherungsmittel zur axialen Sicherung eines Schaufelfußes einer Turbomaschinenschaufel
EP2562356A1 (de) * 2011-08-24 2013-02-27 Siemens Aktiengesellschaft Schaufelanordnung
EP2395200A3 (de) * 2010-06-11 2015-01-21 United Technologies Corporation Schaufelbefestigung in einer Gasturbine
EP2977547A1 (de) * 2014-07-22 2016-01-27 United Technologies Corporation Rotorschaufelschwalbenschwanz mit abgerundeten laufflächen
WO2021074554A1 (fr) * 2019-10-18 2021-04-22 Safran Aircraft Engines Ensemble pour une aube de turbomachine comprenant une attache définissant une alvéole et une cale adaptée pour être reçue dans l'alvéole en même temps qu'un pied de l'aube
WO2022079360A1 (fr) 2020-10-16 2022-04-21 Safran Aircraft Engines Ensemble d'attache pour une aube de turbomachine
FR3124546A1 (fr) 2021-06-28 2022-12-30 Safran Aircraft Engines Aube de rotor a maintien ameliore, procede de fabrication d’une telle aube et rotor comportant une telle aube

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2945074B1 (fr) * 2009-04-29 2011-06-03 Snecma Cale d'aube de soufflante renforcee
IT1403416B1 (it) * 2010-12-21 2013-10-17 Avio Spa Rotore palettato di una turbina a gas per motori aeronautici e metodo per il raffreddamento di detto rotore palettato
GB201106278D0 (en) * 2011-04-14 2011-05-25 Rolls Royce Plc Annulus filler system
FR2975428B1 (fr) * 2011-05-17 2015-11-20 Snecma Roue a aubes de turbomachine
FR2981132B1 (fr) * 2011-10-10 2013-12-06 Snecma Ensemble pour turbomachine a refroidissement de disque
US8851854B2 (en) * 2011-12-16 2014-10-07 United Technologies Corporation Energy absorbent fan blade spacer
US9422819B2 (en) * 2012-12-18 2016-08-23 United Technologies Corporation Rotor blade root spacer for arranging between a rotor disk and a root of a rotor blade
US9359906B2 (en) 2012-12-18 2016-06-07 United Technologies Corporation Rotor blade root spacer with a fracture feature
US20150322805A1 (en) * 2012-12-27 2015-11-12 United Technologies Corporation Blade underroot spacer with hook removal
US10508556B2 (en) 2013-01-17 2019-12-17 United Technologies Corporation Rotor blade root spacer with grip element
US9840922B2 (en) 2014-03-07 2017-12-12 United Technologies Corporation Fan blade spacer
GB201417417D0 (en) * 2014-10-02 2014-11-19 Rolls Royce Plc Slider
US10099323B2 (en) 2015-10-19 2018-10-16 Rolls-Royce Corporation Rotating structure and a method of producing the rotating structure
RU198476U1 (ru) * 2020-02-03 2020-07-13 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Диск ротора газотурбинного двигателя из никелевого жаропрочного сплава
US11242761B2 (en) 2020-02-18 2022-02-08 Raytheon Technologies Corporation Tangential rotor blade slot spacer for a gas turbine engine
FR3107724B1 (fr) 2020-02-27 2022-06-24 Safran Aircraft Engines Rotor de soufflante à aubes à calage variable et turbomachine équipée d’un tel rotor
KR102454379B1 (ko) * 2020-09-08 2022-10-14 두산에너빌리티 주식회사 로터 및 이를 포함하는 터보머신
FR3120389B1 (fr) 2021-03-04 2023-06-02 Safran Aircraft Engines Ensemble pour un rotor pour une turbomachine
FR3121171B1 (fr) 2021-03-25 2023-04-14 Safran Aircraft Engines Rotor de soufflante pour une turbomachine
KR20230091604A (ko) * 2021-12-16 2023-06-23 한화에어로스페이스 주식회사 보호심을 구비하는 로터 어셈블리 및 이를 포함하는 가스 터빈 엔진
FR3132126B1 (fr) * 2022-01-24 2025-02-21 Safran Aircraft Engines Moteur d'aéronef comprenant des aubes fixées au carter
FR3139159B1 (fr) * 2022-08-31 2024-07-19 Safran Aircraft Engines Roue de turbine comprenant un dispositif de maintien radial de pieds d’aube dans les alveoles d’un disque de rotor
US12146421B2 (en) * 2022-10-28 2024-11-19 Rtx Corporation Deformable root spacer for a gas turbine engine rotor blade
FR3159192A1 (fr) * 2024-02-08 2025-08-15 Safran Aircraft Engines Cale pour aube mobile de turbomachine

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EP0699824A1 (de) * 1994-08-29 1996-03-06 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Einrichtung zur Laufschaufelfixierung und zur Beseitigung von Rotorwuchten bei axial durchströmten Verdichtern oder Turbinen von Gasturbinentriebwerken
EP1138879A1 (de) * 2000-03-30 2001-10-04 ALSTOM Power N.V. Turbinenrotorscheibe und Schaufelbefestigung mittels Tannenbaumfuss und Montageverfahren
FR2841609A1 (fr) 2002-06-27 2004-01-02 Snecma Moteurs Cale de retenue du pied des aubes de soufflante
DE102005008509A1 (de) * 2004-02-25 2005-09-22 Mitsubishi Heavy Industries, Ltd. Laufschaufelkörper und Rotationsmaschine mit einem Laufschaufelkörper
EP1693551A1 (de) * 2005-01-27 2006-08-23 Snecma Vorrichtung zur Positionierung einer Rotorschaufel und beschaufelte Rotorscheibe mit einer solchen Vorrichtung

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US5519677A (en) * 1993-03-22 1996-05-21 Sony Corporation Biaxial actuator for driving an objective lens in both focusing and tracking directions
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RU2227150C1 (ru) * 2002-12-10 2004-04-20 Открытое акционерное общество "Термостойкие изделия и инженерные разработки" Слоистый уплотнительный материал для прокладки
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Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0699824A1 (de) * 1994-08-29 1996-03-06 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Einrichtung zur Laufschaufelfixierung und zur Beseitigung von Rotorwuchten bei axial durchströmten Verdichtern oder Turbinen von Gasturbinentriebwerken
EP1138879A1 (de) * 2000-03-30 2001-10-04 ALSTOM Power N.V. Turbinenrotorscheibe und Schaufelbefestigung mittels Tannenbaumfuss und Montageverfahren
FR2841609A1 (fr) 2002-06-27 2004-01-02 Snecma Moteurs Cale de retenue du pied des aubes de soufflante
DE102005008509A1 (de) * 2004-02-25 2005-09-22 Mitsubishi Heavy Industries, Ltd. Laufschaufelkörper und Rotationsmaschine mit einem Laufschaufelkörper
EP1693551A1 (de) * 2005-01-27 2006-08-23 Snecma Vorrichtung zur Positionierung einer Rotorschaufel und beschaufelte Rotorscheibe mit einer solchen Vorrichtung

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2395200A3 (de) * 2010-06-11 2015-01-21 United Technologies Corporation Schaufelbefestigung in einer Gasturbine
WO2012065599A1 (de) 2010-11-15 2012-05-24 Mtu Aero Engines Gmbh Sicherungsmittel zur axialen sicherung eines schaufelfusses einer turbomaschinenschaufel
US9470099B2 (en) 2010-11-15 2016-10-18 Mtu Aero Engines Gmbh Securing device for axially securing a blade root of a turbomachine blade
EP2455588A1 (de) * 2010-11-15 2012-05-23 MTU Aero Engines GmbH Sicherungsmittel zur axialen Sicherung eines Schaufelfußes einer Turbomaschinenschaufel
CN104053858B (zh) * 2011-08-24 2016-02-17 西门子公司 叶片装置
WO2013026735A1 (de) * 2011-08-24 2013-02-28 Siemens Aktiengesellschaft Schaufelanordnung
EP2562356A1 (de) * 2011-08-24 2013-02-27 Siemens Aktiengesellschaft Schaufelanordnung
US9708919B2 (en) 2011-08-24 2017-07-18 Siemens Aktiengesellschaft Blade arrangement
EP2977547A1 (de) * 2014-07-22 2016-01-27 United Technologies Corporation Rotorschaufelschwalbenschwanz mit abgerundeten laufflächen
WO2021074554A1 (fr) * 2019-10-18 2021-04-22 Safran Aircraft Engines Ensemble pour une aube de turbomachine comprenant une attache définissant une alvéole et une cale adaptée pour être reçue dans l'alvéole en même temps qu'un pied de l'aube
FR3102206A1 (fr) * 2019-10-18 2021-04-23 Safran Aircraft Engines Ensemble pour une aube de turbomachine comprenant une attache définissant une alvéole et une cale adaptée pour être reçue dans l’alvéole en même temps qu’un pied de l’aube
WO2022079360A1 (fr) 2020-10-16 2022-04-21 Safran Aircraft Engines Ensemble d'attache pour une aube de turbomachine
US12140046B2 (en) 2020-10-16 2024-11-12 Safran Aircraft Engines Fastening assembly for a turbomachine blade
FR3124546A1 (fr) 2021-06-28 2022-12-30 Safran Aircraft Engines Aube de rotor a maintien ameliore, procede de fabrication d’une telle aube et rotor comportant une telle aube

Also Published As

Publication number Publication date
FR2918129B1 (fr) 2009-10-30
US20090004017A1 (en) 2009-01-01
US20130259695A1 (en) 2013-10-03
CA2634942A1 (fr) 2008-12-26
EP2009245B1 (de) 2017-10-04
EP2009245B2 (de) 2020-12-16
JP2009008079A (ja) 2009-01-15
FR2918129A1 (fr) 2009-01-02
CA2634942C (fr) 2015-12-01
JP5496476B2 (ja) 2014-05-21
RU2008125805A (ru) 2009-12-27
US8529209B2 (en) 2013-09-10
US8845294B2 (en) 2014-09-30
RU2479724C2 (ru) 2013-04-20

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