Deprecated: The each() function is deprecated. This message will be suppressed on further calls in /home/zhenxiangba/zhenxiangba.com/public_html/phproxy-improved-master/index.php on line 456
EP2562361B2 - Aube directrice de sortie de fan composite structurelle pour turbomachine - Google Patents
[go: Go Back, main page]

EP2562361B2 - Aube directrice de sortie de fan composite structurelle pour turbomachine - Google Patents

Aube directrice de sortie de fan composite structurelle pour turbomachine Download PDF

Info

Publication number
EP2562361B2
EP2562361B2 EP12181806.6A EP12181806A EP2562361B2 EP 2562361 B2 EP2562361 B2 EP 2562361B2 EP 12181806 A EP12181806 A EP 12181806A EP 2562361 B2 EP2562361 B2 EP 2562361B2
Authority
EP
European Patent Office
Prior art keywords
exit guide
fan
gas turbine
turbine engine
diameter shroud
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.)
Active
Application number
EP12181806.6A
Other languages
German (de)
English (en)
Other versions
EP2562361A1 (fr
EP2562361B1 (fr
Inventor
Nicholas D. Stilin
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.)
RTX Corp
Original Assignee
United Technologies Corp
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=46750230&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP2562361(B2) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP2562361A1 publication Critical patent/EP2562361A1/fr
Application granted granted Critical
Publication of EP2562361B1 publication Critical patent/EP2562361B1/fr
Publication of EP2562361B2 publication Critical patent/EP2562361B2/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced

Definitions

  • the present disclosure is directed toward turbomachine assemblies and more particularly, toward a structural fan exit guide vane for use in a gas turbine engine.
  • Turbomachines such as gas turbine engines, draw air or other gases into the machine using a fan component.
  • the rotation of the fan blades drawing the air in causes the incoming air to swirl in the direction of the fan's rotation.
  • the air In order to operate the turbomachine properly, however, the air must pass axially through the turbomachine.
  • turbomachines include fan exit guide vanes that straighten the air flow behind the fan blades.
  • Fan exit guide vanes assemblies include multiple vanes, each of which has an airfoil shaped profile that is aerodynamically designed to force the airflow passing through the fan exit guide vane into an axial flow path. Also included within turbomachine assemblies is a separate fan frame that supports the engine core, the fan, and the fan case. The fan frame also maintains the concentricness of the fan case, and the fan blades, and the engine core, thus providing for proper fan tip clearance between the engine shroud and the fan blades.
  • EP 0513958 A2 describes a composite fan stator assembly for a gas turbine engine having at least two fan rotor stages.
  • EP 0654586 A1 describes a stator vane assembly comprising a row of spaced stator vanes for passing engine fluid working medium in a gas turbine engine.
  • WO 91/15357 A1 describes a fabric preform for reinforcing a composite structure gas turbine engine blade.
  • US 2006/113706 A1 describes a method of producing parts made of a high temperature-resistant composite, such as the vanes of an inlet guide vane assembly.
  • US 2009/0317246 A discloses a guide vane segment for a by-pass flow channel of an engine.
  • the guide vane segment comprises an outer ring and inner ring with guide vanes arranged therebetween.
  • the segments are formed of fiber-reinforced plastic composite material.
  • Figure 1A illustrates a partial side view of an air intake for a gas turbine engine 10.
  • Figure 1B illustrates a front view of the gas turbine engine 10 with a cutout view 60 illustrating the fan exit guide vanes 50 behind the fan blades 30.
  • the gas turbine engine 10 has an air intake fan 40 that rotates fan blades 30 radially about an axis A.
  • the rotation of the fan blades 30 draws air into the gas turbine engine 10 along a flow path 32.
  • the fan 40 is encased in a fan case 20, such as a turbine engine shroud. As the air passes through the fan blades 30, the air begins swirling radially relative to axis A due to the rotation of the fan blades 30.
  • each of the structural fan exit guide vane segments 50 includes multiple foil shaped guide vanes 52.
  • Each guide vane 52 is connected to an inner diameter shroud 58 and an outer diameter shroud 56.
  • Each of the outer diameter shrouds 56 are connected to the fan case 20.
  • Each of the inner diameter shrouds 58 are connected to an engine core 42.
  • the structural fan exit guide vanes 50 provide structural support to the engine core 42 and the fan case 20, thereby ensuring that proper clearance is maintained between the tips of the fan blades 30 and the fan case 20. Additionally, the structural support of the structural fan exit guide vane segments 50 maintains the concentricness of the engine core 42, the fan blades 30, and the fan case 20.
  • FIG. 1B illustrates a front view of the gas turbine engine 10, with a cutout segment 60 illustrating the structural fan exit guide vane segments 50 positioned axially behind the fan blades 30.
  • Each of the structural fan exit guide vanes segments 50 includes a first exit guide vane 52 and a second exit guide vane 54.
  • the outer diameter shroud 56 of each structural fan exit guide vane segment 50 abuts the outer diameter shrouds of each adjacent structural fan exit guide vane segment 50 resulting in a circular structural fan exit guide vane segment assembly behind the fan blades 30.
  • the structural fan exit guide vane assembly structurally supports the engine core 42, the fan blades 30, and the fan case 20 and axially straightens the flow path 32.
  • each of the inner diameter shrouds 58 abuts the inner diameter shrouds 58 of each adjacent structural fan exit guide vane segment 50.
  • each structural fan exit guide vane segment 50 abutting two adjacent fan exit guide vane segments 50 creates a circular structural fan exit guide vane assembly that provides the structural support described above, and the airflow straightening described above, while at the same time not requiring a separate structural frame assembly to support the fan 40, the fan case 20, and the engine core 42.
  • FIG. 2 illustrates a more detailed contextual side drawing of a single structural fan exit guide vane 100.
  • the outer diameter shroud 156 and the inner diameter shroud 158 of the structural fan exit guide vane 100 are connected by guide vanes 152, 154.
  • Each of the shrouds 156, 158 is fastened to the fan case 20 and the engine case 42 via a plurality of fasteners 170, such as bolts.
  • the fasteners 170 protrude through the shrouds 156, 158 and into the fan case 20 and the engine core 42.
  • Each of the inner diameter shroud 158 and the outer diameter shroud 156 also includes a fiber bulge 160, resulting from the molding process, that physically contacts the fan case 20 (in the case of the outer diameter shroud 156) and the engine core 42 (in the case of the inner diameter shroud 158).
  • FIG 3A illustrates an isometric view of a structural fan exit guide vane segment 200 that can be used as the structural fan exit guide vane segment 50 of Figures 1A and 1B .
  • the structural fan exit guide vane segment 200 includes an arced outer diameter shroud 256 and an arced inner diameter shroud 258 with each of the arcs being coaxial.
  • the shrouds 256, 258 are connected via two fan exit guide vanes 252, 254.
  • Each of the shrouds 256, 258 also includes multiple counter sunk holes 272 for fastening the shrouds 256, 258 to the fan case 20 and the engine core 42.
  • the arcing of the shrouds is concentric.
  • the countersinking of the fastener bolts allows the fastener heads to be flush with the exposed surface of the shrouds 256, 258, thereby minimizing the effect of the fasteners on the airflow along the flow path 32 through the gas turbine engine 10.
  • integral flow path spacer 280 Also attached to both the inner and the outer diameter shrouds 256, 258 is an integral flow path spacer 280.
  • the integral flow path spacer 280 on the outer diameter shroud 256 is visible in Figure 3A , while the integral flow path spacer 280 on the inner diameter shroud 258 is hidden due to the view angle.
  • the integral flow path spacer 280 provides an airflow seal between each structural guide vane 200 and the adjacent structural guide vanes 200.
  • the integral flow path spacer 280 is only placed on a single shroud edge of each of the inner and outer diameter shrouds 256, 258.
  • each shroud edge with a spacer abuts an edge of an adjacent shroud 256, 258 without a spacer resulting in each abutment being sealed by a single integral flow path spacer 280.
  • Each of the guide vanes 252, 254 has an airfoil shaped profile that allows the vanes 252, 254 to force air passing through the structural fan exit guide vane assembly into an axial flow path.
  • the particular foil profile of the vanes 252, 254 can be designed according to known techniques to fit the requirements of a particular gas turbine engine implementation.
  • Figure 3B illustrates an alternate viewpoint of the structural guide vane assembly of Figure 3A , with like numerals indicating like elements.
  • the view shown in Figure 3B shows the integral flow path spacer 280 on each of the inner and outer diameter shrouds 256, 258. Also illustrated is the fiber bulge 260 on the inner diameter shroud 256.
  • the isometric view of Figure 3B further illustrates the foil profile of the guide vanes 252, 254.
  • Figure 4 provides a zoomed isometric view of the outer diameter shroud 256 and the integral flow path spacer 280 of Figures 3A and 3B .
  • the integral flow path spacer 280 is a solid piece of flexible material, such as rubber, and includes a seal portion 282 and a connection portion 284.
  • the seal portion 282 overhangs the edge of the outer diameter shroud 258.
  • the seal portion 282 deforms to provide an airtight seal between the two outer diameter shrouds 256.
  • the seal portion 282 also provides vibrational damping between the structural guide vane segments 200.
  • connection portion 284 of the integral flow path spacer 280 is affixed to the shroud segment, attaching the integral flow path spacer 282 to the shroud.
  • a similar integral flow path spacer 282 design is used with the inner diameter shroud 258.
  • the structural fan exit guide vane segments described above and illustrated in the figures use a single monolithic carbon/epoxy structure to construct the guide vane segment as a single piece.
  • the two vanes are shaped into a preform having the desired airfoil profile using a continuous or semi-continuous fiber.
  • the fiber preform is then infused with a carbon/epoxy resin during a molding process.
  • This type of resin molding generates an end component that is a single piece and is constructed of a fiber reinforced polymer matrix composite.
  • the molding process also creates the inner and outer diameter shrouds using standard carbon/epoxy laminate molding processes.
  • the counter sunk holes can either be created as part of the molding process or drilled after the molding process is finished.
  • three or more guide vanes can be constructed in the same manner, and could be used in each monolithic vane segment and still fall within the above disclosure.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (9)

  1. Moteur à turbine à gaz comprenant :
    un ventilateur (40) ; et
    un cadre de ventilateur supportant ledit ventilateur (40) ;
    ledit cadre de ventilateur comprenant une pluralité de segments d'aube de guidage de sortie de ventilateur (200), dans lequel chacun desdits segments d'aube de guidage de sortie de ventilateur composites structurels (200) comprend :
    un composant monolithique présentant un bandage de diamètre intérieur (258) ;
    un bandage de diamètre extérieur (256) ;
    une pluralité d'aubes de guidage de sortie de ventilateur (252, 254) raccordant ledit bandage de diamètre intérieur (258) et ledit bandage de diamètre extérieur (256) ;
    dans lequel ledit bandage de diamètre intérieur (258) comprend au moins un trou fraisé (272) utilisable pour raccorder ledit bandage de diamètre intérieur (258) à un cadre de moteur (42) ; et
    dans lequel ledit bandage de diamètre extérieur (256) comprend au moins un trou fraisé (272) utilisable pour raccorder ledit bandage de diamètre extérieur (256) à un carter de moteur (20) ;
    dans lequel ledit bandage de diamètre intérieur (258) est un segment d'arc présentant un premier rayon, ledit bandage de diamètre extérieur (256) est un segment d'arc présentant un second rayon, et ledit second rayon est plus grand que ledit premier rayon ; et
    dans lequel ledit bandage de diamètre intérieur (258) comprend une pluralité de trous fraisés (272), un élément de fixation faisant saillie au travers de chacun de ladite pluralité de trous fraisés (272) fixant ainsi ledit segment d'aube de guidage de sortie de ventilateur (200) audit cadre ; et dans lequel ledit bandage de diamètre extérieur (256) comprend une pluralité de trous fraisés (272), un élément de fixation faisant saillie au travers de chacun de ladite pluralité de trous fraisés (272) fixant ainsi ledit segment d'aube de guidage de sortie de ventilateur (200) à un carter de moteur, et dans lequel une tête de chaque dit élément de fixation est alignée sur de tels trous fraisés (272) de sorte que les têtes d'élément de fixation soient alignées sur la surface exposée des bandages (256, 258) minimisant ainsi l'effet des éléments de fixation sur le flux d'air le long de la voie de flux du moteur à turbine à gaz.
  2. Moteur à turbine à gaz selon la revendication 1, dans lequel ledit composant monolithique (200) est construit en un matériau composite, ledit matériau composite comprenant par exemple un moulage de laminé carbone/époxy.
  3. Moteur à turbine à gaz selon une quelconque revendication précédente, comprenant en outre un écarteur de voie de flux intégral (280) fixé à un seul côté dudit bandage de diamètre extérieur (256) et/ou dudit bandage de diamètre intérieur (258).
  4. Moteur à turbine à gaz selon une quelconque revendication précédente, dans lequel chacune desdites aubes de guidage de sortie de ventilateur (252 ; 254) présente un profil en forme de profil aérodynamique.
  5. Moteur à turbine à gaz selon une quelconque revendication précédente, dans lequel ladite pluralité d'aubes de guidage de sortie de ventilateur (252 ; 254) comprend exactement deux aubes de guidage de sortie de ventilateur (252 ; 254).
  6. Moteur à turbine à gaz selon une quelconque revendication précédente, dans lequel ladite pluralité d'aubes de guidage de sortie de ventilateur (252 ; 254) comprend un composite de matrice de polymère renforcé par des fibres.
  7. Moteur à turbine à gaz selon une quelconque revendication précédente, dans lequel chacun de ladite pluralité de segments de guidage de sortie de ventilateur (200) bute contre au moins deux segments d'aube de guidage de sortie de ventilateur adjacents (200).
  8. Moteur à turbine à gaz selon la revendication 7, comprenant en outre un écarteur de voie de flux intégral (280) utilisable pour créer un joint entre chaque bandage de diamètre extérieur en butée (256) et/ou comprenant en outre un écarteur de voie de flux intégral (280) utilisable pour créer un joint entre chaque bandage de diamètre intérieur en butée (258).
  9. Moteur à turbine à gaz selon l'une quelconque des revendications 1 à 8, dans lequel chacun de ladite pluralité de segments d'aubes de guidage de sortie de ventilateur (200) supporte structurellement ledit moteur à turbine à gaz, par exemple dans lequel ledit moteur à turbine à gaz est supporté structurellement sur une sortie de gaz via seulement lesdits segments d'aube de guidage de sortie de ventilateur (200).
EP12181806.6A 2011-08-25 2012-08-24 Aube directrice de sortie de fan composite structurelle pour turbomachine Active EP2562361B2 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/217,372 US20130052004A1 (en) 2011-08-25 2011-08-25 Structural composite fan exit guide vane for a turbomachine

Publications (3)

Publication Number Publication Date
EP2562361A1 EP2562361A1 (fr) 2013-02-27
EP2562361B1 EP2562361B1 (fr) 2015-12-09
EP2562361B2 true EP2562361B2 (fr) 2019-04-10

Family

ID=46750230

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12181806.6A Active EP2562361B2 (fr) 2011-08-25 2012-08-24 Aube directrice de sortie de fan composite structurelle pour turbomachine

Country Status (2)

Country Link
US (1) US20130052004A1 (fr)
EP (1) EP2562361B2 (fr)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9303520B2 (en) * 2011-12-09 2016-04-05 General Electric Company Double fan outlet guide vane with structural platforms
US20130149130A1 (en) * 2011-12-09 2013-06-13 General Electric Company Fan Hub Frame for Double Outlet Guide Vane
US9303531B2 (en) * 2011-12-09 2016-04-05 General Electric Company Quick engine change assembly for outlet guide vanes
EP2735706B8 (fr) * 2012-11-21 2016-12-07 Safran Aero Booster S.A. Redresseur à aubes de compresseur de turbomachine axiale et procédé de fabrication
FR3003668B1 (fr) * 2013-03-25 2020-10-30 Snecma Procede de conception d'une preforme commune pour la realisation de preformes d'aubes directrices de sortie de turbomachine en materiau composite a profils geometriques differents
US20160146104A1 (en) * 2013-07-08 2016-05-26 United Technologies Corporation Angled Core Engine
FR3021714B1 (fr) * 2014-06-02 2016-06-24 Snecma Obturateur d'orifice de fixation d'aube d'un redresseur de turbomachine
US10589475B2 (en) 2014-09-23 2020-03-17 General Electric Company Braided blades and vanes having dovetail roots
GB201513232D0 (en) * 2015-07-28 2015-09-09 Rolls Royce Plc A nozzle guide vane passage
US10047763B2 (en) * 2015-12-14 2018-08-14 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling
US10774788B2 (en) * 2016-06-28 2020-09-15 Raytheon Technologies Corporation Particle extraction system for a gas turbine engine
US10385868B2 (en) * 2016-07-05 2019-08-20 General Electric Company Strut assembly for an aircraft engine
US10570917B2 (en) 2016-08-01 2020-02-25 United Technologies Corporation Fan blade with composite cover
FR3056250B1 (fr) * 2016-09-19 2020-06-05 Safran Aircraft Engines Roue d'aube redresseuse en carter intermediaire
US10443625B2 (en) * 2016-09-21 2019-10-15 General Electric Company Airfoil singlets
US10724390B2 (en) 2018-03-16 2020-07-28 General Electric Company Collar support assembly for airfoils
US10483659B1 (en) * 2018-11-19 2019-11-19 United Technologies Corporation Grounding clip for bonded vanes
FR3091723B1 (fr) * 2019-01-15 2021-04-02 Safran Aircraft Engines Aube ou Pale d'hélice composite pour aéronef intégrant une pièce de conformation
FR3134598B1 (fr) * 2022-04-15 2024-04-05 Safran Aircraft Engines Aube fixe en matériaux composites fixée radialement sur une structure fixe d’une turbomachine
FR3166179A1 (fr) * 2024-09-12 2026-03-13 Safran Aircraft Engines Section de soufflante avec joint deformable

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0953729A1 (fr) † 1998-05-01 1999-11-03 Techspace aero Aubage redresseur de turbomachine
US20090317246A1 (en) † 2006-06-30 2009-12-24 Fischer Advanced Composite Components Ag Guide Vane Arrangement for a Driving Mechanism
EP2339120A1 (fr) † 2009-12-22 2011-06-29 Techspace Aero S.A. Étage redresseur de turbomachine et compresseur associé

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2942843A (en) * 1956-06-15 1960-06-28 Westinghouse Electric Corp Blade vibration damping structure
GB1237532A (en) * 1967-06-24 1971-06-30 Rolls Royce Improvements in turbines and compresser rotors
GB2161110B (en) * 1984-07-07 1988-03-23 Rolls Royce An annular bladed member having an integral shroud and a method of manufacture thereof
GB9007162D0 (en) * 1990-03-30 1990-05-30 Courtaulds Plc Preform and composite structure
US5226789A (en) * 1991-05-13 1993-07-13 General Electric Company Composite fan stator assembly
JP3631271B2 (ja) * 1993-11-19 2005-03-23 ユナイテッド テクノロジーズ コーポレイション インナーシュラウド一体型ステータベーン構造
US5722813A (en) * 1996-10-28 1998-03-03 Alliedsignal Inc. Segmented composite compressor deswirl
US6821087B2 (en) * 2002-01-21 2004-11-23 Honda Giken Kogyo Kabushiki Kaisha Flow-rectifying member and its unit and method for producing flow-rectifying member
FR2852884B1 (fr) * 2003-03-26 2005-05-06 Hurel Hispano Procede de fabrication de pieces en composite a matrice polyimide
US7645120B2 (en) * 2005-04-27 2010-01-12 Honda Motor Co., Ltd. Flow-guiding member unit and its production method
US8105039B1 (en) * 2011-04-01 2012-01-31 United Technologies Corp. Airfoil tip shroud damper

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0953729A1 (fr) † 1998-05-01 1999-11-03 Techspace aero Aubage redresseur de turbomachine
US20090317246A1 (en) † 2006-06-30 2009-12-24 Fischer Advanced Composite Components Ag Guide Vane Arrangement for a Driving Mechanism
EP2339120A1 (fr) † 2009-12-22 2011-06-29 Techspace Aero S.A. Étage redresseur de turbomachine et compresseur associé

Also Published As

Publication number Publication date
US20130052004A1 (en) 2013-02-28
EP2562361A1 (fr) 2013-02-27
EP2562361B1 (fr) 2015-12-09

Similar Documents

Publication Publication Date Title
EP2562361B2 (fr) Aube directrice de sortie de fan composite structurelle pour turbomachine
EP2586990B1 (fr) Dispositif de protection de cheville
US8182209B2 (en) Air reinjection compressor
US10358929B2 (en) Composite airfoil
EP2778427B1 (fr) Système de recirculation automatique de purge de compresseur
US9482095B2 (en) Web connected dual aerofoil members
EP2867503B1 (fr) Ensemble carénage
EP2213840A2 (fr) Support d'aubes statoriques pour une turbomachine et procédé pour minimiser le poids associé
EP2811138B1 (fr) Structure de partie de couplage pour aube et moteur à réaction utilisant la même
EP2971552B1 (fr) Plateforme de ventilateur composite moulée par injection
KR20080063131A (ko) 안내 날개 및 이를 제조하는 방법
EP1924758B1 (fr) Ensemble d'aubes avec bagues extérieures
US20150192140A1 (en) Composite Housing with a Metallic Flange for the Compressor of an Axial Turbomachine
US10738630B2 (en) Platform apparatus for propulsion rotor
EP1926887B1 (fr) Ensemble d'aubes à pieds d'aube améliorés
US12535007B2 (en) Cover plate connections for a hollow fan blade
US7413400B2 (en) Vane assembly with grommet
JP4820373B2 (ja) スタティックガスタービン部分品及びそうした部分品の補修法
US9951654B2 (en) Stator blade sector for an axial turbomachine with a dual means of fixing
EP2932069B1 (fr) Organe de retenue de moyeu de turbine
EP3064741B1 (fr) Rotor de compresseur centrifugue en fleche vers l'avant pour moteurs à turbine à gaz
US8087871B2 (en) Turbomachine compressor wheel member
US10393019B2 (en) Assembly and method for influencing flow through a fan of a gas turbine engine
US10247043B2 (en) Ducted cowl support for a gas turbine engine
EP2865879B1 (fr) Structure de partie de liaison d'aube, et turboréacteur utilisant ladite structure

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

17P Request for examination filed

Effective date: 20130814

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

17Q First examination report despatched

Effective date: 20141217

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20150701

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 764671

Country of ref document: AT

Kind code of ref document: T

Effective date: 20151215

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602012012842

Country of ref document: DE

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20151209

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160309

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 764671

Country of ref document: AT

Kind code of ref document: T

Effective date: 20151209

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160310

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160411

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160409

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

REG Reference to a national code

Ref country code: DE

Ref legal event code: R026

Ref document number: 602012012842

Country of ref document: DE

PLBI Opposition filed

Free format text: ORIGINAL CODE: 0009260

REG Reference to a national code

Ref country code: CH

Ref legal event code: PCOW

Free format text: NEW ADDRESS: 10 FARM SPRINGS RD., FARMINGTON, CT 06032 (US)

PLAX Notice of opposition and request to file observation + time limit sent

Free format text: ORIGINAL CODE: EPIDOSNOBS2

26 Opposition filed

Opponent name: SAFRAN AIRCRAFT ENGINES

Effective date: 20160908

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: UNITED TECHNOLOGIES CORPORATION

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 5

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

PLBB Reply of patent proprietor to notice(s) of opposition received

Free format text: ORIGINAL CODE: EPIDOSNOBS3

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160831

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160831

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 602012012842

Country of ref document: DE

Representative=s name: SCHMITT-NILSON SCHRAUD WAIBEL WOHLFROM PATENTA, DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 6

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 602012012842

Country of ref document: DE

Representative=s name: SCHMITT-NILSON SCHRAUD WAIBEL WOHLFROM PATENTA, DE

Ref country code: DE

Ref legal event code: R081

Ref document number: 602012012842

Country of ref document: DE

Owner name: UNITED TECHNOLOGIES CORP. (N.D.GES.D. STAATES , US

Free format text: FORMER OWNER: UNITED TECHNOLOGIES CORPORATION, HARTFORD, CONN., US

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160824

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160824

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20120824

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

Ref country code: MT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160831

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 7

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

APBM Appeal reference recorded

Free format text: ORIGINAL CODE: EPIDOSNREFNO

APBP Date of receipt of notice of appeal recorded

Free format text: ORIGINAL CODE: EPIDOSNNOA2O

APAH Appeal reference modified

Free format text: ORIGINAL CODE: EPIDOSCREFNO

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151209

APBU Appeal procedure closed

Free format text: ORIGINAL CODE: EPIDOSNNOA9O

PUAH Patent maintained in amended form

Free format text: ORIGINAL CODE: 0009272

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: PATENT MAINTAINED AS AMENDED

27A Patent maintained in amended form

Effective date: 20190410

AK Designated contracting states

Kind code of ref document: B2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: DE

Ref legal event code: R102

Ref document number: 602012012842

Country of ref document: DE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602012012842

Country of ref document: DE

Owner name: RAYTHEON TECHNOLOGIES CORPORATION (N.D.GES.D.S, US

Free format text: FORMER OWNER: UNITED TECHNOLOGIES CORP. (N.D.GES.D. STAATES DELAWARE), FARMINGTON, CONN., US

Ref country code: DE

Ref legal event code: R081

Ref document number: 602012012842

Country of ref document: DE

Owner name: RTX CORPORATION (N.D.GES.D. STAATES DELAWARE),, US

Free format text: FORMER OWNER: UNITED TECHNOLOGIES CORP. (N.D.GES.D. STAATES DELAWARE), FARMINGTON, CONN., US

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230520

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20250724

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20250724

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20250725

Year of fee payment: 14

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602012012842

Country of ref document: DE

Owner name: RTX CORPORATION (N.D.GES.D. STAATES DELAWARE),, US

Free format text: FORMER OWNER: RAYTHEON TECHNOLOGIES CORPORATION (N.D.GES.D.STAATES DELAWARE), ARLINGTON, VA, US