EP1319844B1 - Bague extérieure pour recevoir des pieds d'aubes de volets redresseurs dans un compresseur haute pression d'une turbine à gaz - Google Patents

Bague extérieure pour recevoir des pieds d'aubes de volets redresseurs dans un compresseur haute pression d'une turbine à gaz Download PDF

Info

Publication number
EP1319844B1
EP1319844B1 EP02023209A EP02023209A EP1319844B1 EP 1319844 B1 EP1319844 B1 EP 1319844B1 EP 02023209 A EP02023209 A EP 02023209A EP 02023209 A EP02023209 A EP 02023209A EP 1319844 B1 EP1319844 B1 EP 1319844B1
Authority
EP
European Patent Office
Prior art keywords
shroud
cover
accordance
support
annular
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 - Fee Related
Application number
EP02023209A
Other languages
German (de)
English (en)
Other versions
EP1319844A1 (fr
Inventor
Norbert Wolf
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1319844A1 publication Critical patent/EP1319844A1/fr
Application granted granted Critical
Publication of EP1319844B1 publication Critical patent/EP1319844B1/fr
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor

Definitions

  • the invention relates to a bearing ring for supporting blade roots of adjustable stator blades in the high-pressure compressor of a gas turbine, and in particular to a bearing ring according to the features of the preamble of claim 1.
  • the invention relates to a bearing ring (Shroud), as used in particular in high-pressure compressors modern turbofan engines for internal storage of the adjustable stator blades in the field of high pressure compressor.
  • bearing rings or shrouds are usually made of aluminum, steel alloys or titanium.
  • a construction of this kind shows, for example, the US 5,062,767 A , which shows a bearing ring according to the features of the preamble of claim 1.
  • the bearing rings are usually constructed in two parts, so that a front and a rear body are available. These basic bodies are each annular. To reduce weight, an axial annular space is formed, which is turned off, for example. In order to reduce air turbulence, vibrations and noise developments, the annular space is provided in the prior art with a rubber filling. This is introduced by means of a vulcanization process.
  • the invention has for its object to provide a bearing ring of the type mentioned above, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and in particular has a low weight.
  • annular cover body in the opening region of the annular space, an annular cover body is arranged, which is provided with mounting recesses. Furthermore, it is provided that a tubular support element is arranged in the intermediate region between the mounting recess of the cover body and the associated mounting hole of the base body.
  • the bearing ring according to the invention is characterized by a number of significant advantages.
  • annular covering body is used instead of the rubber filling subject to the above-mentioned disadvantages.
  • An essential advantage of the solution according to the invention is that it can be produced easily and quickly.
  • the complex operations that are required for introducing a rubber filling, can thus be completely eliminated. This results in a significant cost advantage over the prior art.
  • Another major advantage is that no age-prone materials, such as rubber, are used. This increases the reliability as well as the life.
  • Another advantage lies in the weight reduction to be achieved, since much less material is needed than in a filling with rubber or other filling materials.
  • the covering body according to the invention is used for covering in the mouth region of the annulus, no other structural changes to the body are required. It is thus possible to retrofit existing body after removing the rubber filling accordingly.
  • the cover can be easily removed and replaced at any time, for example during maintenance or other work.
  • the covering body is formed substantially in the form of a flat ring. This can be made in a simple manner, for example, from a metallic sheet, such as aluminum or titanium. Especially It is also advantageous if the cover body is profiled at least at its edges. A flanging or an edge can thus lead to a particularly advantageous clamping or to an interference fit, so that the cover body can be used reliably in the annular space.
  • stiffening measures such as beads or the like may be used.
  • the support element is preferably cup-shaped or hat-shaped. Like the cover body, it can be produced from a metallic sheet, by rolling or deep-drawing or by means of a similar forming process. It is particularly favorable if the free edge region of the support element is profiled for holding the covering body, for example bent or crimped.
  • the support member thus anchors the cover body and biases it against the base body, so that there is a secure attachment.
  • the bias is done by means of connecting screws, which also serve to clamp the two main body of the bearing ring.
  • the dimensioning of the support body is preferably chosen so that they are slightly shorter than the depth of the annular space of the body.
  • the gap size may be 0.5 mm, for example.
  • cover body and the support elements may be formed in one piece or in several parts.
  • cover body and the support elements may be produced in one piece or in several parts.
  • cover body and / or the support elements made of plastic or similar material, for example by means of a spraying process.
  • the Fig. 1 shows in a highly simplified manner a portion of a known from the prior art gas turbine.
  • the area A indicates the positioning of a bearing ring for the storage of stator blades 2.
  • the further description of the schematically indicated components can be dispensed with, since these are known from the prior art.
  • Fig. 2 is a perspective exploded view of a known from the prior art bearing ring shown, comprising a front body 3 and a rear body 4.
  • the two main body 3, 4 are each end turned and provided with a rubber filling 12 in the annular space 5 formed in this case.
  • the two basic bodies 1, 2 are each half recesses 14 introduced, the (see Fig. 3 ) serve for the storage of bushes 13, which in turn store a blade root 1 of the respective stator blade 2.
  • the stator blades 2 are rotatable in a known manner to change the angle of attack can. As a result, the performance of the compressor or compressor is adaptable to the operating conditions.
  • corresponding mounting holes 6 in the basic bodies 3, 4 are provided.
  • the Fig. 4 shows a simplified sectional view of the embodiment of the bearing ring according to the invention. This comprises, as already described, a front base body 3 and a rear base body 4. These are each provided with said mounting holes 6.
  • the Fig. 4 further shows the two substantially U-shaped annular spaces 5, which are each axially open.
  • Fig. 4 is a substantially flat, annular cover body 7 is shown (see also FIGS. 5 and 6 ), which is provided with a corresponding number of mounting recesses 8, which are aligned with the mounting holes 6 in order to perform the screws 15 can.
  • each hat-shaped or cup-shaped support member 9 is inserted, which, as well as from Fig. 7 can be seen, is provided with a central recess 17 in order to perform the screw 15 can.
  • Fig. 4 further shows that an edge 10 of the cover body 7 is profiled or bent to ensure a tight tight fit in the annulus 5. Similarly, an edge portion 11 of the support member 9 is bent or profiled to hold the cover body 7 and bias. For this purpose, the length of the support element 9 is slightly smaller than the available depth in the annular space 5, so that when tightening the screw 15, a corresponding tension of the cover body 7 results.
  • the Fig. 6 shows in a perspective partial view of the annular cover body 7, while in the illustration of Fig. 5 in a schematic way, the individual support elements 9 are shown in addition to the cover body 7.

Landscapes

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

Claims (11)

  1. Bague de palier destinée à loger des pieds (1) d'aubes de stator (2) réglables dans le compresseur à haute pression d'une turbine à gaz, avec un corps de base annulaire avant (3) et un corps de base annulaire arrière (4), qui présentent chacun un espace annulaire (5) ouvert dans le sens axial pour former une section transversale en forme de U pour l'essentiel, ainsi qu'une pluralité de perçages de montage (6) axiaux, caractérisée en ce que dans la zone d'ouverture de l'espace annulaire (5) est disposé un corps de recouvrement annulaire (7) muni d'évidements de montage (8), et qu'un élément de maintien (9) tubulaire est disposé dans la zone intermédiaire entre les évidements de montage (8) du corps de recouvrement annulaire (7) et les perçages de montage (6) associés des corps de base annulaires avant et arrière (3, 4).
  2. Bague de palier selon la revendication n° 1, caractérisée en ce que le corps de recouvrement (7) a pour l'essentiel la forme d'un anneau plat.
  3. Bague de palier selon la revendication n° 1 ou n° 2, caractérisée en ce que le corps de recouvrement (7) est fabriqué en tôle métallique.
  4. Bague de palier selon une des revendications n° 1 à n° 3, caractérisée en ce que le corps de recouvrement (7) est profilé au moins sur ses bords (10).
  5. Bague de palier selon une des revendications n° 1 à n° 4, caractérisée en ce que l'élément de maintien (9) a la forme d'une coupelle ou d'une chape.
  6. Bague de palier selon la revendication n° 5, caractérisée en ce que le que le rebord libre de l'élément de maintien (9) est profilé pour maintenir le corps de recouvrement (7).
  7. Bague de palier selon une des revendications n° 1 à n° 6, caractérisée en ce que le corps de recouvrement (7) et l'élément de maintien (9) sont formés comme composants distincts.
  8. Bague de palier selon une des revendications n° 1 à n° 6, caractérisée en ce que le corps de recouvrement (7) et l'élément de maintien (9) sont formés d'une seule pièce.
  9. Bague de palier selon une des revendications n° 1 à n° 8, caractérisée en ce que l'élément de maintien (9) présente une hauteur inférieure à la profondeur de l'espace annulaire (5).
  10. Bague de palier selon une des revendications n° 1 à n° 9, caractérisée en ce que le corps de recouvrement (7) et l'élément de maintien (9) sont fabriqués en métal.
  11. Bague de palier selon une des revendications n° 1 à n° 9, caractérisée en ce que le corps de recouvrement (7) et l'élément de maintien (9) sont fabriqués en matière plastique.
EP02023209A 2001-12-13 2002-10-16 Bague extérieure pour recevoir des pieds d'aubes de volets redresseurs dans un compresseur haute pression d'une turbine à gaz Expired - Fee Related EP1319844B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10161292 2001-12-13
DE10161292A DE10161292A1 (de) 2001-12-13 2001-12-13 Lagerring zur Lagerung von Schaufelfüßen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine

Publications (2)

Publication Number Publication Date
EP1319844A1 EP1319844A1 (fr) 2003-06-18
EP1319844B1 true EP1319844B1 (fr) 2009-12-02

Family

ID=7709105

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02023209A Expired - Fee Related EP1319844B1 (fr) 2001-12-13 2002-10-16 Bague extérieure pour recevoir des pieds d'aubes de volets redresseurs dans un compresseur haute pression d'une turbine à gaz

Country Status (3)

Country Link
US (1) US6790000B2 (fr)
EP (1) EP1319844B1 (fr)
DE (2) DE10161292A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014205986A1 (de) 2014-03-31 2015-10-01 MTU Aero Engines AG Leitschaufelkranz, Leitschaufel, Innenring und Strömungsmaschine
EP3176386A1 (fr) 2015-12-04 2017-06-07 MTU Aero Engines GmbH Système de virole interne, virole interne, boîtier intermédiaire et turbomachine associés

Families Citing this family (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10353810A1 (de) * 2003-11-17 2005-06-23 Rolls-Royce Deutschland Ltd & Co Kg Innendeckband für die Statorschaufeln des Verdichters einer Gasturbine
DE10358421A1 (de) * 2003-12-13 2005-07-07 Mtu Aero Engines Gmbh Rotor für eine Turbomaschine
GB0504588D0 (en) * 2005-03-05 2005-04-13 Rolls Royce Plc Pivot ring
US7753647B2 (en) * 2005-07-20 2010-07-13 United Technologies Corporation Lightweight cast inner diameter vane shroud for variable stator vanes
US7628579B2 (en) * 2005-07-20 2009-12-08 United Technologies Corporation Gear train variable vane synchronizing mechanism for inner diameter vane shroud
US7690889B2 (en) * 2005-07-20 2010-04-06 United Technologies Corporation Inner diameter variable vane actuation mechanism
US7588415B2 (en) * 2005-07-20 2009-09-15 United Technologies Corporation Synch ring variable vane synchronizing mechanism for inner diameter vane shroud
US7665959B2 (en) * 2005-07-20 2010-02-23 United Technologies Corporation Rack and pinion variable vane synchronizing mechanism for inner diameter vane shroud
US7510369B2 (en) * 2005-09-02 2009-03-31 United Technologies Corporation Sacrificial inner shroud liners for gas turbine engines
EP1811134A1 (fr) * 2006-01-23 2007-07-25 ABB Turbo Systems AG Dispositif de guidage réglable
DE102006024085B4 (de) 2006-05-23 2020-04-16 MTU Aero Engines AG Turboverdichter in Axialbauweise
US7713022B2 (en) * 2007-03-06 2010-05-11 United Technologies Operations Small radial profile shroud for variable vane structure in a gas turbine engine
US8328512B2 (en) 2009-06-05 2012-12-11 United Technologies Corporation Inner diameter shroud assembly for variable inlet guide vane structure in a gas turbine engine
US8777561B2 (en) 2010-11-05 2014-07-15 Hamilton Sundstrand Corporation Compressor shroud having a retention cover channel for receiving a retention cover
US9957832B2 (en) 2012-02-28 2018-05-01 United Technologies Corporation Variable area turbine
EP2644833A1 (fr) * 2012-03-26 2013-10-02 Alstom Technology Ltd Anneau de support
WO2014046965A1 (fr) * 2012-09-20 2014-03-27 United Technologies Corporation Module de système d'engrenage d'entraînement de soufflante et mécanisme d'accouplement d'aube de guidage d'entrée
US10107122B2 (en) 2013-02-10 2018-10-23 United Technologies Corporation Variable vane overlap shroud
FR3009335B1 (fr) * 2013-07-30 2015-09-04 Snecma Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine
WO2015077011A1 (fr) 2013-11-19 2015-05-28 United Technologies Corporation Extension de carénage interne à éléments multiples pour une turbomachine
FR3014152B1 (fr) * 2013-11-29 2015-12-25 Snecma Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine et procede d'assemblage d'un tel dispositif
DE102014223975A1 (de) * 2014-11-25 2016-05-25 MTU Aero Engines AG Leitschaufelkranz und Strömungsmaschine
US10072746B2 (en) * 2015-05-05 2018-09-11 Valeo Embrayages Stator assembly of hydrokinetic torque converter, and method for making the same
DE102016215807A1 (de) * 2016-08-23 2018-03-01 MTU Aero Engines AG Innenring für einen Leitschaufelkranz einer Strömungsmaschine
DE102017109952A1 (de) * 2017-05-09 2018-11-15 Rolls-Royce Deutschland Ltd & Co Kg Rotorvorrichtung einer Strömungsmaschine
DE102017209682A1 (de) * 2017-06-08 2018-12-13 MTU Aero Engines AG Axial geteilter Turbomaschinen-Innenring
US10526911B2 (en) * 2017-06-22 2020-01-07 United Technologies Corporation Split synchronization ring for variable vane assembly
DE102018203442A1 (de) * 2018-03-07 2019-09-12 MTU Aero Engines AG Innenring für eine Turbomaschine, Leitschaufelkranz mit einem Innenring, Turbomaschine und Verfahren zur Herstellung eines Innenrings
BE1026411B1 (fr) * 2018-06-21 2020-01-30 Safran Aero Boosters Sa Virole extérieure de turbomachine
DE102018210601A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Segmentring zur montage in einer strömungsmaschine
US11608747B2 (en) 2021-01-07 2023-03-21 General Electric Company Split shroud for vibration reduction
US11572794B2 (en) 2021-01-07 2023-02-07 General Electric Company Inner shroud damper for vibration reduction
US11629606B2 (en) * 2021-05-26 2023-04-18 General Electric Company Split-line stator vane assembly
CN113898419A (zh) * 2021-10-10 2022-01-07 中国航发沈阳发动机研究所 一种进气机匣结构及其组装方法
US11879480B1 (en) 2023-04-07 2024-01-23 Rolls-Royce North American Technologies Inc. Sectioned compressor inner band for variable pitch vane assemblies in gas turbine engines

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2868439A (en) * 1954-05-07 1959-01-13 Goodyear Aircraft Corp Plastic axial-flow compressor for gas turbines
DE2121707C3 (de) * 1971-05-03 1974-06-20 Motoren- Und Turbinen-Union Friedrichshafen Gmbh, 7990 Friedrichshafen Leitschaufelkranz
FR2524934B1 (fr) * 1982-04-08 1986-12-26 Snecma Dispositif de butee de securite pour pivot d'aubes de stator a calage variable
FR2582720B1 (fr) * 1985-05-29 1989-06-02 Snecma Procede de realisation de pivot d'aube de turbomachine et aube de stator le comportant
US4792277A (en) * 1987-07-08 1988-12-20 United Technologies Corporation Split shroud compressor
US4834613A (en) * 1988-02-26 1989-05-30 United Technologies Corporation Radially constrained variable vane shroud
US5279031A (en) * 1988-12-06 1994-01-18 Alliedsignal Inc. High temperature turbine engine structure
US5062767A (en) * 1990-04-27 1991-11-05 The United States Of America As Represented By The Secretary Of The Air Force Segmented composite inner shrouds
FR2685033B1 (fr) * 1991-12-11 1994-02-11 Snecma Stator dirigeant l'entree de l'air a l'interieur d'une turbomachine et procede de montage d'une aube de ce stator.
US5421703A (en) 1994-05-25 1995-06-06 General Electric Company Positively retained vane bushing for an axial flow compressor
FR2723614B1 (fr) * 1994-08-10 1996-09-13 Snecma Dispositif d'assemblage d'un etage circulaire d'aubes pivotantes.
CA2231986A1 (fr) * 1997-01-10 1999-09-12 Masahito Kataoka Pale fixe a secteur porte-aubes integre et methode de fabrication
FR2775731B1 (fr) * 1998-03-05 2000-04-07 Snecma Etage circulaire d'aubes aux extremites interieures unies par un anneau de liaison
US6164903A (en) * 1998-12-22 2000-12-26 United Technologies Corporation Turbine vane mounting arrangement
US6086327A (en) * 1999-01-20 2000-07-11 Mack Plastics Corporation Bushing for a jet engine vane

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014205986A1 (de) 2014-03-31 2015-10-01 MTU Aero Engines AG Leitschaufelkranz, Leitschaufel, Innenring und Strömungsmaschine
EP2955335A1 (fr) 2014-03-31 2015-12-16 MTU Aero Engines GmbH Stator, aube directrice, bague intérieure et turbomachine
US10578127B2 (en) 2014-03-31 2020-03-03 MTU Aero Engines AG Vane ring, inner ring, and turbomachine
DE102014205986B4 (de) * 2014-03-31 2021-03-18 MTU Aero Engines AG Leitschaufelkranz und Strömungsmaschine
EP3176386A1 (fr) 2015-12-04 2017-06-07 MTU Aero Engines GmbH Système de virole interne, virole interne, boîtier intermédiaire et turbomachine associés
US10494942B2 (en) 2015-12-04 2019-12-03 MTU Aero Engines AG Inner ring system for an inlet guide vane cascade of a turbomachine

Also Published As

Publication number Publication date
DE50214035D1 (de) 2010-01-14
US20030113204A1 (en) 2003-06-19
EP1319844A1 (fr) 2003-06-18
US6790000B2 (en) 2004-09-14
DE10161292A1 (de) 2003-06-26

Similar Documents

Publication Publication Date Title
EP1319844B1 (fr) Bague extérieure pour recevoir des pieds d'aubes de volets redresseurs dans un compresseur haute pression d'une turbine à gaz
EP1032749A1 (fr) Rotor a aubes integrees
DE102015224283A1 (de) Leitschaufelcluster für eine Strömungsmaschine
EP2268902B1 (fr) Entretoise pour carter intermédiaire de turbine et carter intermédiaire de turbine
WO2017093245A1 (fr) Roue de ventilateur pour un ventilateur axial
EP2520769A1 (fr) Anneau intérieur pour la formation d'une couronne d'aube directrice, couronne d'aube directrice et turbomachine
DE102014212174A1 (de) Bürstendichtungssystem zum Abdichten eines Spalts zwischen relativ zueinander bewegbaren Bauteilen einer Strömungsmaschine
EP1728972A2 (fr) Dispositif de verrouillage d'une aube de turbine
EP3287608B1 (fr) Bague intérieure d'une couronne d'aubes directrices d'une turbomachine
EP1462617B1 (fr) Aubage pour une turbomachine axiale
EP2394028B1 (fr) Dispositif d'étanchéité sur l'arbre à aubes d'un étage de rotor d'une turbomachine axiale et son utilisation
DE19643336C2 (de) Verfahren zum Demontieren des stirnseitigen Lagergehäuses oder ND-Verdichter-Wellenteiles eines Flugtriebwerkes
EP2378066A2 (fr) Rotor pour une turbomachine
EP3034788A2 (fr) Aube de compresseur d'une turbine a gaz
DE102008038038A1 (de) Laufschaufelsystem für eine Laufschaufelreihe einer Strömungsmaschine
EP1798420A2 (fr) Ventilateur axial à pales variables et méthode pour monter ce ventilateur
EP2133574A2 (fr) Grille de protection spatiale pour ventilateurs axiaux et procédé de fabrication de la grille de protection
DE102017204243A1 (de) Dichtfin mit zumindest einer gewölbten Seitenflanke
DE10225679A1 (de) Lagerring zur Lagerung von Schaufelfüßen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine
DE102008056512B4 (de) Verdichtergehäuse einer Strömungsmaschine mit schneckenförmigem Strömungskanal
DE102007053135A1 (de) Gasturbinenbauteil, insbesondere Flugtriebwerksbauteil bzw. Verdichterbauteil
EP3312388A1 (fr) Pultdach dichtfin
EP2577117B1 (fr) Procédé pour fixer un élément d'étanchéité à brosse dans une rainure d'un segment de boîtier
WO2019086065A1 (fr) Conduit intermédiaire produit par fabrication additive et destiné à être agencé entre un compresseur basse pression et un compresseur haute pression, ainsi que procédé de fabrication dudit conduit
EP2998515B1 (fr) Élements de remplissage d'un ventilateur d'une turbine a gaz

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

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR IE IT LI LU MC NL PT SE SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK RO SI

17P Request for examination filed

Effective date: 20030819

AKX Designation fees paid

Designated state(s): DE FR GB

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

RIN1 Information on inventor provided before grant (corrected)

Inventor name: WOLF, NORBERT

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 50214035

Country of ref document: DE

Date of ref document: 20100114

Kind code of ref document: P

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20100903

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

Ref country code: DE

Payment date: 20121029

Year of fee payment: 11

Ref country code: FR

Payment date: 20121107

Year of fee payment: 11

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

Ref country code: GB

Payment date: 20121025

Year of fee payment: 11

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 50214035

Country of ref document: DE

Representative=s name: HOEFER & PARTNER, DE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 50214035

Country of ref document: DE

Representative=s name: HOEFER & PARTNER, DE

Effective date: 20130402

Ref country code: DE

Ref legal event code: R081

Ref document number: 50214035

Country of ref document: DE

Owner name: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, DE

Free format text: FORMER OWNER: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, 15827 BLANKENFELDE, DE

Effective date: 20130402

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20131016

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

Ref country code: GB

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

Effective date: 20131016

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20140630

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 50214035

Country of ref document: DE

Effective date: 20140501

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

Ref country code: FR

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

Effective date: 20131031

Ref country code: DE

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

Effective date: 20140501