EP2796668A2 - Section de carter d'un étage de compresseur ou de turbine d'une turbomachine - Google Patents

Section de carter d'un étage de compresseur ou de turbine d'une turbomachine Download PDF

Info

Publication number
EP2796668A2
EP2796668A2 EP14164186.0A EP14164186A EP2796668A2 EP 2796668 A2 EP2796668 A2 EP 2796668A2 EP 14164186 A EP14164186 A EP 14164186A EP 2796668 A2 EP2796668 A2 EP 2796668A2
Authority
EP
European Patent Office
Prior art keywords
webs
housing section
housing
section according
turbomachine
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
EP14164186.0A
Other languages
German (de)
English (en)
Other versions
EP2796668B1 (fr
EP2796668A3 (fr
Inventor
Karl Maar
Thomas Hess
Petra Kufner
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2796668A2 publication Critical patent/EP2796668A2/fr
Publication of EP2796668A3 publication Critical patent/EP2796668A3/fr
Application granted granted Critical
Publication of EP2796668B1 publication Critical patent/EP2796668B1/fr
Not-in-force 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F01D11/125—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material with a reinforcing structure
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave

Definitions

  • the invention relates to a housing section of a turbomachine compressor or turbomachine turbine stage according to the preamble of claim 1 and to a turbomachine, in particular gas turbine, with such a housing section.
  • a housing portion encloses a flow space in which rotating blades are disposed.
  • the wall thickness of the housing portion can be increased, but this has the disadvantage that increases the weight of the housing portion.
  • the object of the invention is to provide a turbomachine compressor stage or a turbine engine stage which has sufficient safety with low weight.
  • a turbomachine compressor or turbomachine turbine stage has at least one housing section with a radially outer jacket.
  • the radially outer shell has a plurality of webs, which extend radially inwardly, wherein the webs are inclined to the radius.
  • the radially outer shell is in one embodiment, in particular in cross section, closed and formed like an annular ring.
  • the radially outer shell can be longitudinally divided and composed of two or more parts permanently or detachably.
  • the webs are materially connected to the radially outer jacket, in particular formed integrally therewith, in particular urgeformt.
  • An advantage of radially inwardly extending lands may be that the weight of the housing portion is not significantly increased, but at the same time it is ensured that abutment of blades or parts thereof will not result in excessive deformation the radially outer shell and thus the housing section leads. Additionally or alternatively, an advantage of the housing portion may be that it can be manufactured by an additive manufacturing method, wherein different materials can be used for the production of the housing portion. Additionally or alternatively, an advantage of such webs may be that the stiffness of the housing portion is positively influenced to transmit maximum loads.
  • a housing section of a turbomachine compressor stage or turbine engine stage is understood in particular to be a housing section which encloses one or more rotor blade stages of a turbomachine arranged one after the other in the flow direction.
  • the turbomachine compressor stage and / or turbine engine stage may be preceded by at least one vane stage and / or at least one vane stage downstream.
  • Turbomachinery compressor stage is understood in one embodiment that portion of the turbomachine, which exclusively compresses an air mass flow determined for a combustion chamber of the turbomachine.
  • a fan upstream of the turbomachine compressor stage may promote mass air flow and bypass flow.
  • a diameter ratio of the rotor blades to the stator blades may be greater than or equal to 0.5, in particular 0.75, preferably 0.85.
  • a radius is understood as meaning a direction from a longitudinal axis of the housing section to the radially outer jacket, the direction being perpendicular to the longitudinal axis.
  • the webs may be inclined axially. This means that the webs can extend along the longitudinal axis of the housing portion and perpendicular to this. Additionally or alternatively, the webs in the circumferential direction of the Housing section extend.
  • the webs are connected to an inner shell. Radially inwardly of the inner shell may be arranged a flow channel jacket which limits a flow space of the step. Similarly, the inner shell itself can limit the flow space of the stage and thus act as a flow channel jacket. Additionally or alternatively, the webs may be interconnected.
  • the webs may be formed in a cross section perpendicular to the web longitudinal axis circular or polygonal. In one embodiment, webs can define, in particular enclose, a cavity, which can be axially inclined analogously to the webs and can extend in the longitudinal direction.
  • One or more, defined by webs, in particular enclosed cavities communicate in one embodiment with a coolant, in particular cooling air inlet and / or a coolant, in particular cooling air outlet.
  • the coolant inlet and / or coolant outlet can each be provided in a housing shell, which can be axially upstream or downstream of the housing section of the turbomachine compressor or turbomachine turbine stage.
  • the housing shell may enclose at least one vane stage.
  • a defined by lands cavity communicates in one embodiment only with the coolant inlet and / or the coolant outlet. In one embodiment, the cavity does not communicate with a flow space in which, among other things, the blades and / or vanes are arranged and which is enclosed by the housing portion and the housing shells.
  • the cavities it is preferably possible to reduce or reduce a heat input into the housing section and thus to reduce the temperature of the housing section.
  • the cavity for the transfer of coolant, in particular cooling air, between the upstream and downstream housing shells can be used, which can also have a positive effect on the heat input into the housing section.
  • The, in particular interconnected, webs can form a lattice or honeycomb structure in cross section, in particular in a cross section perpendicular to the web longitudinal axis.
  • Another advantage of such a cavity defined by webs may consist in that a transport of coolant which is virtually free of leakage loss can be achieved between the housing shell arranged upstream and downstream of the housing section. Additionally or alternatively, a reduced number of components and thus a reduction of the possible wear points can be achieved.
  • the webs may be prefolded.
  • the webs may be prefolded such that they fold under load loading, such as due to abutment of a broken blade or part thereof, according to a predetermined folding characteristic.
  • Individual webs can be separated from each other by a cavity and / or not connected to each other.
  • individual webs in particular with an end remote from the radially outer jacket, can be connected to an inner jacket.
  • the webs can be pre-folded several times, in particular zigzag-like, convex and / or concave.
  • Prefolded webs may in particular have at least two sections which, preferably in one edge, merge into one another and are inclined in opposite directions axially and / or in the circumferential direction against the radius.
  • a stiffener In a cavity between webs, a stiffener may be arranged.
  • the stiffener may have a grid or honeycomb structure in cross-section. The stiffener may improve the stiffness of the housing portion upon impact of the blades or parts of these against the housing portion and counteract deformation of the housing portion.
  • the housing section described above may be part of a turbomachine, in particular a gas turbine. It is clear that the turbomachine can also have a plurality of housing sections described above.
  • housing portion 1 has a radially outer shell 10 and an inner shell 11.
  • the radially outer shell 10 is separated from the inner shell 11 by a cavity 13.
  • From the radially outer jacket 10 extend in the cavity 13, a plurality of webs 12 radially inwardly.
  • the webs 12 are connected at one end to the radially outer shell 10 and at the other end to the inner shell 11.
  • a flow channel jacket 16 is arranged, which defines a flow space 2.
  • blades 4 are arranged.
  • the housing portion 1 a plurality of axially offset from one another arranged guides 14 for (in Fig. 1 not shown) adjustable vanes.
  • the guides 14 are connected to the radially outer shell 10 and the inner shell 11 respectively integrally formed and with the flow channel jacket 16 form, material and / or frictionally connected.
  • the webs 12 are repeatedly prefolded and thus inclined to the radius, so that at a load stress on the housing portion 1, the webs 12 are folded according to a predetermined folding characteristic. In particular, a folding of the webs 12 takes place in the radial direction.
  • the webs 12 are arranged in the axial direction within the cavity 13 adjacent to each other and pre-folded several times zigzag.
  • FIG. 2 Fig. 3 shows a longitudinal section of a housing section 100 according to another embodiment of the present invention.
  • the housing portion 100 has a radially outer shell 10 from which a plurality of webs 120 extend radially inwardly, wherein the webs 120 are interconnected.
  • the webs 120 are inclined axially, wherein the webs 120 in the illustrated case obliquely to a longitudinal axis, not shown, of the housing portion 100 (horizontally in Fig. 2 ).
  • the interconnected webs 120 form a grid or honeycomb structure in a cross section perpendicular to the web longitudinal axis.
  • the in FIG. 3 shown housing section 100 has in addition to the in FIG. 2 shown housing portion 100 on an inner shell 11.
  • the webs 120 are connected to the radially outer shell 10.
  • FIG. 3 shown webs 120 enclose analogous to those in FIG. 2 illustrated webs 120 cavities, through the cooling air from a cooling air inlet (left in Fig. 3 ) to a cooling air outlet (right in Fig. 3 ), as in Fig. 3 indicated by flow arrows.
  • an inlet means 3 is provided, which extends radially inwardly.
  • the inlet means 3 can come into contact with a blade 4 and serves in particular to reduce an undesirable leakage flow between the blade 4 and the inner shell 11 of the housing portion 100.
  • the housing portion 100 is at its upstream side (left in FIG Fig. 3 ) is connected in the connecting portion 14 via a screw with a housing shell 200. Further, the housing portion 100 is at the downstream side thereof (right in FIG Fig. 3 ) connected via a further connecting portion 15 with a further housing shell 201.
  • the two housing shells 200, 201 may each enclose a stator vane not shown. In the connection of the further housing shell 201 with the housing portion 100 may be a positive connection.
  • the in FIG. 4 illustrated housing portion 100 ' differs from that in FIG. 3 illustrated housing portion 100 characterized in that no inner shell 10 is provided in this.
  • the inlet means 3 ' is formed integrally with the webs 120'. It is ensured that the inlet means is positioned so that it can come into contact with the blades 4 '.
  • the cooling air inlet opening is in the connecting section 14 and the cooling air outlet opening is provided in the further connecting section 15.
  • the cooling air inlet opening and the cooling air outlet opening communicate with a cooling air channel provided in the respective housing shell 200, 201.
  • cooling air flows through the cooling air inlet opening into the cavities of the webs and flows through them to the cooling air outlet opening.
  • cooling air can flow via the housing section 100 between two housing shells 200, 201 adjacent to the turbomachine in the longitudinal axis direction, the flow direction of the cooling air being illustrated by the arrows P in the figures.
  • the webs and the cooling air inlet opening and the cooling air outlet opening are formed such that the cooling air does not communicate with the flow space 2 of the turbomachine.
EP14164186.0A 2013-04-24 2014-04-10 Section de carter d'un étage de compresseur ou de turbine d'une turbomachine Not-in-force EP2796668B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013207452.2A DE102013207452A1 (de) 2013-04-24 2013-04-24 Gehäuseabschnitt einer Turbomaschinenverdichter- oder Turbomaschinenturbinenstufe

Publications (3)

Publication Number Publication Date
EP2796668A2 true EP2796668A2 (fr) 2014-10-29
EP2796668A3 EP2796668A3 (fr) 2015-01-21
EP2796668B1 EP2796668B1 (fr) 2017-03-01

Family

ID=50478268

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14164186.0A Not-in-force EP2796668B1 (fr) 2013-04-24 2014-04-10 Section de carter d'un étage de compresseur ou de turbine d'une turbomachine

Country Status (4)

Country Link
US (1) US9771830B2 (fr)
EP (1) EP2796668B1 (fr)
DE (1) DE102013207452A1 (fr)
ES (1) ES2620514T3 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3375984A1 (fr) * 2017-03-17 2018-09-19 MTU Aero Engines GmbH Dispositif de circulation pour une turbomachine, procédé de fabrication d'un dispositif de circulation et turbomachine

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015202070A1 (de) 2015-02-05 2016-08-25 MTU Aero Engines AG Gasturbinenbauteil
FR3040733B1 (fr) * 2015-09-07 2018-08-31 Poly Shape Carter pour machines tournantes et en particulier pour turbomachines.
US20170089213A1 (en) 2015-09-28 2017-03-30 United Technologies Corporation Duct with additive manufactured seal
DE102016201581A1 (de) * 2016-02-02 2017-08-03 MTU Aero Engines AG Rotor-Stator-Verbund für eine axiale Strömungsmaschine und Flugtriebwerk
US10830097B2 (en) * 2016-02-04 2020-11-10 General Electric Company Engine casing with internal coolant flow patterns
US10209009B2 (en) 2016-06-21 2019-02-19 General Electric Company Heat exchanger including passageways
US10802467B2 (en) * 2017-01-06 2020-10-13 General Electric Company Methods of defining internal structures for additive manufacturing
US11427330B2 (en) 2019-11-15 2022-08-30 General Electric Company System and method for cooling a leading edge of a high speed vehicle
US11260953B2 (en) 2019-11-15 2022-03-01 General Electric Company System and method for cooling a leading edge of a high speed vehicle
US11352120B2 (en) 2019-11-15 2022-06-07 General Electric Company System and method for cooling a leading edge of a high speed vehicle
US11260976B2 (en) 2019-11-15 2022-03-01 General Electric Company System for reducing thermal stresses in a leading edge of a high speed vehicle
US11267551B2 (en) 2019-11-15 2022-03-08 General Electric Company System and method for cooling a leading edge of a high speed vehicle
US11466593B2 (en) 2020-01-07 2022-10-11 Raytheon Technologies Corporation Double walled stator housing
US11745847B2 (en) 2020-12-08 2023-09-05 General Electric Company System and method for cooling a leading edge of a high speed vehicle
US11407488B2 (en) 2020-12-14 2022-08-09 General Electric Company System and method for cooling a leading edge of a high speed vehicle
US11577817B2 (en) 2021-02-11 2023-02-14 General Electric Company System and method for cooling a leading edge of a high speed vehicle

Family Cites Families (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3046648A (en) * 1959-04-13 1962-07-31 Aircraft Prec Products Inc Method of manufacturing replaceable labyrinth type seal assembly
US3365172A (en) * 1966-11-02 1968-01-23 Gen Electric Air cooled shroud seal
US3719365A (en) * 1971-10-18 1973-03-06 Gen Motors Corp Seal structure
USRE30600E (en) * 1973-02-23 1981-05-05 International Harvester Company Compliant structural members
GB2017228B (en) * 1977-07-14 1982-05-06 Pratt & Witney Aircraft Of Can Shroud for a turbine rotor
FR2467978A1 (fr) * 1979-10-23 1981-04-30 Snecma Dispositif de retention pour carter de compresseur d'une turbomachine
US4452335A (en) * 1982-05-03 1984-06-05 United Technologies Corporation Sound absorbing structure for a gas turbine engine
US5160248A (en) * 1991-02-25 1992-11-03 General Electric Company Fan case liner for a gas turbine engine with improved foreign body impact resistance
US5520508A (en) * 1994-12-05 1996-05-28 United Technologies Corporation Compressor endwall treatment
GB2313161B (en) * 1996-05-14 2000-05-31 Rolls Royce Plc Gas turbine engine casing
US5791871A (en) * 1996-12-18 1998-08-11 United Technologies Corporation Turbine engine rotor assembly blade outer air seal
US6182531B1 (en) * 1998-06-12 2001-02-06 The Boeing Company Containment ring for flywheel failure
GB0116988D0 (en) * 2000-08-11 2001-09-05 Rolls Royce Plc A gas turbine engine blade containment assembly
GB0510538D0 (en) * 2005-05-24 2005-06-29 Rolls Royce Plc A rotor blade containment assembly for a gas turbine engine
GB0609632D0 (en) * 2006-05-16 2006-06-28 Rolls Royce Plc An ice impact panel
US8371009B2 (en) * 2007-12-12 2013-02-12 General Electric Company Methods for repairing composite containment casings
FR2925118B1 (fr) * 2007-12-14 2009-12-25 Snecma Panneau de support d'abradable dans une turbomachine
GB0813820D0 (en) * 2008-07-29 2008-09-03 Rolls Royce Plc A fan casing for a gas turbine engine
US8202041B2 (en) * 2008-10-31 2012-06-19 Pratt & Whitney Canada Corp Fan case for turbofan engine
GB0916823D0 (en) * 2009-09-25 2009-11-04 Rolls Royce Plc Containment casing for an aero engine
GB201003634D0 (en) * 2010-03-05 2010-04-21 Rolls Royce Plc Containment casing
US8500390B2 (en) * 2010-05-20 2013-08-06 Pratt & Whitney Canada Corp. Fan case with rub elements
GB201020143D0 (en) * 2010-11-29 2011-01-12 Rolls Royce Plc A gas turbine engine blade containment arrangement
GB201103682D0 (en) * 2011-03-04 2011-04-20 Rolls Royce Plc A turbomachine casing assembly

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3375984A1 (fr) * 2017-03-17 2018-09-19 MTU Aero Engines GmbH Dispositif de circulation pour une turbomachine, procédé de fabrication d'un dispositif de circulation et turbomachine

Also Published As

Publication number Publication date
EP2796668B1 (fr) 2017-03-01
EP2796668A3 (fr) 2015-01-21
ES2620514T3 (es) 2017-06-28
US9771830B2 (en) 2017-09-26
US20140321998A1 (en) 2014-10-30
DE102013207452A1 (de) 2014-11-13

Similar Documents

Publication Publication Date Title
EP2796668B1 (fr) Section de carter d'un étage de compresseur ou de turbine d'une turbomachine
DE60203959T2 (de) Luftgekühltes Abgasgehäuse für eine Gasturbine
DE112015001237B4 (de) Abgasturbolader
DE60211061T2 (de) Axialturbine mit einer Stufe in einem Abströmkanal
EP2179143B1 (fr) Refroidissement de fente entre une paroi de chambre de combustion et une paroi de turbine d'une installation de turbine à gaz
DE1601564A1 (de) Mantelring fuer Gasturbinenanlagen
DE102011055473B4 (de) Strömungspfad für ein Dampfturbinenaußengehäuse und Strömungsbarrierevorrichtung
EP3093447B1 (fr) Rotor d'une turbine a gaz ayant un guidage d'air de refroidissement ameliore
EP2824282A1 (fr) Turbine à gaz avec système de refroidissement de turbine à haute pression
DE102015101156A1 (de) Laufschaufel mit hoher Sehnenlänge, zwei Teilspannweiten-Dämpferelementen und gekrümmtem Schwalbenschwanz
EP2126321A1 (fr) Turbine à gaz présentant une couronne directrice et un mélangeur
DE112011104298T5 (de) Gasturbinenmotor mit Sekundärluftstromkreis
EP2818724B1 (fr) Turbomachine et procédé
EP2884054A1 (fr) Aube de guidage variable avec cône tronqué dans un ensemble palier
DE102017110055A1 (de) Zentraler Zwischenkanal, der äußere Wände hinter einem Vorderkantenkanal eines Schaufelblattes überbrückt
CH710576A2 (de) Turbinenschaufel mit mehreren Kühlkanälen.
EP3231998A1 (fr) Segment d'une aube statorique
EP2718545B1 (fr) Turbine à vapeur comprenant un piston de compensation
DE112015001212B4 (de) Deckband, Schaufelanordnung und Rotationsmaschine
CH701151B1 (de) Turbomaschine mit einem Verdichterradelement.
DE102012208263A1 (de) Verdichtervorrichtung für eine Turbomaschine
EP3495639B1 (fr) Module de compresseur pour une turbomachine réduisant la couche limite dans un carter intermédiaire de compresseur
DE102019135335A1 (de) Hybrid-laufschaufeln für turbinentriebwerke
DE60002781T2 (de) Nabe-Achse Verbindung
EP2725203B1 (fr) Conduite d'air froid dans une structure de boîtier d'une turbomachine

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

17P Request for examination filed

Effective date: 20140410

AK Designated contracting states

Kind code of ref document: A2

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

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

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

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 11/12 20060101AFI20141216BHEP

Ipc: F01D 21/04 20060101ALI20141216BHEP

Ipc: F01D 25/14 20060101ALI20141216BHEP

R17P Request for examination filed (corrected)

Effective date: 20150714

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

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20161115

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

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 871611

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170315

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502014002803

Country of ref document: DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 4

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2620514

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20170628

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20170301

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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: 20170301

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: 20170601

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: 20170602

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: 20170301

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: 20170301

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: 20170601

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: 20170301

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: 20170301

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: 20170301

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

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: 20170301

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: 20170301

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: 20170301

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: 20170301

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: 20170301

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: 20170301

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

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: 20170301

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: 20170301

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: 20170703

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: 20170701

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502014002803

Country of ref document: DE

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

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

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: 20170301

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: 20170301

26N No opposition filed

Effective date: 20171204

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

Ref country code: LI

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

Effective date: 20170430

Ref country code: CH

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

Effective date: 20170430

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: 20170301

Ref country code: LU

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

Effective date: 20170410

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20170430

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: IE

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

Effective date: 20170410

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 NON-PAYMENT OF DUE FEES

Effective date: 20170430

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

Ref country code: MT

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: 20170301

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

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: 20140410

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

Ref country code: ES

Payment date: 20190520

Year of fee payment: 6

Ref country code: DE

Payment date: 20190418

Year of fee payment: 6

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

Ref country code: FR

Payment date: 20190423

Year of fee payment: 6

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: 20170301

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

Ref country code: GB

Payment date: 20190424

Year of fee payment: 6

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

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: 20170301

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

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: 20170301

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: 20170301

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 871611

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190410

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502014002803

Country of ref document: DE

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

Ref country code: AT

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

Effective date: 20190410

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

Ref country code: DE

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

Effective date: 20201103

Ref country code: FR

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

Effective date: 20200430

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

Effective date: 20200410

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: 20200410

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20210831

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

Ref country code: ES

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

Effective date: 20200411