EP3495629B1 - Turbomaschinenströmungskanal - Google Patents

Turbomaschinenströmungskanal Download PDF

Info

Publication number
EP3495629B1
EP3495629B1 EP18209511.7A EP18209511A EP3495629B1 EP 3495629 B1 EP3495629 B1 EP 3495629B1 EP 18209511 A EP18209511 A EP 18209511A EP 3495629 B1 EP3495629 B1 EP 3495629B1
Authority
EP
European Patent Office
Prior art keywords
rib
ribs
thickness
flow channel
length
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
EP18209511.7A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3495629A1 (de
Inventor
Günter RAMM
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 EP3495629A1 publication Critical patent/EP3495629A1/de
Application granted granted Critical
Publication of EP3495629B1 publication Critical patent/EP3495629B1/de
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
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • F01D25/162—Bearing supports
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape

Definitions

  • the present invention relates to a flow duct, in particular a transition duct, for a turbomachine, in particular a gas turbine, a turbomachine, in particular a gas turbine, with the flow or transition duct, and an aircraft engine with the gas turbine.
  • a flow channel between two rotors is known, in which deflection vanes and supporting ribs with lines are arranged evenly distributed in the circumferential direction.
  • a flow channel is known in which are arranged in the circumferential direction evenly distributed support ribs with openings for receiving fasteners and from EP 3 095 964 A1 a flow channel is known, in which two groups of support ribs, which are arranged uniformly distributed in the circumferential direction and have openings for the supply of lubricant or coolant, are arranged.
  • An object of an embodiment of the present invention is to improve a turbomachine.
  • a flow duct for a turbomachine in particular a flow duct of a turbomachine, in particular an axial turbomachine, in particular a gas turbine, in particular an aircraft engine, has a plurality of ribs which are arranged between a radially inner lateral surface and a radially outer lateral surface of the flow duct , in one embodiment detachably or non-detachably, in particular cohesively, connected to the inner and/or outer lateral surface or formed integrally, and/or distributed in a circumferential direction, in particular at least partially next to each other or at least partially overlapping in the axial direction, with a first of Ribs have a first, in particular maximum, minimum or average, rib thickness, in particular in the circumferential direction (measured), and a first, in particular maximum, minimum or average, rib length, in particular chord length and/or in the axial direction (measured), and a second of the ribs a second, in particular maximum, minimum or average rib thickness
  • the axial direction is parallel to an axis of rotation, in particular a (main) machine axis, of the turbomachine, and the circumferential direction corresponds in particular to a direction of rotation about this axis.
  • a radial direction is perpendicular to the axial and circumferential directions.
  • this second rib length is smaller than this first rib length, in one embodiment by at least 1%, in particular by at least 5%, in one embodiment by at least 15%, and/or by at most 200%, in particular by at most 100%, in a design by at most 50%, the first or second rib length. Additionally or alternatively, according to one embodiment of the present invention, this second rib thickness is smaller than this first rib thickness, in one embodiment by at least 1%, in particular by at least 5%, in one embodiment by at least 15% and/or by at most 200%, in particular at most 100%, in one embodiment at most 50%, of the first or second rib thickness.
  • first internal structure which has a first, in particular maximum, minimum or average structural thickness, in particular in the circumferential or axial direction (measured)
  • second internal structure which has a second, in particular maximum, minimum or average structure thickness, in particular in the circumferential or axial direction (measured) which is smaller than the first structure thickness, in one embodiment by at least 1%, in particular by at least 5%, in one embodiment by at least 15%, and/or by at most 200%, in particular by at most 100%, in one embodiment by at most 50%, of the first or second structure thickness.
  • (at least) one (first) rib in which a thicker inner structure is arranged becomes (designed) thicker and/or longer than (at least) one (second) rib , in which a contrast thinner inner structure is arranged or is.
  • a deviation is
  • one and the other rib of a pair can be the aforementioned first and second ribs.
  • One and the other rib of one or more pairs can be adjacent (each in the circumferential direction) in one embodiment.
  • one or more other ribs without an internal structure and/or with at least essentially the same rib thickness and length as one or the other rib can be arranged between one rib and the other rib of one or more pairs (each in the circumferential direction).
  • rib thickness/length ratio d/l for two or more of the ribs with internal structures of different thicknesses, at least essentially, the same rib thickness/length ratio d/l given.
  • weight and/or efficiency can be (further) improved in one embodiment.
  • a distance T 12 differs in the circumferential direction according to one embodiment of the present invention between the first and second ribs adjacent thereto (circumferentially) and a circumferential distance T C between at least two (circumferentially) adjacent ones of the ribs, in particular the distance T 12 between the first and second ribs and the distance T 13 between the first and a third rib located on an opposite side of the first rib from the second rib, the distance T 12 between the first and second ribs, and distance T 23 between the second and a third rib located on an opposite side of the first rib Side of the second rib is arranged, and / or Distance T 12 between the first and second ribs and distance T 34 between a third and (circumferentially) adjacent fourth ribs different from the first and second ribs
  • these two distances differ or deviate by at least 1%, in particular by at least 5%, in one embodiment by at least 15%, and/or by at most 200%, in particular by at most 100%, in one embodiment by a maximum of 50%, the larger or smaller of the two distances (from each other).
  • ribs with at least partially different rib lengths and/or thicknesses are distributed non-uniformly in the circumferential direction.
  • a frequency or resonance behavior of the flow channel can be improved.
  • these two aspects of different rib thicknesses and/or lengths, in particular with at least essentially the same rib thickness/length ratio d/l, for inner structures of different thicknesses on the one hand and an uneven circumferential distribution of ribs with at least partially different rib lengths and/or thicknesses, which at least partially have internal structures and/or non-deflecting external profiles, on the other hand can be realized independently of one another, although in one embodiment they are advantageously combined with one another.
  • the plurality of ribs has ribs, two or more of which have inner structures of different thicknesses and different rib thicknesses and/or lengths, in particular with at least essentially the same rib thickness/length ratio, wherein in addition, these and/or other ribs of the plurality are unevenly distributed in circumferential distribution.
  • a frequency or resonance behavior and/or efficiency of the flow channel can be (further) improved.
  • n ⁇ 8, n ⁇ 7, n ⁇ 6, n ⁇ 5, n ⁇ 4, n ⁇ 3, n ⁇ 2, n ⁇ 8, n ⁇ 4, n ⁇ 2 and/or n 1 .
  • a multiplicity of n means that a rotated rib arrangement, for the first time with a rotation of 360°/n around the axis of rotation, in particular (main) machine axis, of the turbomachine, again with the unrotated rib arrangement with regard to circumferential positions of the ribs or with regard to circumferential positions and dimensions of the ribs collapse.
  • the first rib and/or the second rib in particular the first rib in which the first inner structure is arranged and/or the second rib in which the second inner structure is arranged, the structural thickness of which is smaller than the first structural thickness, (respectively) a non-deflecting outer profile, in particular in addition to or also without deviating spacing(s) in the circumferential direction or an uneven circumferential distribution of the plurality of ribs.
  • a non-deflecting outer profile is designed in such a way that it at least essentially does not change a flow of a working fluid, in particular gas, in or through the flow channel, in particular in such a way that a direction of an outflow from a downstream rear edge of the outer profile deviates by at most 5°, in particular at most 1°, from a direction of an, in particular purely axial, flow against an upstream front edge of the outer profile and/or the axial direction.
  • an angle of attack of the outer profile and/or an angle between a profile chord of the Outer profile and the axial direction (each) at most 5°, in particular at most 1°.
  • a profile curvature or maximum deviation of a skeleton line from a profile chord of the outer profile is at most 0.01, in particular at most 0.005.
  • a non-deflecting outer profile is, at least substantially, mirror-symmetrical along its longitudinal axial axis.
  • a frequency or resonance behavior and/or efficiency of the flow channel can be (further) improved.
  • One or more of the inner structures in particular the first and/or second inner structure and/or the inner structure, which, in one or the other rib, has at least one of the pairs with different distances from one another in the circumferential direction and/or at least essentially the same rib thickness/length ratio is arranged, can (each) have one or more support strut(s) and/or one or more passage(s) which are provided or set up or used for the passage of gas and/or liquid, in particular being.
  • a through-passage for the passage of gas and/or liquid has an interface, in particular a connection for the inlet and outlet of gas and/or liquid.
  • various of the inner structures can have different types of through passages, in particular be, in particular at least one of the inner structures a support strut and at least one other of the inner structures a through passage for the passage of a gas or a liquid, at least one of the inner structures a through passage for the passage of a Gas and at least one other of the internal structures a through-passage for the passage of a liquid and/or at least one of the internal structures a through-passage for the passage of a gas or a liquid and at least another of the internal structures has a through-passage for passing another gas or liquid.
  • the radially inner and outer lateral surface of the flow channel can be advantageously supported against one another by support struts, and lubricants, in particular oil, coolants, in particular air, and/or other operating resources can be advantageously guided through passages, in particular over short distances.
  • One or more of the inner structures in particular the first and/or second inner structure and/or the inner structure, which, in one or the other rib, has at least one of the pairs with different distances from one another in the circumferential direction and/or at least essentially the same rib thickness/length ratio is (respectively) arranged in whole or in part integral with the (respective) rib (respectively) in which it (are) (respectively) is (are) arranged. This applies in particular to (integrally manufactured or formed) passages.
  • one or more of the inner structures, in particular the first and/or second inner structure and/or the inner structure, which in one or the other rib can have at least one of the pairs with different distances from one another in the circumferential direction and/or are at least essentially the same Rib thickness / length ratio is (respectively) completely or partially manufactured separately from the (respective) rib or are in which it is or are arranged. This applies in particular to support struts (manufactured or formed separately).
  • through-passages can also be produced or formed separately, in particular having or being pipes, lines or the like.
  • One or more groups of (each among themselves) structurally identical (other) ribs of the plurality in the circumferential direction are unevenly distributed (each among each other) according to the invention.
  • a pitch between ribs of a group of evenly distributed ribs varies by at most 2%, in particular at most 1%.
  • a pitch between ribs of a group of unevenly distributed ribs varies by at least 5%, in particular at least 10%, with a pitch in a manner customary in the art being a, in particular minimum, maximum or average, distance in the circumferential direction between consecutive identical ribs of the respective group is.
  • At least one support strut is arranged in the ribs of at least one group of evenly distributed ribs and/or at least one through-passage for the passage of gas and/or liquid is arranged in the ribs of at least one group of unevenly distributed ribs.
  • a frequency or resonance behavior and/or efficiency of the flow channel can advantageously be (further) improved by the non-uniform distribution and at the same time a weight and/or force distribution can be (further) improved by the uniform distribution.
  • the flow duct is a so-called transition duct, which in a development connects an upstream flow cross section of the turbomachine with a radially offset downstream flow cross section of the turbomachine or is provided or set up or used for this purpose.
  • the flow or transition channel connects two compressors, in particular a high and a medium or low pressure compressor or a medium and a low pressure compressor, or two turbines, in particular a high and a medium or low pressure turbine or a medium and a low-pressure turbine of the turbomachine or is provided or set up for this purpose or is used for this purpose.
  • the turbomachine is an axial (through-flow) turbomachine, in particular a gas turbine, in particular an aircraft engine.
  • FIG. 1 shows a cross section of a transition channel according to an embodiment of the present invention with a radially outer surface 1 and a radially inner surface 2 and a plurality of ribs 11-23 with a first rib 11, a second rib 12, a third rib 13, a fourth rib 14 etc..
  • 3 a cross-section of the rib shown is screwed in, so that in 2 the outer profile A 11 of the first rib 11 and in 3 the outer profile A 12 of the second rib 12 can be seen.
  • the first rib 11 has a first rib thickness d 11 and a first rib length l 11 (cf. 2 )
  • the second rib 12 has a second rib thickness d 12 that is smaller than the first rib thickness d 11 and a second rib length l 12 that is smaller than the first rib length l 11 .
  • first rib 11 there is a first internal structure in the form of an air supply 31 which has a first structure thickness d 31
  • a second internal structure arranged in the form of a support strut 32 which has a second structural thickness d 32 which is smaller than the first structural thickness d 31 .
  • the eighth rib 18 has a rib thickness d 18 that is even smaller than the second rib thickness d 12 and a rib length l 18 (not shown) that is even smaller than the second rib length l 12 .
  • a further inner structure in the form of an oil supply 38 is arranged in the eighth rib 18 and has a structure thickness which is even smaller than the second structure thickness d 32 .
  • the first rib 11, the sixth rib 16 and the 22nd rib 22 are at least essentially identical in construction to one another.
  • the eighth and tenth ribs 18, 20 are also, at least essentially, identical in construction to one another.
  • the remaining ribs 12-15, 17, 19, 21 and 23, in particular the second rib 12 and the fourth rib 14, are also, at least essentially, identical in construction to one another.
  • an internal structure in the form of an air supply (cf. 31), support strut (cf. 32) or oil supply (cf. 38) is arranged in each of the ribs 11-23.
  • all ribs 11-23 each have a non-deflecting outer profile.
  • the rib thickness/length ratio d/l of the ribs 11-23 is, at least essentially, constant, in particular the rib thickness/length ratios d 11 /l 11 , d 12 /l 12 and d 18 /l 18 are, at least essentially, even.
  • the ribs 11-23 are distributed unevenly in the circumferential direction.
  • the distance T 12 between the first rib 11 and the second rib 12 adjacent to it and the same distances between the respective adjacent ribs (15, 16), (16, 17), (17, 18), (18, 19 ), (19, 20), (20, 21), (22, 23) and (23, 11) from the distance T 23 between the second rib 11 and the third rib 13 adjacent to it and the same distances between the respective adjacent ribs (13, 14) and (14, 15).
  • the ribs 12, 13, 14, 15, 17, 19, 21 and 23 with support struts are only present where an air or oil supply is provided, and are therefore distributed unevenly in the circumferential direction, or at the corresponding point of the circumferential division such thicker, longer or thinner, shorter ribs are omitted .
  • the ribs 12-15, 17, 19, 21 and 23 can also be unevenly distributed among one another, as indicated by a dashed rib 14' as an example.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP18209511.7A 2017-12-07 2018-11-30 Turbomaschinenströmungskanal Active EP3495629B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102017222193.3A DE102017222193A1 (de) 2017-12-07 2017-12-07 Turbomaschinenströmungskanal

Publications (2)

Publication Number Publication Date
EP3495629A1 EP3495629A1 (de) 2019-06-12
EP3495629B1 true EP3495629B1 (de) 2023-01-11

Family

ID=64564672

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18209511.7A Active EP3495629B1 (de) 2017-12-07 2018-11-30 Turbomaschinenströmungskanal

Country Status (4)

Country Link
US (1) US11098599B2 (es)
EP (1) EP3495629B1 (es)
DE (1) DE102017222193A1 (es)
ES (1) ES2936514T3 (es)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11459911B2 (en) * 2020-10-30 2022-10-04 Raytheon Technologies Corporation Seal air buffer and oil scupper system and method

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2928648A (en) * 1954-03-01 1960-03-15 United Aircraft Corp Turbine bearing support
US2941781A (en) * 1955-10-13 1960-06-21 Westinghouse Electric Corp Guide vane array for turbines
US2936999A (en) * 1956-12-07 1960-05-17 United Aircraft Corp Tangential bearing supports
US3704075A (en) 1970-12-14 1972-11-28 Caterpillar Tractor Co Combined turbine nozzle and bearing frame
DE10210866C5 (de) 2002-03-12 2008-04-10 Mtu Aero Engines Gmbh Leitschaufelbefestigung in einem Strömungskanal einer Fluggasturbine
DE102004036594A1 (de) 2004-07-28 2006-03-23 Mtu Aero Engines Gmbh Strömungsstruktur für eine Gasturbine
US20100275572A1 (en) * 2009-04-30 2010-11-04 Pratt & Whitney Canada Corp. Oil line insulation system for mid turbine frame
DE102011008812A1 (de) 2011-01-19 2012-07-19 Mtu Aero Engines Gmbh Zwischengehäuse
US20130051996A1 (en) * 2011-08-29 2013-02-28 Mtu Aero Engines Gmbh Transition channel of a turbine unit
WO2013165281A1 (en) * 2012-05-02 2013-11-07 Gkn Aerospace Sweden Ab Supporting structure for a gas turbine engine
EP2669474B1 (de) 2012-06-01 2019-08-07 MTU Aero Engines AG Übergangskanal für eine Strömungsmaschine und Strömungsmaschine
US8985277B2 (en) * 2012-07-31 2015-03-24 United Technologies Corporation Case with integral lubricant scavenge passage
PL402185A1 (pl) * 2012-12-21 2014-06-23 General Electric Company Połączona instalacja ściekowa do silników turbinowych
US10221720B2 (en) * 2014-09-03 2019-03-05 Honeywell International Inc. Structural frame integrated with variable-vectoring flow control for use in turbine systems
US9869204B2 (en) * 2015-03-06 2018-01-16 United Technologies Corporation Integrated inner case heat shield
US9982600B2 (en) * 2015-05-19 2018-05-29 United Technologies Corporation Pre-skewed capture plate
GB201512838D0 (en) * 2015-07-21 2015-09-02 Rolls Royce Plc A turbine stator vane assembly for a turbomachine

Also Published As

Publication number Publication date
US20190178095A1 (en) 2019-06-13
US11098599B2 (en) 2021-08-24
EP3495629A1 (de) 2019-06-12
DE102017222193A1 (de) 2019-06-13
ES2936514T3 (es) 2023-03-17

Similar Documents

Publication Publication Date Title
EP2824284B1 (de) Turbofan-Triebwerk
EP2179143B1 (de) Spaltkühlung zwischen brennkammerwand und turbinenwand einer gasturbinenanlage
EP2692986B1 (de) Schaufelgitter mit Seitenwandkonturierung und Strömungsmaschine
DE10210866C5 (de) Leitschaufelbefestigung in einem Strömungskanal einer Fluggasturbine
DE112015001237B4 (de) Abgasturbolader
EP2478186B1 (de) Rotor einer Turbomaschine
DE102015219556A1 (de) Diffusor für Radialverdichter, Radialverdichter und Turbomaschine mit Radialverdichter
EP0690206A2 (de) Diffusor für Turbomaschine
EP2746533B1 (de) Schaufelgitter und Strömungsmaschine
EP3121371B1 (de) Turbine mit gekühlten turbinenleitschaufeln
EP1632648B1 (de) Gasturbine mit Übergangskanal
DE10037684A1 (de) Niederdruckdampfturbine mit Mehrkanal-Diffusor
EP2669474A1 (de) Übergangskanal für eine Strömungsmaschine und Strömungsmaschine
EP3324002B1 (de) Dichtungssystem für eine turbinenstufe und axiale strömungsmaschine
DE102009040758A1 (de) Umlenkvorrichtung für einen Leckagestrom in einer Gasturbine und Gasturbine
DE102007050916A1 (de) Verfahren und Vorrichtung zum Zusammenbau von Gasturbinen-Triebwerken
EP3561228B1 (de) Schaufel, schaufelsegment und baugruppe für eine turbomaschine und turbomaschine
EP3495629B1 (de) Turbomaschinenströmungskanal
EP2607625A1 (de) Turbomaschine und Turbomaschinenstufe
EP2665896B1 (de) Zwischengehäuse einer Gasturbine mit einer aussen liegenden Begrenzungswand welche stromaufwärts einer Stützrippe eine in Umfangrichtung verändernde Kontur aufweist zur Verringerung der Sekundärströmungsverluste
EP3401503A1 (de) Rotorvorrichtung einer strömungsmaschine
DE102008031781B4 (de) Schaufelgitter für eine Strömungsmaschine und Strömungsmaschine mit einem solchen Schaufelgitter
EP3719258B1 (de) Laufschaufel einer strömungsmaschine
EP3492701B1 (de) Turbomaschinen-strömungskanal
DE10255389A1 (de) Niederdruckdampfturbine mit Mehrkanal-Diffusor

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

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

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

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

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20191212

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

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

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20200507

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

Free format text: STATUS: EXAMINATION IS IN PROGRESS

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

Free format text: STATUS: EXAMINATION IS IN PROGRESS

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20220914

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

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

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502018011400

Country of ref document: DE

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: AT

Ref legal event code: REF

Ref document number: 1543544

Country of ref document: AT

Kind code of ref document: T

Effective date: 20230215

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2936514

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20230317

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20230111

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: 20230111

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

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: 20230111

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: 20230511

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: 20230411

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: 20230111

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: 20230111

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: 20230111

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: 20230111

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: 20230111

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: 20230511

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: 20230412

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: 20230111

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502018011400

Country of ref document: DE

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

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: 20230111

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: 20230111

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: 20230111

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: 20230111

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: 20230111

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

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

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: 20230111

26N No opposition filed

Effective date: 20231012

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

Ref country code: GB

Payment date: 20231123

Year of fee payment: 6

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

Ref country code: ES

Payment date: 20231215

Year of fee payment: 6

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: 20230111

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

Ref country code: FR

Payment date: 20231122

Year of fee payment: 6

Ref country code: DE

Payment date: 20231120

Year of fee payment: 6