EP2725194A1 - Aube de rotor d'une turbine à gaz - Google Patents

Aube de rotor d'une turbine à gaz Download PDF

Info

Publication number
EP2725194A1
EP2725194A1 EP13190022.7A EP13190022A EP2725194A1 EP 2725194 A1 EP2725194 A1 EP 2725194A1 EP 13190022 A EP13190022 A EP 13190022A EP 2725194 A1 EP2725194 A1 EP 2725194A1
Authority
EP
European Patent Office
Prior art keywords
blade
overhang
suction
edge
sealing edge
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
EP13190022.7A
Other languages
German (de)
English (en)
Other versions
EP2725194B1 (fr
Inventor
Knut Dr. Lehmann
Manuel Herm
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
Rolls Royce PLC
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
Rolls Royce PLC
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
Priority claimed from GB201219267A external-priority patent/GB201219267D0/en
Priority claimed from DE201210021400 external-priority patent/DE102012021400A1/de
Application filed by Rolls Royce Deutschland Ltd and Co KG, Rolls Royce PLC filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2725194A1 publication Critical patent/EP2725194A1/fr
Application granted granted Critical
Publication of EP2725194B1 publication Critical patent/EP2725194B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade

Definitions

  • the invention relates to a turbine rotor blade of a gas turbine with a blade profile formed in the radial direction (relative to an engine axis of the gas turbine) or in the longitudinal direction of the blade and with a blade tip.
  • a blade tip is referred to in the context of the present invention, the radially outer end of the turbine rotor blade.
  • the invention furthermore relates not only to rotor blades, but also to stator blades, wherein the blade tip in the case of stator blades is defined as a radially inner end of the blade.
  • the invention has for its object to provide a turbine rotor blade of the type mentioned, which allows for a simple structure and simple, inexpensive to manufacture an optimization of the leakage mass flow and has a good component strength.
  • the blade tip has at least on its suction side, starting from a stagnation point on the blade leading edge up to an intersection of the suction-side profile line of the blade with a trailing edge circle, an overhang (winglet).
  • the overhang at the stagnation point and at the intersection with the trailing edge circle is substantially zero and reaches its maximum value at about 40% of the run length of the suction side profile line.
  • the size of the suction-side overhang (vertical distance from the suction-side profile line) reaches approximately 45% of the diameter of the maximum circle T max which can be inscribed in the blade profile.
  • the blade tip on its pressure side starting from a stagnation point on the blade leading edge to an intersection of the pressure side profile line of the blade with the trailing edge circle, also has an overhang (winglet), which at the stagnation point and is substantially zero at the intersection and which has a maximum value at about a run length between 20% and 60% of the total run length of the pressure side profile line.
  • winglet overhang
  • a peripheral sealing edge is formed at the radially outer edge region of the blade (in the case of a rotor blade) or at the radially inner edge region in the case of a stator blade.
  • This can, for example, have a substantially rectangular cross-section, so that a depression / cavity is formed in the middle region of the blade tip.
  • the sealing edge can furthermore preferably have a region with a reduced height or a region with a height of zero, which is provided in the region of the suction-side overhang between a running length of the suction-side profile line of 10% to 30%.
  • an opening is formed through which an inflow of the boundary layer close to the housing can take place on the blade tip.
  • the radial height may be between half of the blade tip gap and the triple blade tip gap.
  • the width of the sealing edge this can be formed between the triple blade tip gap and the sixfold blade tip gap.
  • the height of the overhang (winglets) in the radial direction it can be particularly favorable if this height amounts to a maximum of 10% of the radial length of the blade profile.
  • a preferred value is 5%. This means that about 90% to 95% of the blade profile is formed unchanged and that only the outer 10 or 5% of the length of the blade profile is provided with the overhang or winglet according to the invention.
  • edge region of the overhang (winglets) at the radial end at an angle.
  • This angle is defined in a plane spanned by a radial vector from the sealing edge to the engine axis and a vector normal to the sealing edge. The angle then forms between a tangent to the outer sealing edge surface and the radial vector.
  • the gas turbine engine 10 is a generalized example of a turbomachine, in which the invention can be applied.
  • the engine 10 is formed in a conventional manner and comprises in succession an air inlet 11, a fan 12 circulating in a housing, a medium pressure compressor 13, a high pressure compressor 14, a combustion chamber 15, a high pressure turbine 16, a medium pressure turbine 17 and a low pressure turbine 18 and a Exhaust nozzle 19, which are all arranged around a central engine axis 1.
  • the intermediate pressure compressor 13 and the high pressure compressor 14 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, that radially inwardly from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude.
  • the compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and mid pressure turbine 17, respectively.
  • the turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine rotor blades 24 projecting outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the blades 22 disposed thereon and the turbine rotor hub 27 and the turbine rotor blades 24 disposed thereon rotate about the engine axis 1 during operation.
  • the Fig. 2 shows an end view of an embodiment of a turbine rotor blade according to the invention 24. It is understood that the frontal Surface is not flat, but part of a cylinder jacket around the engine axis 1. To simplify the illustration, the end surface is in each case flat in the following figures.
  • the Fig. 2 thus shows an inventive design of the rotor blade tip in plan view.
  • a feature of the invention the special shape of the suction-side overhang 30.
  • the inventive design of the suction-side overhang 30 is by means of Fig. 8 and 10 described in more detail.
  • the winglet overhang T w (s) is defined as a thickness distribution, ie as a vertical distance to the suction-side blade profile line.
  • the thickness distribution with the maximum profile thickness T max of the blade tip is made dimensionless.
  • the thickness distribution in Fig. 10 especially advantageous.
  • the thickness distribution is close to 0 (no significant overhang 30 is present).
  • the overhang 30 increases only very slowly along s.
  • two further thickness distributions (dashed lines shown), which thus narrow an area for the particularly advantageous design of the suction-side overhang 30.
  • a blade profile 29 is shown as a dashed line, this line corresponds to the blade profile under the winglet 30 at 90% of the blade height.
  • Line 38 shows the contour of the suction-side overhang ( Fig. 8 ) while the line 39 the contour of the pressure-side overhang ( Fig. 9 ) shows.
  • the reference numeral 31 indicates the circle which can be inscribed in the region of the maximum thickness of the cross section of the blade profile 29.
  • the reference numeral 32 shows the trailing edge circle.
  • the edge of the overhang 30 is formed in the form of a sealing edge 33, which is carried out substantially circumferentially. It has, as will be described below, an opening 34 ( FIGS. 12 and 13 ). While in Fig. 8 the suction-side overhang is shown and explained in detail, shows the Fig. 9 the pressure-side overhang with its contour 39.
  • the Fig. 4 to 7 each show sectional views along the in Fig. 3 shown cutting lines.
  • the thicknesses of the overhangs on the suction side and the pressure side are in the 10 and 11 shown.
  • the course is in each case applied over a dimensionless running length s, which extends from the stagnation point on the blade leading edge LE along the suction or pressure-side profile line to the intersection of the profile line with the trailing edge circle TE.
  • the size of the overhang T w (s) is normalized to the diameter of the maximum circle T max which can be inscribed in the blade profile. It follows at which points in each case the maximum values are provided particularly favorable.
  • the dashed lines in the 10 and 11 show a preferred design range, while the solid line represents an optimized solution.
  • FIG. 12 to 15 again gives a representation of the flow conditions.
  • the Fig. 13 shows in particular an inflow through the opening 34 and a flow through the blade tip gap 37. Accordingly, the FIGS. 14 and 15 for clarity, an example of a blade tip-splitting vortex 41 forming as well as a secondary flow vortex 42.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13190022.7A 2012-10-26 2013-10-24 Aube de rotor d'une turbine à gaz Active EP2725194B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB201219267A GB201219267D0 (en) 2012-10-26 2012-10-26 Turbine blade
DE201210021400 DE102012021400A1 (de) 2012-10-31 2012-10-31 Turbinenrotorschaufel einer Gasturbine

Publications (2)

Publication Number Publication Date
EP2725194A1 true EP2725194A1 (fr) 2014-04-30
EP2725194B1 EP2725194B1 (fr) 2020-02-19

Family

ID=49448046

Family Applications (2)

Application Number Title Priority Date Filing Date
EP13190022.7A Active EP2725194B1 (fr) 2012-10-26 2013-10-24 Aube de rotor d'une turbine à gaz
EP13190039.1A Active EP2725195B1 (fr) 2012-10-26 2013-10-24 Aube rotorique de turbine et étage rotorique associé

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP13190039.1A Active EP2725195B1 (fr) 2012-10-26 2013-10-24 Aube rotorique de turbine et étage rotorique associé

Country Status (2)

Country Link
US (2) US10641107B2 (fr)
EP (2) EP2725194B1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3043715A1 (fr) * 2015-11-16 2017-05-19 Snecma Aube de turbine comprenant une pale avec baignoire comportant un intrados incurve dans la region du sommet de pale
EP3421725A1 (fr) * 2017-06-26 2019-01-02 Siemens Aktiengesellschaft Aube de compresseur
WO2019035800A1 (fr) * 2017-08-14 2019-02-21 Siemens Aktiengesellschaft Aubes de turbine

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2725194B1 (fr) 2012-10-26 2020-02-19 Rolls-Royce Deutschland Ltd & Co KG Aube de rotor d'une turbine à gaz
US9638041B2 (en) 2013-10-23 2017-05-02 General Electric Company Turbine bucket having non-axisymmetric base contour
US20150110617A1 (en) * 2013-10-23 2015-04-23 General Electric Company Turbine airfoil including tip fillet
US9797258B2 (en) 2013-10-23 2017-10-24 General Electric Company Turbine bucket including cooling passage with turn
US9551226B2 (en) 2013-10-23 2017-01-24 General Electric Company Turbine bucket with endwall contour and airfoil profile
US9528379B2 (en) 2013-10-23 2016-12-27 General Electric Company Turbine bucket having serpentine core
US9670784B2 (en) 2013-10-23 2017-06-06 General Electric Company Turbine bucket base having serpentine cooling passage with leading edge cooling
US20150345301A1 (en) * 2014-05-29 2015-12-03 General Electric Company Rotor blade cooling flow
US10508549B2 (en) * 2014-06-06 2019-12-17 United Technologies Corporation Gas turbine engine airfoil with large thickness properties
EP2977548B1 (fr) * 2014-07-22 2021-03-10 Safran Aero Boosters SA Aube et turbomachine associée
EP2977549B1 (fr) * 2014-07-22 2017-05-31 Safran Aero Boosters SA Aubage de turbomachine axiale et turbomachine associée
EP2987956A1 (fr) * 2014-08-18 2016-02-24 Siemens Aktiengesellschaft Aube de compresseur
US9995166B2 (en) 2014-11-21 2018-06-12 General Electric Company Turbomachine including a vane and method of assembling such turbomachine
US20160245095A1 (en) * 2015-02-25 2016-08-25 General Electric Company Turbine rotor blade
US10107108B2 (en) 2015-04-29 2018-10-23 General Electric Company Rotor blade having a flared tip
US10253637B2 (en) * 2015-12-11 2019-04-09 General Electric Company Method and system for improving turbine blade performance
FR3055698B1 (fr) * 2016-09-08 2018-08-17 Safran Aircraft Engines Procede de controle de la conformite du profil d'une surface courbe d'un element d'une turbomachine
JP6871770B2 (ja) * 2017-03-17 2021-05-12 三菱重工業株式会社 タービン動翼、及びガスタービン
EP3477059A1 (fr) * 2017-10-26 2019-05-01 Siemens Aktiengesellschaft Surface portante de compresseur
GB201719538D0 (en) * 2017-11-24 2018-01-10 Rolls Royce Plc Gas turbine engine
US11118462B2 (en) * 2019-01-24 2021-09-14 Pratt & Whitney Canada Corp. Blade tip pocket rib
US11066935B1 (en) 2020-03-20 2021-07-20 General Electric Company Rotor blade airfoil
US11371359B2 (en) 2020-11-26 2022-06-28 Pratt & Whitney Canada Corp. Turbine blade for a gas turbine engine
US20230349299A1 (en) * 2022-04-28 2023-11-02 Hamilton Sundstrand Corporation Additively manufactures multi-metallic adaptive or abradable rotor tip seals

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1491556A (en) * 1974-02-02 1977-11-09 Mtu Muenchen Gmbh Rotor blades for turbomachines
EP1898052A2 (fr) * 2006-08-21 2008-03-12 General Electric Company Extrémité évasée d'aube de turbine

Family Cites Families (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US711832A (en) 1902-06-26 1902-10-21 Lester C Denison Adjustable side bearing for cars.
US1955929A (en) * 1932-03-18 1934-04-24 Voith Gmbh J M Impeller
GB793143A (en) 1956-05-17 1958-04-09 Daimler Benz Ag Improvements relating to axial-flow compressors
US3706512A (en) 1970-11-16 1972-12-19 United Aircraft Canada Compressor blades
GB1366024A (en) 1972-11-28 1974-09-04 Levy J Colouring process for photographic prints
US4424001A (en) * 1981-12-04 1984-01-03 Westinghouse Electric Corp. Tip structure for cooled turbine rotor blade
US4761116A (en) * 1987-05-11 1988-08-02 General Electric Company Turbine blade with tip vent
US5503527A (en) 1994-12-19 1996-04-02 General Electric Company Turbine blade having tip slot
GB9607578D0 (en) 1996-04-12 1996-06-12 Rolls Royce Plc Turbine rotor blades
US6422821B1 (en) 2001-01-09 2002-07-23 General Electric Company Method and apparatus for reducing turbine blade tip temperatures
GB2409006B (en) 2003-12-11 2006-05-17 Rolls Royce Plc Tip sealing for a turbine rotor blade
GB2413160B (en) * 2004-04-17 2006-08-09 Rolls Royce Plc Turbine rotor blades
EP1591624A1 (fr) 2004-04-27 2005-11-02 Siemens Aktiengesellschaft Aube de compresseur et compresseur
GB0503185D0 (en) * 2005-02-16 2005-03-23 Rolls Royce Plc A turbine blade
FR2885645A1 (fr) * 2005-05-13 2006-11-17 Snecma Moteurs Sa Aube creuse de rotor pour la turbine d'un moteur a turbine a gaz, equipee d'une baignoire
CA2675151A1 (fr) 2006-01-13 2007-07-19 Eth Zurich Pale de turbine a pointe renfoncee
US20070237627A1 (en) 2006-03-31 2007-10-11 Bunker Ronald S Offset blade tip chord sealing system and method for rotary machines
US7740445B1 (en) * 2007-06-21 2010-06-22 Florida Turbine Technologies, Inc. Turbine blade with near wall cooling
GB0724612D0 (en) 2007-12-19 2008-01-30 Rolls Royce Plc Rotor blades
CN101255873B (zh) 2008-02-28 2010-06-09 大连海事大学 压气机动叶叶尖小翼
CN101255800B (zh) 2008-02-28 2010-06-09 大连海事大学 涡轮或汽轮机动叶叶尖小翼
GB0813556D0 (en) 2008-07-24 2008-09-03 Rolls Royce Plc A blade for a rotor
GB0815957D0 (en) 2008-09-03 2008-10-08 Rolls Royce Plc Blades
GB201006450D0 (en) 2010-04-19 2010-06-02 Rolls Royce Plc Blades
GB201006449D0 (en) * 2010-04-19 2010-06-02 Rolls Royce Plc Blades
GB201006451D0 (en) * 2010-04-19 2010-06-02 Rolls Royce Plc Blades
US8944774B2 (en) * 2012-01-03 2015-02-03 General Electric Company Gas turbine nozzle with a flow fence
EP2725194B1 (fr) * 2012-10-26 2020-02-19 Rolls-Royce Deutschland Ltd & Co KG Aube de rotor d'une turbine à gaz
US20140241899A1 (en) * 2013-02-25 2014-08-28 Pratt & Whitney Canada Corp. Blade leading edge tip rib
US20150110617A1 (en) * 2013-10-23 2015-04-23 General Electric Company Turbine airfoil including tip fillet
DE102013224998A1 (de) * 2013-12-05 2015-06-11 Rolls-Royce Deutschland Ltd & Co Kg Turbinenrotorschaufel einer Gasturbine und Verfahren zur Kühlung einer Schaufelspitze einer Turbinenrotorschaufel einer Gasturbine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1491556A (en) * 1974-02-02 1977-11-09 Mtu Muenchen Gmbh Rotor blades for turbomachines
EP1898052A2 (fr) * 2006-08-21 2008-03-12 General Electric Company Extrémité évasée d'aube de turbine

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3043715A1 (fr) * 2015-11-16 2017-05-19 Snecma Aube de turbine comprenant une pale avec baignoire comportant un intrados incurve dans la region du sommet de pale
WO2017085387A1 (fr) * 2015-11-16 2017-05-26 Safran Aircraft Engines Aube de turbine de turbomachine, turbine et turbomachine associées
GB2560124A (en) * 2015-11-16 2018-08-29 Safran Aircraft Engines Turbine engine turbine vane, and related turbine and turbine engine
US10753215B2 (en) 2015-11-16 2020-08-25 Safran Aircraft Engines Turbine vane comprising a blade with a tub including a curved pressure side in a blade apex region
GB2560124B (en) * 2015-11-16 2022-04-13 Safran Aircraft Engines Turbine vane comprising a blade with a tub including a curved pressure side in a blade apex region
EP3421725A1 (fr) * 2017-06-26 2019-01-02 Siemens Aktiengesellschaft Aube de compresseur
WO2019001979A1 (fr) * 2017-06-26 2019-01-03 Siemens Aktiengesellschaft Profil aérodynamique de compresseur
CN110869584A (zh) * 2017-06-26 2020-03-06 西门子股份公司 压气机翼型
RU2728549C1 (ru) * 2017-06-26 2020-07-30 Сименс Акциенгезелльшафт Аэродинамический профиль компрессора
US11391164B2 (en) 2017-06-26 2022-07-19 Siemens Energy Global GmbH & Co. KG Compressor aerofoil
CN110869584B (zh) * 2017-06-26 2022-10-11 西门子能源环球有限责任两合公司 压气机翼型
WO2019035800A1 (fr) * 2017-08-14 2019-02-21 Siemens Aktiengesellschaft Aubes de turbine

Also Published As

Publication number Publication date
US10641107B2 (en) 2020-05-05
EP2725195B1 (fr) 2019-09-25
EP2725194B1 (fr) 2020-02-19
US20140119920A1 (en) 2014-05-01
EP2725195A1 (fr) 2014-04-30
US9593584B2 (en) 2017-03-14
US20140119942A1 (en) 2014-05-01

Similar Documents

Publication Publication Date Title
EP2725194B1 (fr) Aube de rotor d'une turbine à gaz
DE60017541T2 (de) Schaufelblatt für eine axiale Turbomaschine
EP1478828B1 (fr) Structure de recirculation de turbocompresseurs
EP1609999B1 (fr) Turbo machine
DE602004006323T2 (de) Verfahren zur Herstellung einer Turbine mit Turbinenschaufeln unterschiedlicher Resonanzfrequenzen samt einer solchen Turbine
EP2025945B1 (fr) Machine de traitement des écoulements dotée d'un creux de paroi de canal de ceinture
EP2242931B1 (fr) Structure d'écoulement pour turbocompresseur
DE69423789T2 (de) Stroemungsleiteinrichtung fuer den kompressorteil einer stroemungsmaschine
EP1530670B1 (fr) Structure de recirculation d'un turbocompresseur
EP2802780B1 (fr) Ventilateur axial ou diagonal avec arête de détente sur l'extrados de l'aube
EP2138727B1 (fr) Bande de recouvrement d'aube dotée d'un passage
EP2877701B1 (fr) Rotor d'un turbocompresseur
EP2696029B1 (fr) Grille d'aube avec définition de contour de la paroi latérale et turbomachine
EP2669474B1 (fr) Canal de passage pour une turbomachine et turbomachine
EP2496794B1 (fr) Turbomachine à compression ou expansion axiale
EP1614863A1 (fr) Structure de fluide d'un turbocompresseur
EP2881541A1 (fr) Refroidissement de pointe d'aube d'un aube de rotor de turbine à gaz
EP3121373B1 (fr) Roue de turbine refroidie, plus particulièrement pour un réacteur
DE102007020025A1 (de) Form eines Gaskanals in einer Axialströmungs-Gasturbinenmaschine
EP1759090A1 (fr) Aube comportant une zone de transition
DE10330084A1 (de) Rezirkulationsstruktur für Turboverdichter
DE102015224283A1 (de) Leitschaufelcluster für eine Strömungsmaschine
EP2846000B1 (fr) Roue statorique d'une turbine à gaz
EP2059655A1 (fr) Aube mobile refroidie pour turbines
DE102015203871A1 (de) Rotor einer Turbine einer Gasturbine mit verbesserter Kühlluftführung

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: 20131024

AK Designated contracting states

Kind code of ref document: A1

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

AX Request for extension of the european patent

Extension state: BA ME

17P Request for examination filed

Effective date: 20141027

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

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ROLLS-ROYCE PLC

Owner name: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

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: 20190820

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

RIN1 Information on inventor provided before grant (corrected)

Inventor name: HERM, MANUEL

Inventor name: LEHMANN, KNUT, DR.

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

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

Owner name: ROLLS-ROYCE PLC

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

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

Owner name: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

Owner name: ROLLS-ROYCE PLC

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: 502013014307

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1235187

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200315

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: NL

Ref legal event code: MP

Effective date: 20200219

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

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: 20200219

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: 20200519

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: 20200219

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: 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: 20200619

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: 20200519

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: 20200520

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: 20200219

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: 20200219

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: 20200219

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: 20200219

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

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: 20200219

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: 20200219

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: 20200219

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: 20200219

Ref country code: ES

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

Effective date: 20200219

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: 20200219

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: 20200712

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: 20200219

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: 20200219

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502013014307

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

26N No opposition filed

Effective date: 20201120

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: 20200219

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: 20200219

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: 20200219

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Effective date: 20201024

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

Ref country code: LU

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

Effective date: 20201024

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: 20200219

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20201031

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: 20201024

Ref country code: LI

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

Effective date: 20201031

Ref country code: CH

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

Effective date: 20201031

Ref country code: BE

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

Effective date: 20201031

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: 20201024

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1235187

Country of ref document: AT

Kind code of ref document: T

Effective date: 20201024

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: 20201024

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: 20200219

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: 20200219

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: 20200219

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: 20200219

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: 20200219

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

Effective date: 20230528

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

Ref country code: FR

Payment date: 20231026

Year of fee payment: 11

Ref country code: DE

Payment date: 20231027

Year of fee payment: 11