EP3973146B1 - Abnehmbarer stift an einer turbomaschinendüse - Google Patents

Abnehmbarer stift an einer turbomaschinendüse Download PDF

Info

Publication number
EP3973146B1
EP3973146B1 EP20720100.5A EP20720100A EP3973146B1 EP 3973146 B1 EP3973146 B1 EP 3973146B1 EP 20720100 A EP20720100 A EP 20720100A EP 3973146 B1 EP3973146 B1 EP 3973146B1
Authority
EP
European Patent Office
Prior art keywords
head
abutment
casing
assembly according
flange
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
EP20720100.5A
Other languages
English (en)
French (fr)
Other versions
EP3973146A1 (de
Inventor
Paul Jean-Jacques Michel REVERSEAU
Didier Pierre FABRE
Sabrina BENKACI
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.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3973146A1 publication Critical patent/EP3973146A1/de
Application granted granted Critical
Publication of EP3973146B1 publication Critical patent/EP3973146B1/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
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2250/12—Two-dimensional rectangular
    • 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
    • F05D2250/13—Two-dimensional trapezoidal
    • F05D2250/131—Two-dimensional trapezoidal polygonal
    • 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
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to an assembly for a turbomachine. More specifically, the invention relates to the architecture of a turbine and in particular the mounting support for a distributor in a high-pressure turbine.
  • the published patent document FR 3 066 226 A1 discloses in its figure 1 a high-pressure turbine distributor, mounted on an annular casing.
  • the distributor comprises a platform supporting an annular row of stationary vanes.
  • An annular row of pins (denoted 22) allows the circumferential and radial positioning of a flange of the platform to a flange of the housing.
  • a stop (denoted 21) completes the connection between the distributor and the casing, the stop axially maintaining the flanges bearing against each other. The stop rests radially on a support ring (denoted 3).
  • removing the distributor requires removing the stopper and removing the stopper can only be done by removing the support ring, fixed to the casing.
  • the object of the invention is to propose a design for the coupling of the distributor and the high-pressure turbine casing which allows faster maintenance operations, and in particular aimed at eliminating the dismantling of the support ring and of the crankcase.
  • the subject of the invention is an assembly for a turbomachine, comprising: a turbine nozzle comprising an annular platform, an internal radial flange extending radially inwards from the platform, and one or more vanes extending radially outside from the platform; a housing including an outer radial flange; and a stop providing axial retention of the outer radial flange in contact with the inner radial flange; remarkable in that the abutment is formed of a head and a body assembled in a removable manner to the head.
  • the invention also relates to a turbomachine comprising a combustion chamber, the turbomachine being characterized in that it comprises a high-pressure turbine downstream of the combustion chamber, the turbine being equipped with an assembly according to one of the embodiments set forth above.
  • the invention finally relates to a method for maintaining a turbomachine, noteworthy in that the turbomachine is according to the embodiment of the preceding paragraph and in that the method comprises, in this order: a step of removing the body of the stopper; and a step of removing the distributor, during which the head of the abutment remains engaged in the casing and the support ring remains fixed to the casing, the method also preferably comprising a step of reassembling the distributor then a step of fixing the body of the stop on the head of the stop.
  • the measures of the invention are interesting in that only part of the abutment is to be detached from the casing to allow dismantling of the distributor. The assembly of the casing and the support ring is thus preserved. Moreover, as in operation the abutment is not subjected to significant forces, the assembly of the two parts of the abutment can be done by simple means of the quick fastening type.
  • the terms “internal” (or “inner”) and “external” (or “outer”) refer to a positioning relative to the axis of rotation of an axial turbomachine which is also the axis of rotation of the turbine.
  • the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
  • the radial direction is perpendicular to the axis of rotation. Upstream and downstream refer to the main flow direction of the stream in the turbomachine.
  • integral is understood as integral in rotation, and in particular rigidly linked.
  • one-piece is equivalent to “made from material” and designates different elements made from the same block of material, as opposed to “attached” which means that an element is attached, after its manufacture, to another element.
  • the figures represent the elements schematically, in particular without all of the assembly or sealing elements. Certain dimensions of the elements drawn, and in particular their radial thicknesses, are exaggerated in order to facilitate understanding of the figures.
  • distributedor is meant a set of circumferentially adjacent angular sectors and forming an annular row of stationary vanes, each of the sectors possibly comprising at least one, for example two or three stationary vanes.
  • the figure 1 schematically represents an axial turbomachine 2.
  • the turbojet engine 2 comprises a low-pressure compressor 4 and a high-pressure compressor 6, a combustion chamber 8 and one or more turbines 9.
  • the mechanical power of the turbine 9 transmitted to the rotor 12 sets in motion the two compressors 4 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator blades. The rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to gradually compress the latter until it enters the combustion chambers 8.
  • a fan 16 is coupled to the rotor 12 and generates an air flow which is divided into a primary flow 18 and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the turbine outlet.
  • Reduction means such as an epicyclic reducer 22, can reduce the speed of rotation of the fan and/or of the low-pressure compressor with respect to the associated turbine.
  • the secondary flow can be accelerated so as to generate a thrust reaction necessary for the flight of an aircraft.
  • the turbine or turbines 9 comprise alternating rotating blades and stationary blades.
  • the term "distributor” will be used to refer to a set of stationary vanes and their support platform.
  • the platform can be an entire ring or a circumferential segment (partial ring).
  • the first distributor downstream of the combustion chambers 8 is indicated by the number 10 on the figure 1 . It is followed by an 11 wheel.
  • the picture 2 is a sectional view partially representing a stage of the turbine 9 according to a known construction.
  • the stage of the turbine 9 is composed of a distributor 10 and an impeller 11.
  • the wheel 11 comprises an annular row of moving blades 110 each mounted in a cell 111 of a disc 112.
  • the distributor 10 comprises an annular row of stationary vanes 101 connected by their internal ends (foot) to a lower platform 102, which is annular.
  • Platform 102 has a flange 103 extending radially inward. This flange 103 makes it possible to make the vanes 101 integral with the annular casing 30, fixed.
  • the blades 101, 110 extend radially in the hot and high pressure air stream 18.
  • the casing 30 comprises an internal spindle 301, an external spindle 302, an external radial flange 303 and an internal radial flange 304.
  • the spindles 301, 302 are coaxial along the axis 14.
  • the outer radial flange 303 is in axial contact with the inner flange 103, the flange 303 being downstream of the flange 103.
  • the flanges 103, 303 are positioned and held radially and circumferentially together by means of pins 32, distributed angularly around of the axis 14.
  • the pins 32 extend axially through the flanges 103, 303.
  • Pin 32 visible in the section of the picture 2 extends along an axis denoted A, parallel to axis 14.
  • a stop 34 This stop extends radially along an axis denoted B.
  • the axes A and B are represented on the picture 2 to facilitate understanding of the invention, but these axes are not in the same plane, the abutment 34 being circumferentially offset with respect to the pins 32.
  • the abutment 34 extends through an orifice 305 provided in the housing 30.
  • a seal 36 housed in the flange 303 prevents air leaks from the vein 18 to the inside.
  • the stop 34 is radially supported by a support ring 40.
  • the support ring 40 is assembled to the casing 30 at its internal flange 304 by screws (not shown) extending along the axis C.
  • support 40 is also radially supported by the internal spindle 301 of the casing 30.
  • the support ring 40 can rest on a lip 306 of the casing 30.
  • the support ring 40 is provided with a layer of abradable 50 to ensure sealing by cooperating with wipers 62 of a rotating flange 60, integral with wheel 11.
  • the picture 2 illustrates the assembly in its assembled state.
  • the abutment 34 can only be removed from the housing 30 after disassembly of the support ring 40.
  • the object of the invention is to reduce the number of dismantling steps required to remove the distributor.
  • the picture 3 shows a partial sectional view of an assembly according to the invention. Pieces similar to the known set shown in figure 2 retain their reference numbers. The invention essentially differs from the known assembly by the design of the abutment.
  • the abutment is referenced 70.
  • This consists of a head 72 and a body 78.
  • the head 72 comprises an internal portion 74 and an external portion 76 which passes through the orifice 305 of the housing 30.
  • the internal portion 74 has a dimension (diameter if it is a cylinder or diagonal if it is a polygon) which is greater than the diameter of the orifice 305 so that the internal portion 74 does not enter the orifice 305.
  • head 72 is supported via its internal portion 74 by the support ring 40, fixed to the crankcase 30.
  • the head 72 is assembled in a removable manner to the body 78.
  • the head 72 and the body 78 are separable from each other, reversibly.
  • the head does not pass through the casing. She is received in accommodation provided for this purpose.
  • the head is welded to the casing or tightly mounted in its housing, so as to remain integral with the casing during dismantling of the body.
  • the body 78 is adapted to be in contact with the flange 103 to prevent the axial separation of the flanges 103, 303.
  • the body radially overlaps the internal flange 103.
  • radial overlap it is meant that geometric points of the body 78 have radial coordinates identical to that of geometric points of the flange 103.
  • the head 72 is at a radial distance from the internal flange 103 in order to allow, once the body 78 has been removed, the axial sliding of the distributor 10 upstream (to the left on the picture 3 ).
  • the figure 4 illustrates an exemplary embodiment of the stop 70.
  • the head 72 comprises in this example an internal thread 761 in which engages a threaded portion 781 of the body 78.
  • the body 78 may have a portion facilitating its gripping for unscrewing purposes , such as a portion with a square section 782.
  • body 78 and outer portion 76 of head 72 have generally axisymmetric shapes around axis B.
  • the figure 4 also partially shows the lip 306 of the casing which is close to the internal portion 74.
  • the figure 5 illustrates the internal portion 74 seen along the V:V direction defined in figure 4 . It shows the substantially polygonal section 741 of the inner portion 74, which in this example is a square.
  • the square 741 can have rounded corners 742.
  • In dotted line is represented a position of the internal portion 74 in contact with the lip 306. Indeed, during the unscrewing of the body 78 blindly - that is to say without maintaining or having access to the head 72 of the stop 70 -, if the internal portion 74 has a polygonal section, the latter can pivot and come to rest on a surface to be stopped in rotation and allow the unscrewing of the body 78 without that the internal portion 74 does not “rotate in a vacuum”.
  • the stopping surface is a surface of the lip 306.
  • the rotation of the internal portion 74 can be stopped by the internal flange 304 of the housing or by a surface of the support ring 40.
  • the contact surface between the support ring 40 and the abutment 70 can also stop the head 72 in rotation: for example, the support ring 40 can be provided with grooves and the internal portion 74 can be equipped with grooves (radial with respect to axis B) which can engage in the grooves.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (10)

  1. Eine Turbomaschinenbaugruppe (2), die Folgendes umfasst:
    - einen Verteiler (10) einer Turbine (9) mit einer ringförmigen Plattform (102), einem inneren radialen Flansch (103), der sich von der Plattform (102) radial nach innen erstreckt, und einer oder mehreren Schaufeln (101), die sich von der Plattform (102) radial nach außen erstrecken;
    - ein Gehäuse (30) mit einem radial äußeren Flansch (303); und
    - einen Anschlag (70), der eine axiale Beibehaltung des radial äußeren Flansches (303) in Kontakt mit dem inneren radialen Flansch (103) sicherstellt;
    dadurch gekennzeichnet, dass der Anschlag (70) einen Kopf (72) und einen Körper (78) umfasst, der abnehmbar auf dem Kopf (72) angebracht ist.
  2. Die Baugruppe nach Anspruch 1, dadurch gekennzeichnet, dass der Kopf (72) und der Körper (78) jeweils ein Innengewinde (761) und der Körper (78) und der Kopf (72) jeweils ein mit dem Innengewinde (761) kompatibles Außengewinde (781) umfassen.
  3. Die Baugruppe nach Anspruch 1, dadurch gekennzeichnet, dass der Körper (78) und der Kopf (72) durch einen Bajonettmechanismus zusammengefügt sind.
  4. Die Baugruppe nach Anspruch 1, dadurch gekennzeichnet, dass der Körper (78) und der Kopf (72) fest zusammengefügt sind.
  5. Die Baugruppe nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass der Kopf (72) radial von den Flanschen (103, 303) entfernt ist.
  6. Die Baugruppe nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass der Kopf (72) T-förmig ist und einen inneren Teil (74) mit polygonalem Querschnitt (741) und einen achsensymmetrischen äußeren Teil (76) aufweist.
  7. Die Baugruppe nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass der Kopf (72) durch das Gehäuse (30) verläuft.
  8. Die Baugruppe nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass der Anschlag (70) sich in radialer Richtung erstreckt und Stifte (32) sich axial erstrecken, wobei jeder der Stifte (32) durch den Flansch (303) des Gehäuses (30) und den Flansch (103) des Verteilers (10) verläuft.
  9. Eine Turbomaschine (2) mit einer Brennkammer (8), wobei die Turbomaschine (2) dadurch gekennzeichnet ist, dass sie eine Hochdruckturbine (9) stromabwärts der Brennkammer (8) umfasst, wobei die Turbine (9) mit einer Baugruppe nach einem der Ansprüche 1 bis 8 ausgestattet ist.
  10. Verfahren zur Wartung einer Turbomaschine (2), dadurch gekennzeichnet, dass die Turbomaschine (2) dem Anspruch 9 entspricht und dass das Verfahren aus den folgenden Schritten in dieser Reihenfolge besteht:
    - einen Schritt der Demontage des Körpers (78) des Anschlags (70); und
    - einen Schritt der Demontage des Verteilers (10), wobei der Kopf (72) des Anschlags (70) in das Gehäuse (30) eingesetzt bleibt und der Stützring (40) an dem Gehäuse (30) befestigt bleibt,
    wobei das Verfahren ferner vorzugsweise einen Schritt des Wiedereinbaus des Verteilers (10) und dann einen Schritt des Festklemmens des Körpers (78) des Anschlags (70) an dem Kopf (72) des Anschlags (70) umfasst.
EP20720100.5A 2019-05-21 2020-04-27 Abnehmbarer stift an einer turbomaschinendüse Active EP3973146B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1905298A FR3096397B1 (fr) 2019-05-21 2019-05-21 Pion amovible sur distributeur de turbomachine
PCT/EP2020/061624 WO2020233947A1 (fr) 2019-05-21 2020-04-27 Pion amovible sur distributeur de turbomachine

Publications (2)

Publication Number Publication Date
EP3973146A1 EP3973146A1 (de) 2022-03-30
EP3973146B1 true EP3973146B1 (de) 2022-12-21

Family

ID=67384146

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20720100.5A Active EP3973146B1 (de) 2019-05-21 2020-04-27 Abnehmbarer stift an einer turbomaschinendüse

Country Status (5)

Country Link
US (1) US11603775B2 (de)
EP (1) EP3973146B1 (de)
CN (1) CN113811669A (de)
FR (1) FR3096397B1 (de)
WO (1) WO2020233947A1 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3117147B1 (fr) * 2020-12-09 2022-10-28 Safran Aircraft Engines Ensemble statorique de turbine avec degré de liberté radial entre un distributeur et un anneau d’étanchéité

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB715086A (en) * 1953-02-06 1954-09-08 Rolls Royce Improvements relating to separable joints
US4883405A (en) * 1987-11-13 1989-11-28 The United States Of America As Represented By The Secretary Of The Air Force Turbine nozzle mounting arrangement
US5201846A (en) * 1991-11-29 1993-04-13 General Electric Company Low-pressure turbine heat shield
US5441385A (en) * 1993-12-13 1995-08-15 Solar Turbines Incorporated Turbine nozzle/nozzle support structure
FR2743603B1 (fr) * 1996-01-11 1998-02-13 Snecma Dispositif de jonction de segments d'un distributeur circulaire a un carter de turbomachine
US5848874A (en) * 1997-05-13 1998-12-15 United Technologies Corporation Gas turbine stator vane assembly
JP2001082103A (ja) * 1999-09-09 2001-03-27 Toshiba Corp 蒸気タービン用ノズルダイアフラム
RU2260700C2 (ru) * 2003-11-24 2005-09-20 Открытое акционерное общество "Авиадвигатель" Сопловой аппарат турбины газотурбинного двигателя
FR2935428B1 (fr) * 2008-08-26 2015-06-26 Snecma Aubage fixe de turbomachine a masse reduite et turbomachine comportant au moins un tel aubage fixe
FR2935429B1 (fr) * 2008-08-26 2011-11-25 Snecma Aubage fixe de turbomachine a masse reduite et turbomachine comportant au moins un tel aubage fixe
FR2960591B1 (fr) * 2010-06-01 2012-08-24 Snecma Dispositif pour caler en rotation un segment de distributeur dans un carter de turbomachine ; pion antirotation
GB201016597D0 (en) * 2010-10-04 2010-11-17 Rolls Royce Plc Turbine disc cooling arrangement
CN202545489U (zh) * 2012-04-16 2012-11-21 虞有华 多用途中空膨胀螺栓
FR2995003B1 (fr) * 2012-09-03 2014-08-15 Snecma Rotor de turbine pour une turbomachine
FR3022944B1 (fr) * 2014-06-26 2020-02-14 Safran Aircraft Engines Ensemble rotatif pour turbomachine
DE102014214703A1 (de) * 2014-07-25 2016-01-28 Siemens Aktiengesellschaft Vorrichtung zum Ausrichten eines Leitschaufelträgers zu einem Gehäuse einer Turbine
FR3062876B1 (fr) * 2017-02-14 2021-03-12 Safran Aircraft Engines Compresseur haute pression pour turbomachine
FR3066226B1 (fr) 2017-05-10 2020-07-17 Safran Aircraft Engines Verrouillage anneau stator sous distributeur haute pression

Also Published As

Publication number Publication date
EP3973146A1 (de) 2022-03-30
US11603775B2 (en) 2023-03-14
US20220195891A1 (en) 2022-06-23
FR3096397A1 (fr) 2020-11-27
FR3096397B1 (fr) 2021-04-16
CN113811669A (zh) 2021-12-17
WO2020233947A1 (fr) 2020-11-26

Similar Documents

Publication Publication Date Title
CA2794837C (fr) Helice non carenee pour turbomachine
EP2694781B1 (de) Dichtring für eine turbinenstufe einer flugzeugturbomaschine mit geschlitzten drehschutzzapfen
EP3617452B1 (de) Kupplung für strömungsmaschine, zugehörige turbine und strömungsmaschine
FR3029960A1 (fr) Roue a aubes avec joint radial pour une turbine de turbomachine
WO2012056161A1 (fr) Ensemble de disques de rotor pour une turbomachine
EP3973146B1 (de) Abnehmbarer stift an einer turbomaschinendüse
EP2762681B1 (de) Rotortrommel einer axialen Turbomaschine und zugehörige Turbomaschine
WO2019243484A1 (fr) Virole extérieure de turbomachine
FR3071868B1 (fr) Bras pour carter de turbomachine comprenant un corps et une piece amovible
EP3690192B1 (de) Rotor für einen kompressor einer axialen turbomachine
EP3751102B1 (de) Rotor für den kompressor einer rotationsmaschine und zugehöriges fertigungsverfahren
EP3382242B1 (de) Bürstendichtung für rotor einer turbomaschine
EP4143421A1 (de) Gehäuse mit zwischenflussglättung mit monoblockstrukturarm
EP3382155B1 (de) Dichtungssystem für eine strömungsmaschine, und zugehörige strömungsmaschine
EP3935273B1 (de) Gegenläufige gasturbine für ein flugzeug
EP4034752B1 (de) Anordnung für einen turbinenmotor
EP3553322B1 (de) Einheit für ein axiales turbotriebwerk mit einem zweiteiligen aussenring
EP3715638B1 (de) Hybridrotor mit einem aussenmantel, der an der ringgförmigen verbundwand anliegt
WO2022171957A1 (fr) Procede de reparation d'une bride de rotor de turbomachine
FR3050718A1 (fr) Helice pour turbomachine d'aeronef comprenant des moyens simplifies de retention radiale de pale d'helice
WO2016034804A1 (fr) Ensemble rotatif muni d'un dispositif de calage

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: UNKNOWN

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

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

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: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20211208

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

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

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
INTG Intention to grant announced

Effective date: 20220701

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: 602020007092

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1539169

Country of ref document: AT

Kind code of ref document: T

Effective date: 20230115

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

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: 20221221

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: 20221221

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: 20230321

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: 20221221

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: 20221221

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

Ref country code: FR

Payment date: 20230321

Year of fee payment: 4

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1539169

Country of ref document: AT

Kind code of ref document: T

Effective date: 20221221

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: 20221221

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: 20221221

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: 20221221

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: 20230322

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: 20221221

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: 20221221

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: 20221221

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: 20230421

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: 20221221

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: 20221221

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: 20221221

Ref country code: AT

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

Effective date: 20221221

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

Ref country code: DE

Payment date: 20230321

Year of fee payment: 4

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: 20221221

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: 20221221

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: 20230421

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: 20221221

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602020007092

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

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

Ref country code: DK

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

Effective date: 20221221

26N No opposition filed

Effective date: 20230922

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: LU

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

Effective date: 20230427

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20230430

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: 20221221

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: 20221221

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: 20221221

Ref country code: LI

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

Effective date: 20230430

Ref country code: CH

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

Effective date: 20230430

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: BE

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

Effective date: 20230430

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: 20230427

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: 20230427

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

Ref country code: GB

Payment date: 20240320

Year of fee payment: 5