EP3584413B1 - Ringförmiges und aufgeschrumpftes gussteil für ein turbotriebwerk eines luftfahrzeugs - Google Patents

Ringförmiges und aufgeschrumpftes gussteil für ein turbotriebwerk eines luftfahrzeugs Download PDF

Info

Publication number
EP3584413B1
EP3584413B1 EP19180983.9A EP19180983A EP3584413B1 EP 3584413 B1 EP3584413 B1 EP 3584413B1 EP 19180983 A EP19180983 A EP 19180983A EP 3584413 B1 EP3584413 B1 EP 3584413B1
Authority
EP
European Patent Office
Prior art keywords
flange
extraction
holes
annular
screws
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
EP19180983.9A
Other languages
English (en)
French (fr)
Other versions
EP3584413A1 (de
Inventor
Etienne Gérard Joseph CANELLE
Jacques Marcel Arthur Bunel
Faouzi ALIOUAT
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 EP3584413A1 publication Critical patent/EP3584413A1/de
Application granted granted Critical
Publication of EP3584413B1 publication Critical patent/EP3584413B1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • 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
    • F05D2230/70—Disassembly methods
    • 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
    • F05D2260/31—Retaining bolts or nuts
    • 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
    • F05D2260/37—Retaining components in desired mutual position by a press fit connection

Definitions

  • the present invention relates to an annular casting and shrink-wrapped part of an aircraft turbomachine.
  • the state of the art includes in particular the documents EP-A1-3 048 270 , WO-A1-2016 / 051080 and EP-B1-1 931 859 .
  • An aircraft turbomachine comprises several annular parts, such as, for example, casings, abradable coating supports, etc., which are coaxial and extend around the longitudinal axis of the turbomachine, which is generally coincident with the axis of rotation of its main rotor or of its main rotors.
  • the abradable housings and supports must be well centered and sealed against each other. For this, they are mounted hooped with each other. This is particularly important for abradable mounts which provide a seal between moving and stationary parts of the engine.
  • a turbomachine can be made by foundry.
  • the foundry operation requires the presence of specific protruding studs on the parts which have a dual function. These studs first serve as a reference for checking the part after manufacture, and also serve during the manufacture of the part. These studs must therefore be kept during the life of the part. They are however relatively bulky and should ideally be located on the workpiece flange to meet the needs of the foundry.
  • one of the shrink-wrapped flanges must include extraction sleeves as well as notches for the passage of extraction sleeves from another flange on which this flange is shrunk.
  • the present invention provides a simple, efficient and economical solution to this problem.
  • the invention relates to a part for a turbomachine, this part having a general annular shape around an axis of revolution, this part comprising a first annular flange for fixing by shrinking and comprising an annular row of screw holes, this part part being produced by foundry and comprising projecting studs necessary for the control and production of the part by casting, characterized in that said studs are located on said flange and each comprise a tapping configured to cooperate with an extraction screw of the flange.
  • the invention is advantageous because it makes it possible to integrate the function of the extraction bushings of the prior art into the foundry pads.
  • the part therefore does not need extraction bushings strictly speaking, which frees space on its fixing flange by shrinking.
  • the pads thus have a dual function.
  • the invention also relates to an assembly comprising a part as described above, and a first annular element extending around said axis, the first flange of the part being shrunk and applied axially against a second annular flange of this first element of so that the threads of said studs are aligned with through holes of the second flange, these holes having a diameter smaller than that of said threads.
  • the present invention also relates to an aircraft turbomachine, comprising a part or an assembly as described above.
  • the extraction screw used in step c) may include the stopper and an extension having a predetermined length L1 which is configured to pass through the threads and part of the holes.
  • the stopper and the extension have a total predetermined length L2.
  • the figure 1 is a partial schematic view of a turbomachine and more exactly of a rear or downstream portion of the turbomachine, the upstream and downstream expressions taking account of the flow of gases in the turbomachine.
  • the gases flow from a fan inside a nacelle towards the interior and around a gas generator which successively comprises low pressure and high pressure compressors, a combustion chamber, high pressure and low pressure turbines, and a gas ejection nozzle.
  • references 10, 12 and 14 respectively denote an annular abradable coating support, an annular bearing support, and an internal casing of the high pressure turbine.
  • the support 10 has a generally cylindrical shape in the example shown and carries an abradable annular coating 16 at its downstream end.
  • the support 10 comprises at its upstream end a first flange 18.
  • the flange 18 comprises two radial faces, respectively upstream 18a and downstream 18b, and a radially internal cylindrical surface 18c for shrinking.
  • the face 18a and the surface 18c are connected to each other.
  • the support 12 has a generally frustoconical shape flared upstream in the example shown, and is here surrounded by the support 10. It comprises at its upstream end a second flange 20.
  • the flange 20 comprises two radial faces, respectively upstream 20a. and downstream support 20b, as well as two cylindrical bearing surfaces, respectively upstream 20c and downstream 20d, for shrinking.
  • the face 20a and the bearing 20c are connected together, and the face 20b and the bearing 20d are connected together ( figure 4 ).
  • the casing 14 has a generally frustoconical shape flared towards the downstream in the example shown and comprises at its upstream end a third flange 22.
  • the flange 22 comprises two radial faces, respectively downstream 22b and upstream 22a support, and a surface radially internal cylindrical hooping 22c.
  • the face 22b and the surface 22c are connected to each other ( figure 4 ).
  • the flanges 18, 20 and 22 comprise aligned holes for the passage of fixing screws 24 whose heads 24a bear for example on the downstream radial face 18b of the first flange 18, and whose threaded bodies receive nuts 24b which bear on the upstream radial face 22a of the third flange 22 ( figure 4 ).
  • the flanges 18, 20, 22 are shrink-wrapped, that is to say they are fixed together by radial clamping one on the other.
  • the part intended to be fixed on another part is heated to expand it and facilitate its engagement on the other part. As it cools, the part retracts and tightens radially against the other part.
  • the flange 18 is shrunk by its surface 18c on the surface 20d of the flange 20, and the flange 22 is shrunk by its surface 22c on the surface 20c of the flange 20.
  • the flange 20 is interposed between the flanges 18, 22 and its radial faces 20a, 20b bear on the flanges 22, 18 respectively and therefore does not include any projections.
  • one of the other parts such as for example the support 10 is produced from a foundry and comprises on its downstream radial face 18b projecting studs 26 (visible at figure 3 ) which are necessary for checking the part and for manufacturing the part.
  • the pads 26 have a general parallelepipedal shape in the example shown.
  • these flanges must be equipped with extraction means, that is to say means capable of generating a sufficient axial separation force between two parts in order to to extract them from one another by defrosting them.
  • these extraction means comprise attached bushings 28, visible at the figure 2 .
  • These bushes 28 are mounted crimped in holes of a flange and receive screws which are intended to bear on a flange adjacent to the flange carrying the bushes, so as to apply the aforementioned separation force.
  • the flange which carries the studs 26 does not include extraction bushings 28 because the function of these bushings is integrated into the plots.
  • the studs 26 indeed include threads 30 for screwing the extraction screw, as can be seen in figure 3 .
  • the threads 30 are through and threaded to cooperate with the extraction screws which are intended to bear on at least one of the other flanges 20, 22 of the assembly.
  • the threads 30 are oriented axially, that is to say parallel to the axis of revolution and assembly of the parts.
  • the extraction screws are screwed from downstream into the threads 30 in the example shown.
  • FIGS. 5a to 5e illustrate disassembly steps of a first embodiment of a method according to the invention, only the support 10 being disassembled and therefore separated from the other two parts (support 12 and casing 14).
  • Each extraction screw 32 has a generally cylindrical shape and comprises a threaded body 32b, one longitudinal end of which is connected to a drive head 32c and of which an opposite longitudinal end comprises an axial extension 32a having a diameter smaller than that of the body.
  • the flange 20 comprises through holes 34 aligned with the threads 30 of the flange 18. These holes 34 are not threaded and have an internal diameter smaller than that of the threads 30, and between the diameter of the extension 32a and the diameter of the body 32b of the screw 32. It is also noted that each thread 30 is connected to a hole 34 by an annular cavity 36 which is located at the interface between the flanges 18, 20. This cavity 36 has a diameter greater than the diameters of the hole 34 and of the thread 30 and comprises a half-portion formed by a hollow on the downstream radial face 20b of the flange 20 and another half-portion formed by a hollow on the upstream radial face 18a of the flange 18 ( figure 4 ).
  • the flange 22 comprises blind holes 38 aligned with the holes 34 and the internal threads 30. These holes 38 are not threaded and here have an internal diameter greater than the internal diameter of the holes 34.
  • the threads 30 are for example three in number regularly distributed around the axis of the support 10. It is therefore understood that the flange 20 in this case comprises three holes 34 and that the flange 22 comprises three holes 38.
  • Each screw 32 is first aligned with the axis of an internal thread 30 and then engaged by its extension 32a in this internal thread 30 ( figures 5a and 5b ).
  • the screw is screwed into the thread by means of a suitable tool in engagement with the drive head 32c, until the extension 32a engages the hole 34 and the end of the body 32b connected to the extension rest on the bottom of the hollow of the downstream radial face 20b of the flange 20 ( figures 5c and 5d ).
  • extension 32a has a length L1 less than the thickness E of the flange 20 (and more exactly, L1 is less than the thickness E 'remaining between the bottom of the forming hollow of the cavity 36 on the face 20b, and the opposite face 20a - figure 5d ) and does not risk coming into contact with the flange 22 during screwing. It is further understood that, for the sole removal of support 10, this extension 32a is not compulsory since it has no particular utility during this extraction.
  • FIG. 6a to 6h illustrate another embodiment of the method according to the invention which here consists in extracting the flanges 18, 22 from the flange 20 and therefore in completely disassembling the assembly.
  • the same screw 32 is used but is here equipped with a stop 40 which is removably mounted on the extension 32a.
  • This stopper has a generally cylindrical shape and is axially aligned with the extension 32a and the body 32b of the screw, the external diameter of this stopper being similar to that of the extension and therefore smaller than that of the body.
  • the total length L2 of the stop 40 and of the extension 32a is greater than the thickness E (E ') of the flange 20 so that the stop and the extension can be engaged in the hole 34 and pass through it. .
  • Each screw 32 is first aligned with the axis of an internal thread 30 then engaged by its extension 32a in this internal thread 30 ( figures 6a and 6b ). The screw is screwed into the tapping until the stop 40 and the extension 32a engage in the hole 34 and this stop rests on the bottom of the blind hole 38 of the downstream radial face 22b of the flange 22 ( figures 6c and 6d ).
  • the screw 32 is screwed again into the tapping 30 until the end of the body 32b connected to the extension 32a bears on the downstream radial face 20b of the flange 20 ( figures 6g ).

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Clamps And Clips (AREA)

Claims (15)

  1. Teil (10) für eine Turbomaschine, wobei dieses Teil eine allgemeine ringförmige Form um eine Drehachse aufweist, wobei dieses Teil einen ersten ringförmigen Befestigungsflansch (18) durch Aufschrumpfung beinhaltet und eine ringförmige Reihe von Schraubendurchführungsöffnungen (24) beinhaltet, wobei dieses Teil durch Guss gefertigt ist und vorragende Stifte (26) umfasst, die zur Kontrolle und zur Fertigung des Teils durch Guss erforderlich sind, dadurch gekennzeichnet, dass die Stifte auf dem Flansch gelegen sind und jeweils ein Innengewinde (30) umfassen, das konfiguriert ist, um mit einer Abdrückschraube (32) des Flansches zusammenzuwirken.
  2. Teil (10) nach Anspruch 1, wobei das Teil eine abschleifbare ringförmige Beschichtung (16) trägt.
  3. Teil (10) nach Anspruch 1 oder 2, wobei der Flansch (18) eine erste radiale Auflageseite (18a) auf einem anderen Flansch (20) und eine zylindrische radial innere Aufschrumpfungsseite (18c) auf einem zylindrischen radial äußeren Umfang (20d) dieses anderen Flansches umfasst.
  4. Teil (10) nach Anspruch 3, wobei die Stifte (26) auf einer zweiten radialen Seite (18b), die der ersten radialen Auflageseite (18a) gegenüberliegt, vorragen.
  5. Anordnung, ein Teil (10) nach einem der vorstehenden Ansprüche und ein erstes ringförmiges Element (12) beinhaltend, das sich um die Achse erstreckt, wobei der erste Flansch (18) des Teils (10) aufgeschrumpft ist und axial an einem zweiten ringförmigen Flansch (20) dieses ersten Elements (12) derart angelegt ist, dass die Innengewinde (30) der Stifte (26) mit den Durchgangslöchern (34) des zweiten Flansches ausgerichtet sind, wobei diese Löcher einen Durchmesser kleiner als derjenige der Innengewinde aufweisen.
  6. Anordnung nach Anspruch 5, wobei sie ein zweites ringförmiges Element (14) umfasst, das sich um die Achse erstreckt und einen dritten Flansch (22) beinhaltet, der aufgeschrumpft ist und axial an dem zweiten Flansch (20), auf der dem ersten Flansch (18) gegenüberliegenden Seite, derart angelegt ist, dass die Innengewinde (30) und die Durchgangslöcher (34) mit den Sacklöchern (38) des dritten Flansches ausgerichtet sind, wobei diese Sacklöcher einen Durchmesser größer als derjenige der Durchgangslöcher aufweisen.
  7. Anordnung nach Anspruch 5 oder 6, wobei die Durchgangslöcher (34) und/der die Sacklöcher (38) ohne Innengewinde sind.
  8. Anordnung nach einem der Ansprüche 5 bis 7, wobei das erste Element eine Lagerstütze (12) ist und/oder das zweite Element ein Turbinengehäuse (14) ist.
  9. Anordnung nach einem der Ansprüche 5 bis 8, dadurch gekennzeichnet, dass sie einen ringförmigen Hohlraum (36) umfasst, der an der Schnittstelle zwischen dem ersten Flansch (18) und dem zweiten Flansch (20) gelegen ist, und der Hohlraum (36) konfiguriert ist, um jedes Innengewinde (30) der Stifte (26) mit dem Loch (34) des zweiten Flansches (20) zu verbinden.
  10. Anordnung nach Anspruch 9, dadurch gekennzeichnet, dass der Hohlraum (36) einen hohlen Halbabschnitt auf einer stromabwärtigen radialen Seite (20b) des zweiten Flansches (20) und einen anderen hohlen Halbabschnitt auf der ersten radialen Auflageseite (18a) des ersten Flansches (18) umfasst.
  11. Anordnung nach einem der Ansprüche 5 bis 10, dadurch gekennzeichnet, dass der zweite Flansch (20) eine vorbestimmte Dicke E aufweist, die dazu vorgesehen ist, größer als eine Länge L1 einer Verlängerung (32a) der Schraube (32) zu sein.
  12. Turbomaschine eines Flugzeugs, die ein Teil nach einem der Ansprüche 1 bis 4 oder eine Anordnung nach einem der Ansprüche 5 bis 8 beinhaltet.
  13. Verfahren zum Aausbau eines Teils (10) in einer Anordnung nach einem der Ansprüche 5 bis 8, die folgenden Schritte beinhaltend:
    a) Einführen einer Abdrückschraube (32) in das Innengewinde (30) jedes der Stifte (26) des Teils,
    b) Verschrauben der Abdrückschrauben in den Innengewinden, bis ihre freien Enden auf dem zweiten Flansch (20) zum Aufliegen kommen,
    c) Fortsetzen des Verschraubens der Abdrückschrauben derart, dass das Anzugsdrehmoment der Schraube eine Abdrückkraft des Teils in Bezug auf den zweiten Flansch und auf das erste Element (12) erzeugt,
    d) Abnehmen des Teils (10).
  14. Verfahren nach Anspruch 10, weiter beinhaltend
    - vor dem Schritt a),
    einen Schritt des (i) Anbringens eines Anschlags (40) am freien Ende jeder der Abdrückschrauben (32) derart, dass sie verlängert werden,
    - zwischen den Schritten a) und c), die folgenden Schritte
    (ii) Verschrauben der Abdrückschrauben in den Innengewinden (30), bis die Anschläge auf dem dritten Flansch (22) zum Aufliegen kommen,
    (iii) Fortsetzen des Verschraubens der Abdrückschrauben derart, dass das Anzugsdrehmoment eine Abdrückkraft des Teils und des ersten Elements (12) in Bezug auf den dritten Flansch (22) und auf das zweite Element (14) erzeugt,
    (iv) Abnehmen des Teils (10) und des ersten Elements (12).
  15. Verfahren nach Anspruch 14, dadurch gekennzeichnet, dass die im Schritt c) verwendete Abdrückschraube (32) den Anschlag (40) und eine Verlängerung (32a) umfasst, die eine vorbestimmte Länge L1 aufweist, die konfiguriert ist, um die Innengewinde (30) und einen Anteil der Löcher (34) zu durchqueren; und dadurch, dass der Anschlag (40) und die Verlängerung (32a) eine vorbestimmte Gesamtlänge L2 aufweisen.
EP19180983.9A 2018-06-20 2019-06-18 Ringförmiges und aufgeschrumpftes gussteil für ein turbotriebwerk eines luftfahrzeugs Active EP3584413B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1855461A FR3082874B1 (fr) 2018-06-20 2018-06-20 Piece annulaire de fonderie et frettee d'une turbomachine d'aeronef

Publications (2)

Publication Number Publication Date
EP3584413A1 EP3584413A1 (de) 2019-12-25
EP3584413B1 true EP3584413B1 (de) 2020-07-22

Family

ID=63080151

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19180983.9A Active EP3584413B1 (de) 2018-06-20 2019-06-18 Ringförmiges und aufgeschrumpftes gussteil für ein turbotriebwerk eines luftfahrzeugs

Country Status (3)

Country Link
US (1) US10920619B2 (de)
EP (1) EP3584413B1 (de)
FR (1) FR3082874B1 (de)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10961869B2 (en) * 2019-03-19 2021-03-30 Raytheon Technologies Corporation Concentric jack screw holes
FR3107550B1 (fr) * 2020-02-24 2022-01-28 Safran Aircraft Engines Procede de montage d’un module de turbomachine d’aeronef
US11174754B1 (en) * 2020-08-26 2021-11-16 Solar Turbines Incorporated Thermal bridge for connecting sections with a large temperature differential under high-pressure conditions
FR3127783B1 (fr) * 2021-10-04 2023-08-25 Safran Aircraft Engines Dispositif de contrôle de placage inter-bride

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4098125A (en) * 1977-03-30 1978-07-04 Lee Thomas E Adjustable volume pipetting device
US5961807A (en) * 1997-10-31 1999-10-05 General Electric Company Multipart electrical seal and method for electrically isolating a metallic projection
US6199453B1 (en) * 1998-04-28 2001-03-13 Steinbock Machinery Co. High temperature bolting system
JP2001107922A (ja) * 1999-10-08 2001-04-17 Mitsubishi Heavy Ind Ltd フランジレスケーシングの締結構造
US6959509B2 (en) * 2002-08-26 2005-11-01 George Vais Quick change infinitely adjustable barrel nut assembly
WO2007040430A1 (en) 2005-10-06 2007-04-12 Frenolink Förvaltnings AB Lifting sling system
EP1931859B1 (de) * 2005-10-06 2012-11-07 Alstom Technology Ltd Leitschaufel-anordnung einer strömungsmaschine
US7730715B2 (en) * 2006-05-15 2010-06-08 United Technologies Corporation Fan frame
US7464496B1 (en) * 2006-05-26 2008-12-16 Davies Robert B Heat exchanger barrel nut
US9175568B2 (en) * 2010-06-22 2015-11-03 Honeywell International Inc. Methods for manufacturing turbine components
US8961125B2 (en) * 2011-12-13 2015-02-24 United Technologies Corporation Gas turbine engine part retention
EP3084310A4 (de) * 2013-12-19 2017-01-04 United Technologies Corporation Gasturbinenmotorwandanordnung mit umlaufender schienenbolzenarchitektur
FR3026331B1 (fr) * 2014-09-30 2016-11-11 Snecma Douille d'extraction
US9879565B2 (en) * 2015-01-20 2018-01-30 United Technologies Corporation Enclosed jacking insert
US9909610B2 (en) * 2015-12-17 2018-03-06 Honeywell International Inc. Heat resistant fastening systems
US10961860B2 (en) * 2016-08-15 2021-03-30 Raytheon Technologies Corporation Non-contact seal with removal features
US10583913B2 (en) * 2017-03-14 2020-03-10 General Electric Company Stud push out mount for a turbine engine spinner assembly having a spinner push out stud joint connecting through a counterbore of a spinner bolt hole
US10895170B2 (en) * 2018-10-22 2021-01-19 Raytheon Technologies Corporation Shear wave resistant flange assembly

Non-Patent Citations (1)

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

Also Published As

Publication number Publication date
FR3082874B1 (fr) 2020-09-04
US10920619B2 (en) 2021-02-16
US20190390571A1 (en) 2019-12-26
EP3584413A1 (de) 2019-12-25
FR3082874A1 (fr) 2019-12-27

Similar Documents

Publication Publication Date Title
EP3584413B1 (de) Ringförmiges und aufgeschrumpftes gussteil für ein turbotriebwerk eines luftfahrzeugs
CA2473335C (fr) Dispositif perfectionne de fixation d'un arbre de moteur sur un support de palier
EP2657558B1 (de) Flexibles Kopplungsmittel und mechanische Übertragung
EP2678531B1 (de) Fanrotor und zugehöriges Turbostrahltriebwerk
FR2943313A1 (fr) Helice non carenee a pales a calage variable pour une turbomachine
EP3610136B1 (de) Vorrichtung zum zentrieren und drehführen einer turbomaschinenwelle mit mittel zur axialen rückhaltung des aussenringes eines lagers
EP3074611A1 (de) Vorrichtung zur zentrierung und führung der rotation einer turbinenmotorwelle mit verbessertem mittel zum zurückhalten des äusseren lagerrings
EP2705256A1 (de) Turbomaschinenrotor mit mittel zur axialbefestigung der schaufeln
FR2991386A1 (fr) Turbomachine comportant des moyens de fixation amont d'un tube de deshuilage
FR2982907A1 (fr) Systeme mecanique pour turbomachine, turbomachine et procede de fixation d'un systeme mecanique dans une turbomachine
FR3005693A1 (fr) Turbomachine d'aeronef a double flux comprenant une virole inter-veine a maintien aval simplifie
WO2018020170A1 (fr) Ensemble de turbomachine comprenant un cône avant et une virole avant
FR2949138A1 (fr) Turbomachine comportant des moyens d'anti-rotation d'un ecrou de palier
WO2014037653A1 (fr) Rotor de soufflante, en particulier pour une turbomachine
FR2921422A1 (fr) Piece annulaire de turbomachine portant des ecrous a jupe de sertissage
EP4034752B1 (de) Anordnung für einen turbinenmotor
FR3018313B1 (fr) Ligne d'arbres creux pour turbomachine d'aeronef, comprenant une bague anti-rotation couplee a un ecrou de serrage interieur
EP4090833A1 (de) Anordnung für einen turbinenmotor
BE1029274B1 (fr) Groupe d’aubes statoriques
FR3082228A1 (fr) Piece de turbomachine comprenant une rondelle cooperant avec un lamage
WO2022106237A1 (fr) Arbre de ligne d'entraînement de turbomoteur d'aéronef comprenant une bague de liaison pour le démontage de la ligne d'entraînement
FR3119646A1 (fr) Rotor de turbomachine
FR2974865A1 (fr) Rotor haute pression pour turbomachine d'aeronef, comprenant des moyens de detrompage associes a des boulons de prefixation de module de turbine
FR3105981A1 (fr) Jonc d’assemblage pour turbomachine
FR3037998A1 (fr) Ensemble pour turbomachine d'aeronef comprenant un carter de turbine ainsi qu'un dispositif de refroidissement par air, et procede d'assemblage d'un tel ensemble

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: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20190618

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

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

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 25/24 20060101AFI20200131BHEP

Ipc: F01D 25/16 20060101ALI20200131BHEP

INTG Intention to grant announced

Effective date: 20200221

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: 602019000310

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1293576

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200815

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: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1293576

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200722

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

Ref country code: ES

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

Effective date: 20200722

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: 20201022

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: 20200722

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: 20201023

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: 20200722

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: 20200722

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: 20201022

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: 20201123

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: 20200722

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

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: 20200722

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: 20200722

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: 20200722

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: 20201122

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: 20200722

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602019000310

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: 20200722

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: 20200722

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: 20200722

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: 20200722

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: 20200722

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: 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: 20200722

26N No opposition filed

Effective date: 20210423

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: 20200722

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20200722

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: 20200722

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20210630

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: 20210618

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: 20210618

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: 20210630

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: LI

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

Effective date: 20220630

Ref country code: CH

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

Effective date: 20220630

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

Ref country code: CY

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

Effective date: 20200722

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

Ref country code: HU

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

Effective date: 20190618

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

Ref country code: IT

Payment date: 20230523

Year of fee payment: 5

Ref country code: FR

Payment date: 20230523

Year of fee payment: 5

Ref country code: DE

Payment date: 20230523

Year of fee payment: 5

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

Ref country code: SE

Payment date: 20230523

Year of fee payment: 5

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: 20200722

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

Ref country code: GB

Payment date: 20230523

Year of fee payment: 5

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: 20200722