EP2204546B1 - Leitschaufelstufe eines Verdichters, entsprechender Verdichter und Verfahren zur Sicherung von Schaufeln in einer solchen Leitschaufelstufe - Google Patents

Leitschaufelstufe eines Verdichters, entsprechender Verdichter und Verfahren zur Sicherung von Schaufeln in einer solchen Leitschaufelstufe Download PDF

Info

Publication number
EP2204546B1
EP2204546B1 EP08172916A EP08172916A EP2204546B1 EP 2204546 B1 EP2204546 B1 EP 2204546B1 EP 08172916 A EP08172916 A EP 08172916A EP 08172916 A EP08172916 A EP 08172916A EP 2204546 B1 EP2204546 B1 EP 2204546B1
Authority
EP
European Patent Office
Prior art keywords
ring
openings
blade
stator stage
accordance
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
EP08172916A
Other languages
English (en)
French (fr)
Other versions
EP2204546A1 (de
Inventor
Enrique Penalver Castro
Yves Culot
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 Aero Boosters SA
Original Assignee
Techspace Aero SA
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 Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP08172916A priority Critical patent/EP2204546B1/de
Priority to AT08172916T priority patent/ATE548542T1/de
Priority to CA2688607A priority patent/CA2688607C/en
Priority to US12/644,101 priority patent/US8764392B2/en
Publication of EP2204546A1 publication Critical patent/EP2204546A1/de
Application granted granted Critical
Publication of EP2204546B1 publication Critical patent/EP2204546B1/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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49947—Assembling or joining by applying separate fastener

Definitions

  • the invention relates to a rectifier stage of an axial turbomachine compressor, more particularly to a rectifier stage coming directly downstream of the inlet fan of a turbojet or turbine engine compressor.
  • the invention also relates to a compressor comprising such a rectifier and to a blade retention method of a rectifier stage of an axial turbine engine compressor, more particularly to a rectifier stage coming directly downstream of the fan. the input of a turbojet or turbine engine compressor.
  • the first stage turbojet or turbine engine rectifier must meet particular requirements with respect to the resistance of the blades to the impact or intrusion of a foreign body. Indeed, turbojets and turbine engines are likely to suck in flight different types of foreign bodies such as ice or birds.
  • the fan at the head of the machine is sized to withstand this kind of stress, but the fact remains that this type of foreign body may not be destroyed sufficiently by the fan to pass through the machine without causing other damage.
  • the rectifier stage directly downstream of the blower can also be subject to damage by this type of foreign body.
  • the blades of this stage can be deformed by the impact of the foreign body and potentially become detached especially at the level of the inner shell.
  • a detachment of a blade would cause the turbomachine very significant damage in comparison with a foreign body of the type mentioned above and must be prevented.
  • the fixing of the blades of the rectifier stage to the outer shell is usually made by welding, riveting or screwing.
  • This type of connection is quite rigid and resistant in comparison with the connection with the inner shell which is generally ensured by embedding and flooding the end of the blade in a damping material. It is therefore necessary to use locking systems at the foot of the blade.
  • the document GB 700.012 discloses a principle of attaching stator vanes to an outer shell and also to an inner shell where the ends of the vanes are inserted into respective slots in the inner and outer shells and where a hook wire is passed through openings in the ends of the blades.
  • This document does not specify the length of the wire and specifies how the wire is inserted into the openings. It appears from the teaching of this document that the insertion of the wire into the openings of several successive blades must be made very difficult because of the rigidity of the wire and the small clearance provided between the wire and the orifices.
  • the document GB 732,919 discloses a principle of stator vane attachment similar to that of the previous document.
  • the blade heads are inserted into respective slots of the stator and a latch wire is inserted into openings of the projecting blade heads.
  • the openings are spaced from the slots and the wire is held by a sheet rigidly fixed to the stator and folded over the wire.
  • the vanes may further be spot welded to the sheet in question.
  • This document does not specify the length of the wire or the number of blades held by a section of wire. Nor does it specify how the ends of adjacent wires are joined. It is however clear that the wire is held in place by the folding of the sheet metal ends extending between the blades.
  • the insertion of the wire into the openings of several successive blades must be made very difficult because of the rigidity of the wire and the small clearance provided between the wire and the orifices.
  • the document EP 1 213 484 B1 also discloses a similar principle of attaching blade heads and feet to the outer and inner rings where a strip or strip is inserted into corresponding openings of the blade heads and feet.
  • binding principles of these documents are limited to a lock, that is to say to prevent the release of a head or a blade root of its respective slot. They also require a final step of fixing the wire or the strip.
  • the object of the invention is to propose a principle of retention of the vanes of a rectifier stage which overcomes the aforementioned problems.
  • the invention consists of a rectifying stage of an axial turbomachine compressor, comprising an outer shell and an inner shell, both concentric; a series of blades arranged radially and fixed at their heads to the outer shell and at their feet to the inner shell, the inner shell comprising a series of openings each receiving the foot of a blade projecting from the inner face the inner ferrule, each blade root having at least one opening projecting from the inner face of the inner ferrule; wherein a spiral ring comprising at least two turns is housed in the openings so as to prevent the blade roots from protruding respective openings of the inner ferrule and so as to form a connection between the blade roots.
  • This arrangement has the advantage of ensuring the dual function of locking the blades relative to the inner ring and maintain the blades together while being particularly easy to implement. Indeed, the spiral ring will hold the blades and will be able to deform by sliding of its spirals with respect to each other. The installation requires no special tools and no closing operation of the ring is necessary.
  • the turns of the ring touch when the ring is at rest.
  • the turns of the ring are in pressure against each other when the ring is at rest.
  • the ring is made of metallic material, preferably spring steel.
  • the turns of the ring describe at least two complete turns.
  • the diameter of the ring at rest essentially corresponds to the diameter of the circle passing through the openings of the blade roots so that the ring is floating in the openings when it is in place.
  • the diameter of the ring at rest is slightly less than the diameter of the circle passing through the openings of the blade roots, preferably between 92 and 98%, so that the ring is in tension when it is in place. .
  • the blade roots comprise two rows of openings spaced from each other, each opening row receiving a respective spiral ring.
  • the openings of the blade roots are circular.
  • the circularity of the openings makes it possible to produce them in a simple manner, for example by simple drilling.
  • the invention also relates to an axial compressor comprising a fan at the compressor head and directly downstream of the fan a rectifier stage according to one of the preceding claims.
  • step a) comprises fixing the blade heads to an outer shell, and the diameter of the ring at rest essentially corresponds to the diameter of the circle passing through the openings of the blade roots so that the ring is floating in the openings when in place.
  • step a) comprises the attachment of the blade heads to an outer shell, and the diameter of the ring at rest is slightly less than the diameter of the circle passing through the openings of the blade roots, preferably between 92 and 98 %, so that the ring is in tension when in place.
  • FIG. figure 1 A turbojet axial compressor stator section is illustrated in FIG. figure 1 .
  • This is the rectifier intended to be placed directly downstream of the blower at the compressor inlet. It is composed of an outer shell 1, an inner shell 2 and a series of blades 3 arranged radially between the outer shell and the inner shell.
  • the blades 3 are rigidly fixed to the outer shell 1 via their heads 4. This attachment is made by welding, riveting, screwing or other means of attachment.
  • the inner ends or feet 5 of the blades 3 are inserted into openings or slots 7 (see figure 2 ) are practiced in the inner shell 2. The blades are free to slide in these openings.
  • the feet 5 of the blades 3 protruding from the inner ferrule are provided with holes or openings in which a spiral ring 6 or 6 'is inserted so as to lock the vanes in the inner ferrule and also to bind all vanes between them.
  • the figure 2 which is a bottom view of an inner ferrule section of the figure 1 further details the connection.
  • Slots or openings 7 are made in the inner shell 2 so that each slot receives the inner end 5 of a projecting blade.
  • Each projecting blade root has two holes or openings 8 and 8 '. Due to the constant position of the holes on the blades and the geometric arrangement of the blades, the holes 8, 8 'form two parallel circles.
  • a spiral ring 6, 6 ' is housed in each series of holes 8 and 8' forming a circle so as to lock the vanes with respect to the inner ferrule and to bind the blades together. As can be seen in the figure 2 each ring 6, 6 'is spiral and has two spirals.
  • the rings are of elastic material, preferably of spring steel, and formed so that the turns are in pressure on each other when they are at rest.
  • This type of ring may correspond to the rings marketed under the name Spirolox® and commonly used in mechanics as a stop ring on tree or boring grooves. In view of the large required diameter and other functional requirements, it is possible and even probable that such a ring is not available as a standard article and that it must be made to measure.
  • the supply may be provided in the form of a coil of the desired diameter and a large number of turns, from which the desired number of turns is cut.
  • the ends of the cut ring should then be rounded with a grinding wheel or other suitable tool.
  • a comfortable mechanical clearance is provided between the openings 8, 8 'and the section of the ring 6, 6' so as to make the mounting operation sufficiently easy.
  • the game will be, for example, of the order of 5% to 60%, more particularly of the order of 10% to 30% at the respective sections of the openings and the ring.
  • the installation is done as follows.
  • One end of the ring is detached from the neighboring turn and is inserted into a first hole 8 or 8 'of a blade and then into the following holes so as to thread the ring gradually, turn by turn, in the series of holes forming a circle. To do this the end must describe as many turns through the holes as there are turns in the ring.
  • the ring Once the other end of the ring is engaged in the holes, the ring returns to its original shape, namely that its different turns remain in contact with each other thus forming a compact and stable ring.
  • the assembly thus requires no special tools and even less any operation of fixing or stabilizing sections or ends of the ring.
  • the diameter of the ring at rest corresponds approximately to the diameter of the virtual circle passing through the holes or openings of the blade roots. Once mounted, the ring is relatively floating in the openings of the blades. Alternatively, it is possible to provide a slightly smaller diameter for the ring so as to put the vanes in tension via the ring. The mounting procedure of the ring remains the same except that the action of threading the ring through the openings will be a little more difficult, especially once the first turn engaged. In this case, the diameter of the ring at rest will be of the order of 92 to 98% of the nominal diameter of the virtual circle passing through the openings. Such a configuration provides the advantage that the ring is not floating and pulls all the blades evenly towards the center of the shell.
  • a minimum number of turns is necessary to ensure the function of automatic closure of the ring and holding its diameter. Indeed, a minimum of two turns seems required to ensure the stability of the ring.
  • the presence of two turns in practice means about two turns knowing that the last turn may not be complete. This is the case of some rings marketed under the name Spirolox® which include two turns but whose two ends do not overlap. It is clear that more turns or fractions of turns are possible depending on, inter alia, the section of the turns, the diameter of the ring and the desired stiffness for the ring.
  • the blade may deform in bending downstream of the flow and will be retained at the inner ring by the ring or rings.
  • the openings of the blade roots are positioned such that they are at a distance from the inner face of the ferrule. This gives a certain freedom to the blades to slide through the openings of the ferrule in case of impact by a foreign body. In case of deformation of the blade, it may retract a little of the inner ferrule until the ring comes into abutment against the inner face of the shell near the opening.
  • the ring Before reaching the stop, however, the ring will exert a growing restraining force with the retraction of the dawn.
  • the ring is indeed able to deform by sliding its turns relative to each other unlike a simple ring closed for example by welding.
  • the proposed construction is therefore able to guarantee a locking of the blades in the inner shell while ensuring an elastic retention of the blades. This construction is also very simple to implement.
  • the inner face of the inner ferrule is usually used to be lined with friable material ("abradable" according to the English expression more common) to cooperate in friction with one or more wipers of the rotor of the compressor.
  • friable material abradable according to the English expression more common

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (13)

  1. Leitapparat eines Verdichters einer axialen Strömungsmaschine, umfassend einen Außenring und einen Innenring, die beide konzentrisch sind;
    einen Satz Schaufeln (3), die in Radialrichtung angeordnet und an ihren Köpfen (4) am Außenring (1) und an ihren Füßen (5) am Innenring (2) befestigt sind, wobei der Innenring (2) einen Satz Ausschnitte (7) umfasst, von denen jeder den Fuß (5) einer Schaufel, der von der Innenseite des Innenringes (2) aus hervorsteht, aufnimmt, wobei jeder Schaufelfuß (5) mindestens eine von der Innenseite des Innenringes (2) aus hervorstehende Öffnung (8, 8') aufweist;
    dadurch gekennzeichnet, dass
    ein Spiralring (6, 6') mit mindestens zwei Windungen in einer Öffnung (8, 8') jeder Schaufel (3) des Schaufelsatzes aufgenommen ist, um zu verhindern, dass die Schaufelfüße (5) die jeweiligen Ausschnitte (7) des Innenringes (2) verlassen und um eine Verbindung zwischen den Schaufelfüßen (5) zu bilden.
  2. Leitapparat nach dem vorangehenden Anspruch, dadurch gekennzeichnet, dass die Windungen des Ringes (6, 6') sich berühren, wenn der Ring im Ruhezustand ist.
  3. Leitapparat nach dem vorangehenden Anspruch, dadurch gekennzeichnet, dass die Windungen des Ringes (6, 6') aneinander drücken, wenn der Ring im Ruhezustand ist.
  4. Leitapparat nach dem vorangehenden Anspruch, dadurch gekennzeichnet, dass der Ring (6, 6') aus metallischem Material, bevorzugt aus Federstahl, gefertigt ist.
  5. Leitapparat nach dem vorangehenden Anspruch, dadurch gekennzeichnet, dass die Windungen des Ringes (6, 6') mindestens zwei vollständige Umdrehungen beschreiben.
  6. Leitapparat nach dem vorangehenden Anspruch, dadurch gekennzeichnet, dass der Durchmesser des Ringes (6, 6') im Ruhezustand dem Durchmesser des virtuellen Kreises entspricht, der so durch die Öffnungen (8, 8') der Schaufelfüße (5) verläuft, dass der Ring, wenn er eingebaut ist, in den Öffnungen schwimmend aufgenommen ist.
  7. Leitapparat nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass der Durchmesser des Ringes (6, 6') im Ruhezustand geringfügig kleiner ist als der Durchmesser des virtuellen Kreises, der durch die Öffnungen (8, 8') der Schaufelfüße (5) verläuft, und bevorzugt zwischen 92 und 98 % beträgt, so dass der Ring, wenn er eingebaut ist, auf Zug belastet wird.
  8. Leitapparat nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass die Schaufelfüße (5) zwei voneinander entfernte Reihen von Öffnungen (8, 8') umfassen, wobei jede Reihe von Öffnungen einen jeweiligen Spiralring (6, 6') aufnimmt.
  9. Leitapparat nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass die Öffnungen der Schaufelfüße (5) kreisförmig sind.
  10. Axialverdichter, der am Kopf des Verdichters einen Bläser und in Strömungsrichtung direkt hinter dem Bläser einen Leitapparat nach einem der vorangehenden Ansprüche umfasst.
  11. Verfahren zum Halten von Leitapparatschaufeln eines Verdichters einer axialen Strömungsmaschine an einem Innenring, das die folgenden Schritte umfasst:
    a) Vorsehen von Schaufeln (3), von denen die Füße (5) jeweils mindestens eine Öffnung (8, 8') umfassen, die zur Aufnahme eines Blockierungsmittels dient;
    b) Einsetzen des Fußes (5) jeder Schaufel in einen entsprechenden Ausschnitt (7) des Innenringes (2), so dass die Öffnung (8, 8') von der Innenseite des Ringes (2) aus hervorsteht;
    gekennzeichnet durch den folgenden Schritt:
    c) Einbau eines Spiralringes (6, 6') mit mindestens zwei Windungen in eine Öffnung (8, 8') jedes Schaufelfußes (5), indem ein Ende des Ringes nacheinander in die Öffnungen so lange eingefädelt wird, bis alle Windungen des Ringes in den Öffnungen aufgenommen sind.
  12. Verfahren zur Befestigung nach dem vorangehenden Anspruch, dadurch gekennzeichnet, dass der Schritt a) die Befestigung der Schaufelköpfe (4) an einem Außenring (1) umfasst, und dass der Durchmesser des Ringes im Ruhezustand im Wesentlichen dem Durchmesser des Kreises entspricht, der so durch die Öffnungen der Schaufelfüße verläuft, dass der Ring, wenn er eingebaut ist, in den Öffnungen schwimmend aufgenommen ist.
  13. Verfahren zur Befestigung nach dem vorangehenden Anspruch, dadurch gekennzeichnet, dass der Schritt a) die Befestigung der Schaufelköpfe (4) an einem Außenring (1) umfasst, und dass der Durchmesser des Ringes im Ruhezustand geringfügig kleiner ist als der Durchmesser des Kreises, der durch die Öffnungen der Schaufelfüße verläuft, und bevorzugt zwischen 92 und 98 % beträgt, so dass der Ring, wenn er eingebaut ist, auf Zug belastet wird.
EP08172916A 2008-12-24 2008-12-24 Leitschaufelstufe eines Verdichters, entsprechender Verdichter und Verfahren zur Sicherung von Schaufeln in einer solchen Leitschaufelstufe Active EP2204546B1 (de)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP08172916A EP2204546B1 (de) 2008-12-24 2008-12-24 Leitschaufelstufe eines Verdichters, entsprechender Verdichter und Verfahren zur Sicherung von Schaufeln in einer solchen Leitschaufelstufe
AT08172916T ATE548542T1 (de) 2008-12-24 2008-12-24 Leitschaufelstufe eines verdichters, entsprechender verdichter und verfahren zur sicherung von schaufeln in einer solchen leitschaufelstufe
CA2688607A CA2688607C (en) 2008-12-24 2009-12-14 Blade retention at a compressor rectifier stage for impact resistance
US12/644,101 US8764392B2 (en) 2008-12-24 2009-12-22 Blade retention at a compressor rectifier stage for impact resistance

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08172916A EP2204546B1 (de) 2008-12-24 2008-12-24 Leitschaufelstufe eines Verdichters, entsprechender Verdichter und Verfahren zur Sicherung von Schaufeln in einer solchen Leitschaufelstufe

Publications (2)

Publication Number Publication Date
EP2204546A1 EP2204546A1 (de) 2010-07-07
EP2204546B1 true EP2204546B1 (de) 2012-03-07

Family

ID=40340751

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08172916A Active EP2204546B1 (de) 2008-12-24 2008-12-24 Leitschaufelstufe eines Verdichters, entsprechender Verdichter und Verfahren zur Sicherung von Schaufeln in einer solchen Leitschaufelstufe

Country Status (4)

Country Link
US (1) US8764392B2 (de)
EP (1) EP2204546B1 (de)
AT (1) ATE548542T1 (de)
CA (1) CA2688607C (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2735707B1 (de) * 2012-11-27 2017-04-05 Safran Aero Boosters SA Leitrad einer axialen Turbomaschine mit segmentiertem Innendeckband und zugehöriger Verdichter
EP3075960B1 (de) * 2015-03-31 2017-12-27 Ansaldo Energia IP UK Limited Leitschaufeleinheit mit mehrfachprofil
US10472979B2 (en) * 2016-08-18 2019-11-12 United Technologies Corporation Stator shroud with mechanical retention
US20190078469A1 (en) * 2017-09-11 2019-03-14 United Technologies Corporation Fan exit stator assembly retention system
US11428106B2 (en) 2017-09-20 2022-08-30 Sulzer Management Ag Assembly of vane units

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE862158C (de) * 1943-10-05 1953-01-08 Brown Ag Schwingungsdaempfer fuer die Schaufeln von Turbomaschinen
FR998220A (fr) 1949-10-26 1952-01-16 Soc D Const Et D Equipements M Perfectionnement dans le montage et dans la fixation des aubes fixes pour turbomachines
NL81546C (de) * 1952-07-22 1955-12-15
GB732919A (en) 1953-07-15 1955-06-29 Rolls Royce Improvements in or relating to blade assemblies of turbo-machines such as compressors and turbines
FR1380241A (fr) * 1963-02-01 1964-11-27 Ass Elect Ind Perfectionnement aux rotors pour turbines à flux axial
DE19507673C2 (de) * 1995-03-06 1997-07-03 Mtu Muenchen Gmbh Leitrad für Turbomaschinen
DE60026687T2 (de) * 2000-12-06 2006-11-09 Techspace Aero S.A. Statorstufe eines Verdichters
GB2410984B (en) * 2004-02-14 2006-03-08 Rolls Royce Plc Securing assembly

Also Published As

Publication number Publication date
EP2204546A1 (de) 2010-07-07
ATE548542T1 (de) 2012-03-15
CA2688607C (en) 2017-03-28
US20110002787A1 (en) 2011-01-06
CA2688607A1 (en) 2010-06-24
US8764392B2 (en) 2014-07-01

Similar Documents

Publication Publication Date Title
EP2204546B1 (de) Leitschaufelstufe eines Verdichters, entsprechender Verdichter und Verfahren zur Sicherung von Schaufeln in einer solchen Leitschaufelstufe
EP2028375B1 (de) Nasenhaube für eine Turbomaschine mit integrierter Auswuchtvorrichtung
CA2640003C (fr) Clinquant pour aube de turbomachine
EP3074638B1 (de) Gebläse für eine turbomaschine
EP3074639B1 (de) Gebläse, insbesondere für eine turbomaschine, sowie flansch dafür
FR2914008A1 (fr) Ensemble rotatif d'une soufflante de turbomachine
EP3186034B1 (de) Reparatur einer baugruppe mit einem hauptkörper und einer verstärkung
EP2706242A1 (de) Befestigung von Laufradschaufeln auf einer Rotortrommel eines Axialkompressors
EP2705256B1 (de) Turbomaschinenrotor mit mittel zur axialbefestigung der schaufeln
FR2966499A1 (fr) Turbine a vapeur avec aube de fermeture a entree axiale pendulaire
EP2072760A1 (de) Vorrichtung zur Befestigung von Leitschaufeln an einen Stufenring des Stators einer Strömungsmaschine und entsprechendes Befestigungsverfahren
FR2918409A1 (fr) Partie tournante de turbomachine comprenant des secteurs inter-aubes formant plateforme rapportes fixement sur un disque
EP1213483A1 (de) Statorstufe eines Verdichters
CA2795466A1 (fr) Piece anti-usure pour echasse d'aube de soufflante de turboreacteur
FR2971541A1 (fr) Dispositif de blocage circonferentiel d'aubes pour turbomachine, a deploiement radial par depliage d'un u
EP1855011B1 (de) Anordnung für den Verdichter eines Luftschiffmotors mit Schaufelrädern, befestigtem Hammer und geneigtem Fuss
EP1481754A1 (de) Hohle Gebläseschaufel für Strömungsmaschine und Verfahren zur Herstellung einer solchen Schaufel
FR2960463A1 (fr) Procede de reparation d'une bride d'un carter
EP3433469B1 (de) Plattform, fananordnung und fan
EP1515002B1 (de) Verdrehsicherung für Turbinenstatorschaufeln in der Gehäusetrennebene
WO2015158983A1 (fr) Assemblage riveté et procédé de fabrication associé
FR3053384A1 (fr) Ensemble de fixation d'un distributeur a un element de structure d'une turbomachine
CA2952750C (fr) Procede de realisation et de reparation d'un organe de turbomachine et organe de turbomachine associe
FR2954951A1 (fr) Etage redresseur pour un compresseur de turbomachine
EP4291757A1 (de) Leitschaufelanordnung mit positionsbeibehaltungseinrichtung

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

AK Designated contracting states

Kind code of ref document: A1

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

AX Request for extension of the european patent

Extension state: AL BA MK RS

17P Request for examination filed

Effective date: 20101213

17Q First examination report despatched

Effective date: 20110125

AKX Designation fees paid

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

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Owner name: TECHSPACE AERO SA

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

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

Ref legal event code: REF

Ref document number: 548542

Country of ref document: AT

Kind code of ref document: T

Effective date: 20120315

Ref country code: CH

Ref legal event code: EP

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: DE

Ref legal event code: R096

Ref document number: 602008013906

Country of ref document: DE

Effective date: 20120503

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20120307

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

Ref country code: LT

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

Effective date: 20120307

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: 20120307

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: 20120607

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: 20120307

LTIE Lt: invalidation of european patent or patent extension

Effective date: 20120307

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

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: 20120608

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: 20120307

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: 20120307

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 548542

Country of ref document: AT

Kind code of ref document: T

Effective date: 20120307

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: 20120307

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

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: 20120307

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: 20120307

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: 20120307

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: 20120307

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: 20120307

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: 20120307

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: 20120707

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: 20120307

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: 20120709

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: 20120307

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: 20120307

26N No opposition filed

Effective date: 20121210

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: 20120307

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602008013906

Country of ref document: DE

Effective date: 20121210

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: 20120618

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 NON-PAYMENT OF DUE FEES

Effective date: 20121231

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: 20120607

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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: IE

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

Effective date: 20121224

Ref country code: CH

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

Effective date: 20121231

Ref country code: LI

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

Effective date: 20121231

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

Ref country code: MT

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

Effective date: 20120307

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: 20120307

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: 20121224

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

Effective date: 20081224

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 8

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602008013906

Country of ref document: DE

Owner name: SAFRAN AERO BOOSTERS S.A., BE

Free format text: FORMER OWNER: TECHSPACE AERO S.A., HERSTAL, BE

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AERO BOOSTERS S.A., BE

Effective date: 20170606

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

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

Ref country code: DE

Payment date: 20191119

Year of fee payment: 12

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

Ref country code: FR

Payment date: 20191120

Year of fee payment: 12

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

Ref country code: GB

Payment date: 20191122

Year of fee payment: 12

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602008013906

Country of ref document: DE

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

Effective date: 20201224

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

Ref country code: FR

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

Effective date: 20201231

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: 20201224

Ref country code: DE

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

Effective date: 20210701

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

Ref country code: BE

Payment date: 20231121

Year of fee payment: 16