EP3061917B1 - Retaining element and fluid flow engine - Google Patents

Retaining element and fluid flow engine Download PDF

Info

Publication number
EP3061917B1
EP3061917B1 EP16151258.7A EP16151258A EP3061917B1 EP 3061917 B1 EP3061917 B1 EP 3061917B1 EP 16151258 A EP16151258 A EP 16151258A EP 3061917 B1 EP3061917 B1 EP 3061917B1
Authority
EP
European Patent Office
Prior art keywords
blades
locking element
threaded
borehole
groove
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.)
Not-in-force
Application number
EP16151258.7A
Other languages
German (de)
French (fr)
Other versions
EP3061917A1 (en
Inventor
Werner Humhauser
Hermann Klingels
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP3061917A1 publication Critical patent/EP3061917A1/en
Application granted granted Critical
Publication of EP3061917B1 publication Critical patent/EP3061917B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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 a securing element for a row of blades of a turbomachine according to the preamble of patent claim 1 and a turbomachine.
  • a well-known construction principle of blade rows, in particular of blade rows, a turbomachine such as an aircraft engine, a stationary gas turbine or steam turbine provides to insert the blades of the respective blade rows with their feet in a rotor-side anchoring. In the radial direction, the blades are held by their feet positively in the anchoring groove. In the circumferential direction is a position assurance by a securing element that is inserted into the anchoring groove.
  • a known securing element has a base body having a front abutment surfaces and a rear abutment surface for positive engagement with opposite groove surfaces, a front locking projection and a rear locking projection for engaging in opposite recesses of the anchoring groove, and a threaded portion for cooperation with a tightening element.
  • the fuse element is inserted into the anchoring groove after insertion of the blades, displaced in its circumferential position and transferred by the tightening element into its securing position or pulled from below against the groove surfaces.
  • a plate-shaped bridge element is arranged between the securing element that is pressed when tightening the suit element from above against the groove surfaces, whereupon the securing element is pulled from below against the groove surfaces.
  • the bridge element is arranged between the securing element and, in combination with the screw, causes a lifting or securing of the securing element to groove surfaces of the anchoring groove.
  • the fuse element can be screwed by design inside with its inside radially outward, whereby the locking projections do not interfere with the groove side recesses and the blades are circumferentially not secured and can disintegrate.
  • a securing element is shown, which is penetrated by a threaded bore for receiving a screw in the vertical direction. When screwing the screw, this is supported on the groove base and thereby lifts the securing element against corresponding groove surfaces.
  • the securing element has a tubular projection or a collar which surrounds the threaded bore concentrically.
  • the US 2012/251329 A1 discloses a securing member for a row of blades of a turbomachine, which is inserted into a rotor-side anchoring groove and has a bottom threaded portion in which a bolt is screwed from the bottom until it emerges with a bolt portion at the top and thereby form-fitting with adjacent blades of the blade row interacts.
  • the object of the invention is to provide a securing element for a row of blades of a turbomachine, in which a faulty assembly is prevented. Furthermore, it is an object of the invention to provide a turbomachine with increased reliability.
  • An inventive securing element for a row of blades of a turbomachine wherein the blade row comprises a plurality of blades, which are used with their feet in a rotor-side anchoring groove and thereby held in the radial direction positively in the anchoring groove, has a base body having a front abutment surfaces and a rear Contact surface for positive engagement with opposite groove surfaces, a front locking projection and a rear locking projection for engaging in opposite recesses of the anchoring groove, and has a threaded portion for cooperation with a tightening element.
  • the threaded area for the tightening element is only accessible on one side. He is either a bottom side closed internal threaded hole.
  • the threaded portion is a threaded pin extending from the main body.
  • the grub screw indicates the installation position clearly, so that an incorrect insertion of the fuse element is effectively prevented in the anchoring groove.
  • a suit element is used in this variant, a mother. As access barrier for the suit element acts while the body per se.
  • the tightening element can only be placed from one side onto the threaded area. As a result, a faulty mounting of the securing element is reliably prevented, since the tightening element can be brought into operative engagement with the threaded area only in the correct positioning of the securing element within the anchoring groove. In a mispositioning the access to the threaded area for the tightening element is blocked.
  • the fuse element according to the invention can not be screwed by design with its inner side or its underside to the outside. A change of sealing vanes to avoid incorrect assembly is not necessary.
  • the internally threaded bore is a through hole and closed on the bottom side by an outside closure element, for example a plate element, on the base body.
  • the internal threaded bore can be due to their continuous character technically easy to bring and the subsequent bottom-side closure, i. after the formation of the internally threaded bore, allows a technically simple closing.
  • the outer-side closure element is attached to the base body by material bonding, such as soldering or welding. This variant allows the retrofitting of existing security elements with the closure elements, so that existing security elements can be protected against incorrect installation.
  • the internally threaded bore is a through hole and closed on the bottom side by an inside closure element.
  • the inside closure element is For example, a plug element which protrudes with a portion in the internally threaded bore. This allows a positive and positive mounting on the body.
  • the internal threaded hole can also be a blind hole.
  • the threaded pin can be inserted into a receiving bore of the base body.
  • the main body and the threaded pin are made individually, which allows easy production.
  • the connection of the threaded pin with the base body can be done for example by means of screwing into the receiving bore, a twist-locking connection and the like.
  • the grub screw can also be firmly bonded to the base body.
  • a material connection is a reliable and technically manageable connection and can be achieved, for example, by welding and soldering.
  • the grub screw can also be inserted into the receiving bore and circumferentially, for example. Welded in the mouth region of the receiving bore with the body.
  • the grub screw is an integral body portion of the body, By this measure, the number of parts and the mounting of the fuse element can be reduced.
  • the production of the fuse element according to a selective or adaptive manufacturing process such as laser sintering, laser melting and the like.
  • Such manufacturing methods also allow, in particular, a flexible design of the base body and of the threaded pin or threaded pin.
  • a preferred turbomachine has a row of blades whose blades are secured in the circumferential direction by means of a securing element according to one of the preceding claims. In such a row of blades incorrect assembly of the securing element is prevented, so that the preferred turbomachine by a increased reliability compared to known turbomachines without the fuse element according to the invention is characterized.
  • Fig. 1 is a sectional view of a first embodiment of a fuse element according to the invention 1 a flow machine of a row of blades shown.
  • turbomachine With reference to Fig. 1 the turbomachine is flowed through in the direction of its machine longitudinal axis, ie in the axial direction, by a primary flow from left to right.
  • Information such as “back” and “front” refer to the flow direction of the primary flow, information such as "radial” on the rotor or machine longitudinal axis of the turbomachine.
  • the turbomachine is, for example, a gas turbine and in particular an aircraft engine.
  • the blade row consists of a multiplicity of rotor blades 2 arranged next to one another in the circumferential direction of the turbomachine.
  • the rotor blades 2 are each received with their base or foot section concealed by the securing element 1 in a rotor-side and circumferential anchoring groove 4.
  • the securing element 1 is inserted in the anchoring groove 4 of the turbomachine and acts as a circumferential securing device for the rotor blades 2.
  • a radial securing of the rotor blades 2 takes place in a form-fitting manner by means of their feet in the anchoring groove 4.
  • the securing element 1 has a cuboid metallic body 6 and in the widest sense is clamped by means of a front abutment surface 8 and a rear abutment surface 10 of the base body 6 with opposite groove surfaces 12, 14 of the anchoring groove 4. It enters with a front locking projection 16 and with a rear locking projection 18 in opposite recesses 20, 22 of the anchoring groove 4 a.
  • the tension takes place by means of a suit element 24, here a screw, and by means of a plate-shaped bridge member 26.
  • the screw 24 is screwed into a threaded portion 28 of the body 6 and is supported with its screw head 38 on the bridge member 26 from the edge to the groove surfaces 12, 14 opposite support surfaces 30, 32 of the anchoring groove 4 rests.
  • the screw 24 is for example a hexagon socket screw, which is actuated by a frontally engaging in the screw head 38 tool.
  • the so-called sealing vanes For receiving the screw head 38, the so-called sealing vanes have corresponding recesses 42 in the region of their radially inner platforms 40.
  • the screw head 38 is screwed in Condition disposed below an annular space side platform surface 44.
  • the threaded portion 28 is in this embodiment, the main body 6 in the vertical direction passing through internal threaded bore.
  • the high direction is in FIG. 1 indicated by the dashed vertical line.
  • the threaded portion 28 is on the bottom side via a plate-shaped closure element 46 closed on the outside.
  • the threaded portion 28 and the internal threaded bore for the screw 24 is accessible only from one side.
  • the outer closure member 46 is made separately from the base body 6 and subsequently connected thereto.
  • the closure element 46 is like the main body 6 metallic.
  • the connection is made, for example, by means of material connection, preferably by means of spot welding or soldering.
  • FIG. 3 is a perspective plan view of the first embodiment of the fuse element 1 according to the invention shown.
  • the base body 6, the mutually opposite locking projections 16, 18, the mutually opposite contact surfaces 8, 10 and the internal threaded bore 28 clearly visible.
  • FIG. 4 a second embodiment of the fuse element 1 according to the invention is shown.
  • the base 6 itself as a one-sided access barrier for a suit element and thus as a closure element 46.
  • the threaded portion 28 is formed as a extending in the vertical direction threaded pin with an external thread.
  • the tightening element not shown, is correspondingly a nut for unscrewing onto the threaded pin 28.
  • the threaded pin 28 is preferably an integral body portion of a base body 6 of the securing element 1 and is mitgefertigt in its manufacture. It is not a separate part, but is formed as part of an example selective or adaptive production of the base body 6. Exemplary production methods are laser sintering or laser melting.
  • FIG. 5 a third embodiment of the fuse element 1 according to the invention is shown.
  • a threaded pin 28 is a separate part of a base body 6 of the securing element 1 and inserted with a portion in a receiving bore 50 of the base body 6.
  • the receiving bore 50 has an internal thread and the threaded pin 28 is correspondingly screwed into the receiving bore 50.
  • a securing element for a row of blades of a turbomachine wherein the blade row comprises a plurality of blades, which are used with their feet in a rotor-side anchoring groove and thereby held in the radial direction positively in the anchoring, with a base body having a front abutment surface and a rear contact surface for positive engagement with opposite groove surfaces, a front locking projection and a rear locking projection for engaging in opposite recesses of the anchoring groove, and a threaded portion for cooperation with a tightening element, wherein access to the threaded portion for the tightening element is locked on one side, and a turbomachine.

Landscapes

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

Description

Die Erfindung betrifft ein Sicherungselement für eine Schaufelreihe einer Strömungsmaschine nach dem Oberbegriff des Patentanspruchs 1 und eine Strömungsmaschine.The invention relates to a securing element for a row of blades of a turbomachine according to the preamble of patent claim 1 and a turbomachine.

Ein bekanntes Bauprinzip von Schaufelreihen, insbesondere von Laufschaufelreihen, einer Strömungsmaschine wie ein Flugzeugtriebwerk, eine stationäre Gasturbine oder Dampfturbine sieht vor, die Schaufeln der jeweiligen Schaufelreihen mit ihren Füßen in eine rotorseitige Verankerungsnut einzusetzen. In radialer Richtung werden die Schaufeln durch ihre Füße formschlüssig in der Verankerungsnut gehalten. In Umfangsrichtung erfolgt eine Lagesicherung durch ein Sicherungselement, dass in die Verankerungsnut eingesetzt ist. Ein bekanntes Sicherungselement hat einen Grundkörper, der eine vordere Anlageflächen und eine hintere Anlagefläche zum Formschluss mit gegenüberliegenden Nutflächen aufweist, einen vorderen Verriegelungsvorsprung und einen hinteren Verriegelungsvorsprung zum Eingreifen in gegenüberliegende Ausnehmungen der Verankerungsnut, und einen Gewindebereich zum Zusammenwirken mit einem Anzugelement hat. Das Sicherungselement wird nach dem Einführen der Schaufeln in die Verankerungsnut eingesetzt, in seiner Umfangsposition verschoben und durch das Anzugelement in seine Sicherungslage überführt bzw. von unten gegen die Nutflächen gezogen. Dabei wird zwischen dem Sicherungselement ein plattenförmiges Brückenelement angeordnet, dass beim Anziehen des Anzugelements von oben gegen die Nutflächen gedrückt wird, woraufhin das Sicherungselement von unten gegen die Nutflächen gezogen wird. Ein derartiges Bauprinzip ist in dem Patent US 7,708,529 B2 der Anmelderin als Stand der Technik gezeigt. Aus der US 4,859,149 ist ebenfalls ein Sicherungselement bekannt, das mit einer Schraube und einem plattenartigen Brückenelement zusammenwirkt. Das Sicherungselement wird von einer Gewindebohrung durchsetzt, in die die Schraube eingedreht wird. Das Brückenelement ist zwischen dem Sicherungselement angeordnet und bewirkt in Kombination mit der Schraube ein Anheben bzw. Sichern des Sicherungselements an Nutflächen der Verankerungsnut. Es hat sich jedoch bei diesen Prinzipien gezeigt, dass das Sicherungselement konstruktionsbedingt mit seiner Innenseite radial nach außen verschraubt werden kann, wodurch die Verriegelungsvorsprünge nicht in die nutseitigen Ausnehmungen eingreifen und die Schaufeln umfangsmäßig nicht gesichert werden und desintegrieren können.A well-known construction principle of blade rows, in particular of blade rows, a turbomachine such as an aircraft engine, a stationary gas turbine or steam turbine provides to insert the blades of the respective blade rows with their feet in a rotor-side anchoring. In the radial direction, the blades are held by their feet positively in the anchoring groove. In the circumferential direction is a position assurance by a securing element that is inserted into the anchoring groove. A known securing element has a base body having a front abutment surfaces and a rear abutment surface for positive engagement with opposite groove surfaces, a front locking projection and a rear locking projection for engaging in opposite recesses of the anchoring groove, and a threaded portion for cooperation with a tightening element. The fuse element is inserted into the anchoring groove after insertion of the blades, displaced in its circumferential position and transferred by the tightening element into its securing position or pulled from below against the groove surfaces. In this case, a plate-shaped bridge element is arranged between the securing element that is pressed when tightening the suit element from above against the groove surfaces, whereupon the securing element is pulled from below against the groove surfaces. Such a construction principle is in the patent US 7,708,529 B2 the applicant shown as prior art. From the US 4,859,149 is also known a securing element which cooperates with a screw and a plate-like bridge element. The fuse element is penetrated by a threaded hole into which the screw is screwed. The bridge element is arranged between the securing element and, in combination with the screw, causes a lifting or securing of the securing element to groove surfaces of the anchoring groove. However, it has been found in these principles that the fuse element can be screwed by design inside with its inside radially outward, whereby the locking projections do not interfere with the groove side recesses and the blades are circumferentially not secured and can disintegrate.

In der US 7,708,529 B2 ist des Weiteren eine Sicherung von Laufschaufeln in Umfangsrichtung dadurch realisiert, dass die Verankerungsnut zinnenartige Radialvorsprünge hat, die axial von Sicherungsstiften durchsetzt sind und hierdurch seitliche Anschläge für die Laufschaufeln bilden.In the US 7,708,529 B2 Furthermore, a securing of blades in the circumferential direction is realized in that the anchoring groove has crenellated radial projections, which are axially penetrated by locking pins and thereby form lateral stops for the blades.

In der CA 2829460 A1 und in der GB 2 156 908 A ist jeweils ein Sicherungselement gezeigt, das von einer Gewindebohrung zur Aufnahme einer Schraube in Hochrichtung durchsetzt ist. Beim Eindrehen der Schraube stützt sich diese am Nutgrund ab und hebt hierdurch das Sicherungselement gegen entsprechende Nutflächen. Zum Zusammenwirken mit sogenannten Verschlussschaufeln hat das Sicherungselement einen rohrartigen Vorsprung bzw. einen Kragen, der die Gewindebohrung konzentrisch umgibt.In the CA 2829460 A1 and in the GB 2 156 908 A in each case a securing element is shown, which is penetrated by a threaded bore for receiving a screw in the vertical direction. When screwing the screw, this is supported on the groove base and thereby lifts the securing element against corresponding groove surfaces. For cooperation with so-called shutter blades, the securing element has a tubular projection or a collar which surrounds the threaded bore concentrically.

Aus der US 4,255,086 sind Sicherungselemente bekannt, die auf einen in einer Verankerungsnut eingesetzten Drahtring aufgefädelt werden.From the US 4,255,086 Securing elements are known, which are threaded onto a wire ring inserted in an anchoring groove.

Die US 2012/251329 A1 offenbart ein Sicherungselement für eine Schaufelreihe einer Strömungsmaschine, die in eine rotorseitige Verankerungsnut eingesetzt wird und einen bodenseitigen Gewindebereich hat, in den von der Unterseite her ein Schraubbolzen eingedreht wird, bis dieser mit einem Bolzenabschnitt an der Oberseite austritt und hierdurch formschlüssig mit benachbarten Schaufeln der Schaufelreihe zusammenwirkt.The US 2012/251329 A1 discloses a securing member for a row of blades of a turbomachine, which is inserted into a rotor-side anchoring groove and has a bottom threaded portion in which a bolt is screwed from the bottom until it emerges with a bolt portion at the top and thereby form-fitting with adjacent blades of the blade row interacts.

Aufgabe der Erfindung ist es, ein Sicherungselement für eine Schaufelreihe einer Strömungsmaschine zu schaffen, bei dem eine Fehlmontage verhindert wird. Des Weiteren ist es Aufgabe der Erfindung, eine Strömungsmaschine mit einer erhöhten Zuverlässigkeit zu schaffen.The object of the invention is to provide a securing element for a row of blades of a turbomachine, in which a faulty assembly is prevented. Furthermore, it is an object of the invention to provide a turbomachine with increased reliability.

Diese Aufgabe wird gelöst durch ein Sicherungselement mit den Merkmalen des Patentanspruchs 1 und durch eine Strömungsmaschine mit den Merkmalen des Patentanspruchs 8.This object is achieved by a securing element having the features of patent claim 1 and by a turbomachine having the features of patent claim 8.

Ein erfindungsgemäßes Sicherungselement für eine Schaufelreihe einer Strömungsmaschine, wobei die Schaufelreihe eine Vielzahl von Schaufeln umfasst, die mit ihren Füßen in einer rotorseitigen Verankerungsnut eingesetzt und hierdurch in radialer Richtung formschlüssig in der Verankerungsnut gehalten sind, hat einen Grundkörper, der eine vordere Anlageflächen und eine hintere Anlagefläche zum Formschluss mit gegenüberliegenden Nutflächen, einen vorderen Verriegelungsvorsprung und einen hinteren Verriegelungsvorsprung zum Eingreifen in gegenüberliegende Ausnehmungen der Verankerungsnut, und einen Gewindebereich zum Zusammenwirken mit einem Anzugelement aufweist. Der Gewindebereich für das Anzugelement ist nur einseitig zugänglich. Er ist entweder eine bodenseitig verschlossene Innengewindebohrung. Durch das Ausbilden einer Innengewindebohrung lässt sich auf bekannte Techniken zurückgreifen, wobei durch den bodenseitigen Verschluss ein zuverlässiges Verschließen erfolgt. Alternativ ist der Gewindebereich ein sich von dem Grundkörper erstreckender Gewindestift. Der Gewindestift gibt die Einbaulage eindeutig vor, so dass ein falsches Einsetzen des Sicherungselements in die Verankerungsnut wirkungsvoll verhindert wird. Als Anzugelement dient bei dieser Variante eine Mutter. Als Zugangssperre für das Anzugelement wirkt dabei der Grundkörper per se.An inventive securing element for a row of blades of a turbomachine, wherein the blade row comprises a plurality of blades, which are used with their feet in a rotor-side anchoring groove and thereby held in the radial direction positively in the anchoring groove, has a base body having a front abutment surfaces and a rear Contact surface for positive engagement with opposite groove surfaces, a front locking projection and a rear locking projection for engaging in opposite recesses of the anchoring groove, and has a threaded portion for cooperation with a tightening element. The threaded area for the tightening element is only accessible on one side. He is either a bottom side closed internal threaded hole. The formation of an internally threaded bore makes it possible to resort to known techniques, with the bottom-side closure providing reliable closure. Alternatively, the threaded portion is a threaded pin extending from the main body. The grub screw indicates the installation position clearly, so that an incorrect insertion of the fuse element is effectively prevented in the anchoring groove. As a suit element is used in this variant, a mother. As access barrier for the suit element acts while the body per se.

Durch die einseitige Zugänglichkeit des Gewindebereichs kann das Anzugelement nur von einer Seite auf den Gewindebereich aufgesetzt werden. Hierdurch wird eine Fehlmontage des Sicherungselements zuverlässig verhindert, da das Anzugelement nur in der richtigen Positionierung des Sicherungselementes innerhalb der Verankerungsnut mit dem Gewindebereich in Wirkeingriff bringbar ist. In einer Fehlpositionierung ist der Zugang zum Gewindebereich für das Anzugelement gesperrt. Das erfindungsgemäße Sicherungselement kann konstruktionsbedingt nicht mit seiner Innenseite bzw. seiner Unterseite nach außen verschraubt werden. Eine Änderung von Verschlussschaufeln zur Vermeidung einer Fehlmontage ist nicht notwendig.Due to the one-sided accessibility of the threaded area, the tightening element can only be placed from one side onto the threaded area. As a result, a faulty mounting of the securing element is reliably prevented, since the tightening element can be brought into operative engagement with the threaded area only in the correct positioning of the securing element within the anchoring groove. In a mispositioning the access to the threaded area for the tightening element is blocked. The fuse element according to the invention can not be screwed by design with its inner side or its underside to the outside. A change of sealing vanes to avoid incorrect assembly is not necessary.

Bevorzugterweise ist die Innengewindebohrung eine Durchgangsbohrung und bodenseitig durch ein außenseitiges Verschlusselement, beispielsweise ein Plattenelement, am Grundkörper verschlossen. Die Innengewindebohrung lässt sich aufgrund ihres durchgehenden Charakters technisch einfach einbringen und der nachträgliche bodenseitige Verschluss, d.h. nach der Ausbildung der Innengewindebohrung, ermöglicht ein technisch einfaches Verschließen. Beispielsweise wird das außenseitige Verschlusselement durch Stoffschluss wie Löten oder Schweißen an dem Grundkörper angebracht. Diese Variante ermöglicht die Nachrüstung von bestehenden Sicherungselementen mit den Verschlusselementen, so dass auch bestehende Sicherungselemente gegen Fehlmontagen geschützt werden können.Preferably, the internally threaded bore is a through hole and closed on the bottom side by an outside closure element, for example a plate element, on the base body. The internal threaded bore can be due to their continuous character technically easy to bring and the subsequent bottom-side closure, i. after the formation of the internally threaded bore, allows a technically simple closing. For example, the outer-side closure element is attached to the base body by material bonding, such as soldering or welding. This variant allows the retrofitting of existing security elements with the closure elements, so that existing security elements can be protected against incorrect installation.

Alternativ ist die Innengewindebohrung eine Durchgangsbohrung und bodenseitig durch ein innenseitiges Verschlusselement verschlossen. Das innenseitige Verschlusselement ist beispielsweise ein Stopfenelement, das mit einem Abschnitt in die Innengewindebohrung hineinragt. Diese ermöglicht eine kraft- und formschlüssige Montage an dem Grundkörper.Alternatively, the internally threaded bore is a through hole and closed on the bottom side by an inside closure element. The inside closure element is For example, a plug element which protrudes with a portion in the internally threaded bore. This allows a positive and positive mounting on the body.

Die Innengewindebohrung kann auch eine Sacklochbohrung sein. Durch diese Maßnahme wird die Teileanzahl des Sicherungselements reduziert, da separate Verschlusselemente zum einseitigen Verschließen des Gewindebereichs entfallen. Zudem wird durch den Wegfall der Montage der Verschlusselemente die Montagezeit verkürzt.The internal threaded hole can also be a blind hole. By this measure, the number of parts of the fuse element is reduced, since separate closure elements account for unilateral closing of the threaded portion. In addition, the assembly time is shortened by eliminating the installation of the closure elements.

Der Gewindestift kann in eine Aufnahmebohrung des Grundkörpers eingesetzt sein. Durch diese Maßnahme werden der Grundkörper und der Gewindestift einzeln hergestellt, was eine einfache Herstellung ermöglicht. Die Verbindung des Gewindestiftes mit dem Grundkörper kann beispielsweise mittels Eindrehen in die Aufnahmebohrung, eine verdrehsichere Rastverbindung und dergleichen erfolgen.The threaded pin can be inserted into a receiving bore of the base body. By this measure, the main body and the threaded pin are made individually, which allows easy production. The connection of the threaded pin with the base body can be done for example by means of screwing into the receiving bore, a twist-locking connection and the like.

Der Gewindestift kann auch stoffschlüssig an dem Grundkörper angebunden sein. Ein Stoffschluss ist eine zuverlässige und technisch beherrschbare Verbindung und kann bspw. durch Schweißen und Löten erzielt werden. Selbstverständlich kann der Gewindestift auch in die Aufnahmebohrung eingesetzt und umfangsseitig bspw. im Mündungsbereich der Aufnahmebohrung mit dem Grundkörper verschweißt sein.The grub screw can also be firmly bonded to the base body. A material connection is a reliable and technically manageable connection and can be achieved, for example, by welding and soldering. Of course, the grub screw can also be inserted into the receiving bore and circumferentially, for example. Welded in the mouth region of the receiving bore with the body.

Alternativ ist der Gewindestift ein integraler Körperabschnitt des Grundkörpers ist, Durch diese Maßnahme werden die Teileanzahl und die Montage des Sicherungselements reduziert. Beispielsweise erfolgt die Herstellung des Sicherungselements gemäß einem selektiven bzw. adaptiven Herstellungsverfahren wie Lasersintern, Laserschmelzen und dergleichen. Derartige Herstellungsverfahren ermöglichen insbesondere auch eine flexible Formgestaltung des Grundkörpers und des Gewindestiftes bzw. Gewindezapfens.Alternatively, the grub screw is an integral body portion of the body, By this measure, the number of parts and the mounting of the fuse element can be reduced. For example, the production of the fuse element according to a selective or adaptive manufacturing process such as laser sintering, laser melting and the like. Such manufacturing methods also allow, in particular, a flexible design of the base body and of the threaded pin or threaded pin.

Eine bevorzugte Strömungsmaschine hat eine Schaufelreihe, deren Schaufeln in Umfangsrichtung mittels eines Sicherungselements nach einem der vorhergehenden Patentansprüche gesichert sind. Bei einer derartigen Schaufelreihe ist eine Fehlmontage des Sicherungselements verhindert, so dass sich die bevorzugte Strömungsmaschine durch eine erhöhte Zuverlässigkeit im Vergleich zu bekannten Strömungsmaschinen ohne das erfindungsgemäße Sicherungselement auszeichnet.A preferred turbomachine has a row of blades whose blades are secured in the circumferential direction by means of a securing element according to one of the preceding claims. In such a row of blades incorrect assembly of the securing element is prevented, so that the preferred turbomachine by a increased reliability compared to known turbomachines without the fuse element according to the invention is characterized.

Sonstige vorteilhafte Ausführungsbeispiele der Erfindung sind Gegenstand weiterer Unteransprüche.Other advantageous embodiments of the invention are the subject of further subclaims.

Im Folgenden werden bevorzugte Ausführungsbeispiele der Erfindung anhand von schematischen Darstellungen näher erläutert. Es zeigen:

Figur 1
einen Längsschnitt durch ein erstes Ausführungsbeispiel eines erfindungsgemäßen Sicherungselements eingesetzt in einer rotorseitigen Verankerungsnut einer Strömungsmaschine,
Figur 2
eine Unteransicht des ersten Ausführungsbeispiels,
Figur 3
eine perspektive Draufsicht auf das erste Ausführungsbeispiel,
Figur 4
eine perspektive Darstellung eines zweiten Ausführungsbeispiels des erfindungsgemäßen Sicherungselements, und
Figur 5
eine perspektive Darstellung eines dritten Ausführungsbeispiels des erfindungsgemäßen Sicherungselements.
In the following preferred embodiments of the invention will be explained in more detail with reference to schematic representations. Show it:
FIG. 1
a longitudinal section through a first embodiment of a securing element according to the invention used in a rotor-side anchoring groove of a turbomachine,
FIG. 2
a bottom view of the first embodiment,
FIG. 3
a perspective top view of the first embodiment,
FIG. 4
a perspective view of a second embodiment of the fuse element according to the invention, and
FIG. 5
a perspective view of a third embodiment of the fuse element according to the invention.

In Fig. 1 ist eine Schnittdarstellung eines ersten Ausführungsbeispiels eines erfindungsgemäßen Sicherungselements 1 einer Strömungsmaschine einer Schaufelreihe gezeigt.In Fig. 1 is a sectional view of a first embodiment of a fuse element according to the invention 1 a flow machine of a row of blades shown.

Mit Bezug zur Fig. 1 wird die Strömungsmaschine in Richtung ihrer Maschinenlängsachse, also in axialer Richtung, von einem Primärstrom von links nach rechts durchströmt. Angaben wie "hinterer" und "vorderer" beziehen sich auf die Strömungsrichtung des Primärstroms, Angaben wie "radial" auf die Rotor- bzw. Maschinenlängsachse der Strömungsmaschine. Die Strömungsmaschine ist beispielsweise eine Gasturbine und insbesondere ein Flugtriebwerk.With reference to Fig. 1 the turbomachine is flowed through in the direction of its machine longitudinal axis, ie in the axial direction, by a primary flow from left to right. Information such as "back" and "front" refer to the flow direction of the primary flow, information such as "radial" on the rotor or machine longitudinal axis of the turbomachine. The turbomachine is, for example, a gas turbine and in particular an aircraft engine.

Die Schaufelreihe besteht aus einer Vielzahl von in Umfangsrichtung der Strömungsmaschine nebeneinander angeordneten Laufschaufeln 2. Die Laufschaufeln 2 sind jeweils mit ihrem vom Sicherungselement 1 verdeckten Fuß bzw. Fußabschnitt in einer rotorseitigen und umfangsseitigen Verankerungsnut 4 aufgenommen.The blade row consists of a multiplicity of rotor blades 2 arranged next to one another in the circumferential direction of the turbomachine. The rotor blades 2 are each received with their base or foot section concealed by the securing element 1 in a rotor-side and circumferential anchoring groove 4.

Das Sicherungselement 1 ist in der Verankerungsnut 4 der Strömungsmaschine eingesetzt und wirkt als Umfangssicherung für die Laufschaufeln 2. Eine radiale Sicherung der Laufschaufeln 2 erfolgt formschlüssig durch ihre Füße in der Verankerungsnut 4. Das Sicherungselement 1 hat einen im weitesten Sinn quaderartigen, metallischen Grundkörper 6 und ist mittels einer vorderen Anlagefläche 8 und einer hinteren Anlagefläche 10 des Grundkörpers 6 mit gegenüberliegenden Nutflächen 12, 14 der Verankerungsnut 4 verspannt. Es taucht mit einem vorderen Verriegelungsvorsprung 16 und mit einem hinteren Verriegelungsvorsprung 18 in gegenüberliegende Ausnehmungen 20, 22 der Verankerungsnut 4 ein. Die Verspannung erfolgt mittels einer eines Anzugelements 24, das hier eine Schraube, und mittels eines plattenförmigen Brückenelements 26. Die Schraube 24 ist in einen Gewindebereich 28 des Grundkörpers 6 eingeschraubt und stützt sich mit ihrem Schraubenkopf 38 auf dem Brückenelement 26 ab, das randseitig auf zu den Nutflächen 12, 14 entgegengesetzten Stützflächen 30, 32 der Verankerungsnut 4 aufliegt. Die Schraube 24 ist beispielweise eine Innensechskantschraube, die durch ein stirnseitig in den Schraubenkopf 38 eingreifendes Werkzeug betätigt wird. Beim Anziehen der Schraube 24 bzw. des Anzugelements wird das Brückenelement 26 von oben gegen die Stützflächen 30, 32 gepresst und hierdurch der Grundkörper 6 von unten gegen die Nutflächen 12, 14 gezogen, wodurch es neben seiner Fixierung in seiner Sicherungslage auch vom Nutgrund 34 abgehoben wird. Zum schaftseitigen Durchführen der Schraube 24 hat das Brückenelement 26 eine entsprechende Durchgangsbohrung 36. Zur Aufnahme des Schraubenkopfes 38 haben die sogenannten Verschlussschaufeln im Bereich ihrer radial inneren Plattformen 40 entsprechende Ausnehmungen 42. Um Turbulenzen im Bereich des Primärstroms zu vermeiden, ist der Schraubenkopf 38 im eingeschraubten Zustand unterhalb einer ringraumseitigen Plattformfläche 44 angeordnet.The securing element 1 is inserted in the anchoring groove 4 of the turbomachine and acts as a circumferential securing device for the rotor blades 2. A radial securing of the rotor blades 2 takes place in a form-fitting manner by means of their feet in the anchoring groove 4. The securing element 1 has a cuboid metallic body 6 and in the widest sense is clamped by means of a front abutment surface 8 and a rear abutment surface 10 of the base body 6 with opposite groove surfaces 12, 14 of the anchoring groove 4. It enters with a front locking projection 16 and with a rear locking projection 18 in opposite recesses 20, 22 of the anchoring groove 4 a. The tension takes place by means of a suit element 24, here a screw, and by means of a plate-shaped bridge member 26. The screw 24 is screwed into a threaded portion 28 of the body 6 and is supported with its screw head 38 on the bridge member 26 from the edge to the groove surfaces 12, 14 opposite support surfaces 30, 32 of the anchoring groove 4 rests. The screw 24 is for example a hexagon socket screw, which is actuated by a frontally engaging in the screw head 38 tool. When tightening the screw 24 and the tightening element, the bridge element 26 is pressed from above against the support surfaces 30, 32 and thereby the base body 6 pulled from below against the groove surfaces 12, 14, whereby it also lifted off the groove base 34 in addition to its fixation in its backup position becomes. For receiving the screw head 38, the so-called sealing vanes have corresponding recesses 42 in the region of their radially inner platforms 40. In order to avoid turbulence in the region of the primary flow, the screw head 38 is screwed in Condition disposed below an annular space side platform surface 44.

Der Gewindebereich 28 ist bei diesem Ausführungsbeispiel eine den Grundkörper 6 in Hochrichtung durchsetzende Innengewindebohrung. Die Hochrichtung ist in Figur 1 durch die gestrichelte vertikale Linie angedeutet. Um eine Fehlmontage des Sicherungselements 1 zu verhindern, ist der Gewindebereich 28 bodenseitig über ein plattenförmiges Verschlusselement 46 außenseitig verschlossen. Somit ist der Gewindebereich 28 bzw. die Innengewindebohrung für die Schraube 24 nur von einer Seite zugänglich.The threaded portion 28 is in this embodiment, the main body 6 in the vertical direction passing through internal threaded bore. The high direction is in FIG. 1 indicated by the dashed vertical line. To prevent incorrect assembly of the securing element 1, the threaded portion 28 is on the bottom side via a plate-shaped closure element 46 closed on the outside. Thus, the threaded portion 28 and the internal threaded bore for the screw 24 is accessible only from one side.

Wie in Figur 2 durch vier Kreuze 48 angedeutet, wird das äußere Verschlusselement 46 separat von dem Grundkörper 6 hergestellt und nachträglich mit diesem verbunden. Das Verschlusselement 46 ist wie der Grundkörper 6 metallisch. Die Anbindung erfolgt beispielsweise mittels Stoffschluss, bevorzugterweise mittels Punktschweißens oder Lötens.As in FIG. 2 indicated by four crosses 48, the outer closure member 46 is made separately from the base body 6 and subsequently connected thereto. The closure element 46 is like the main body 6 metallic. The connection is made, for example, by means of material connection, preferably by means of spot welding or soldering.

In Figur 3 ist eine perspektive Draufsicht auf das erste Ausführungsbeispiels des erfindungsgemäßen Sicherungselements 1 gezeigt. In dieser sind der Grundkörper 6, die zueinander entgegengesetzten Verriegelungsvorsprünge 16, 18, die zueinander entgegengesetzten Anlagenflächen 8, 10 und die Innengewindebohrung 28 deutlich zu erkennen.In FIG. 3 is a perspective plan view of the first embodiment of the fuse element 1 according to the invention shown. In this, the base body 6, the mutually opposite locking projections 16, 18, the mutually opposite contact surfaces 8, 10 and the internal threaded bore 28 clearly visible.

In Figur 4 ist ein zweites Ausführungsbeispiel des erfindungsgemäßen Sicherungselements 1 gezeigt. Im Unterschied zum ersten Ausführungsbeispiel nach den Figuren 1 bis 3 wirkt bei diesem Ausführungsbeispiel der Grundkörper 6 selbst als einseitige Zugangssperre für ein Anzugelement und somit als Verschlusselement 46. Hierzu ist der Gewindebereich 28 als ein sich in Hochrichtung erstreckender Gewindestift mit einem Außengewinde ausgebildet. Das nicht gezeigte Anzugelement ist entsprechend eine Mutter zum Aufdrehen auf den Gewindestift 28. Der Gewindestift 28 ist bevorzugterweise ein integraler Körperabschnitt eines Grundkörpers 6 des Sicherungselements 1 und wird bei dessen Herstellung mitgefertigt. Er ist kein separates Teil, sondern wird im Rahmen einer beispielweise selektiven bzw. adaptiven Herstellung des Grundkörpers 6 ausgebildet. Beispielhafte Herstellungsverfahren sind Lasersintern oder Laserschmelzen.In FIG. 4 a second embodiment of the fuse element 1 according to the invention is shown. In contrast to the first embodiment of the FIGS. 1 to 3 acts in this embodiment, the base 6 itself as a one-sided access barrier for a suit element and thus as a closure element 46. For this purpose, the threaded portion 28 is formed as a extending in the vertical direction threaded pin with an external thread. The tightening element, not shown, is correspondingly a nut for unscrewing onto the threaded pin 28. The threaded pin 28 is preferably an integral body portion of a base body 6 of the securing element 1 and is mitgefertigt in its manufacture. It is not a separate part, but is formed as part of an example selective or adaptive production of the base body 6. Exemplary production methods are laser sintering or laser melting.

In Figur 5 ist ein drittes Ausführungsbeispiel des erfindungsgemäßen Sicherungselements 1 gezeigt. Im Unterschied zum zweiten Ausführungsbeispiel nach den Figur 4 ist ein Gewindestift 28 ein separates Teil eines Grundkörpers 6 des Sicherungselements 1 und mit einem Abschnitt in eine Aufnahmebohrung 50 des Grundkörpers 6 eingesetzt. Beispielsweise hat die Aufnahmebohrung 50 ein Innengewinde und der Gewindestift 28 ist entsprechend in die Aufnahmebohrung 50 eingedreht.In FIG. 5 a third embodiment of the fuse element 1 according to the invention is shown. In contrast to the second embodiment of the FIG. 4 a threaded pin 28 is a separate part of a base body 6 of the securing element 1 and inserted with a portion in a receiving bore 50 of the base body 6. For example, the receiving bore 50 has an internal thread and the threaded pin 28 is correspondingly screwed into the receiving bore 50.

Offenbart ist ein Sicherungselement für eine Schaufelreihe einer Strömungsmaschine, wobei die Schaufelreihe eine Vielzahl von Schaufeln umfasst, die mit ihren Füßen in einer rotorseitigen Verankerungsnut eingesetzt und hierdurch in radialer Richtung formschlüssig in der Verankerungsnut gehalten sind, mit einem Grundkörper, der eine vordere Anlagefläche und eine hintere Anlagefläche zum Formschluss mit gegenüberliegenden Nutflächen, einen vorderen Verriegelungsvorsprung und einen hinteren Verriegelungsvorsprung zum Eingreifen in gegenüberliegende Ausnehmungen der Verankerungsnut, und einen Gewindebereich zum Zusammenwirken mit einem Anzugelement hat, wobei ein Zugang zum Gewindebereich für das Anzugelement einseitig gesperrt ist, sowie eine Strömungsmaschine.Disclosed is a securing element for a row of blades of a turbomachine, wherein the blade row comprises a plurality of blades, which are used with their feet in a rotor-side anchoring groove and thereby held in the radial direction positively in the anchoring, with a base body having a front abutment surface and a rear contact surface for positive engagement with opposite groove surfaces, a front locking projection and a rear locking projection for engaging in opposite recesses of the anchoring groove, and a threaded portion for cooperation with a tightening element, wherein access to the threaded portion for the tightening element is locked on one side, and a turbomachine.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Sicherungselementfuse element
22
Leitschaufelvane
44
Verankerungsnutanchoring groove
66
Grundkörperbody
88th
vordere Anlageflächefront contact surface
1010
hintere Anlageflächerear contact surface
1212
vordere Nutflächefront groove surface
1414
hintere Nutflächerear groove surface
1616
vorderer Verriegelungsvorsprungfront locking projection
1818
hinterer Verriegelungsvorsprungrear locking projection
2020
Ausnehmungrecess
2222
Ausnehmungrecess
2424
Anzugelement / Schraube / MutterTightening element / screw / nut
2626
Brückenelementbridge element
2828
Gewindebereich / Innengewindebohrung / GewindestiftThreaded area / internally threaded hole / threaded pin
3030
Stützflächesupport surface
3232
Stützflächesupport surface
3434
Nutgrundgroove base
3636
DurchgangsbohrungThrough Hole
3838
Schraubenkopfscrew head
4040
Plattformplatform
4242
Ausnehmungrecess
4444
Plattformflächeplatform surface
4646
Verschlusselementclosure element
4848
Kreuzecrosses
5050
Aufnahmebohrunglocation hole

Claims (8)

  1. A locking element (1) for a row of blades of a turbomachine, wherein the row of blades comprises a plurality of blades (2) that are inserted by their roots in a rotor-side anchoring groove (4) and are thereby held in the radial direction in form-fitting manner in the anchoring groove, the locking element having a basic body (6) that has a front bearing surface (8) and a back bearing surface (10) for form-fitting with opposite-lying groove surfaces (12, 14), a front lock projection (16) and a back lock projection (18) for engaging in opposite-lying recesses (20, 22) of the anchoring groove (4), and a threaded region (28) for interacting with a tightening element (24), wherein the threaded region (28) for the tightening element (24) is accessible only on one side, characterized in that the threaded region (28) is an inner thread borehole that is closed on the bottom side, or the threaded region (28) is a threaded pin extending from the basic body (6).
  2. The locking element according to claim 1, wherein the inner thread borehole (28) is a through-borehole and is closed on the bottom by an external closure element (46).
  3. The locking element according to claim 1, wherein the inner thread borehole (28) is a through-borehole and is closed on the bottom by an internal closure element (46).
  4. The locking element according to claim 1, wherein the inner thread borehole (28) is a blind borehole.
  5. The locking element according to claim 1, wherein the threaded pin (28) is inserted into an uptake hole of the basic body (6).
  6. The locking element according to claim 1 or 5, wherein the threaded pin (28) is integrally bonded to the basic body (6).
  7. The locking element according to claim 5, wherein the threaded pin (28) is an integral segment of the basic body (6).
  8. A turbomachine comprising a row of blades, the blades (2) thereof being locked in the circumferential direction by means of the locking element (1) according to any of the preceding claims.
EP16151258.7A 2015-02-24 2016-01-14 Retaining element and fluid flow engine Not-in-force EP3061917B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102015203290.6A DE102015203290A1 (en) 2015-02-24 2015-02-24 Securing element and turbomachine

Publications (2)

Publication Number Publication Date
EP3061917A1 EP3061917A1 (en) 2016-08-31
EP3061917B1 true EP3061917B1 (en) 2018-06-06

Family

ID=55129741

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16151258.7A Not-in-force EP3061917B1 (en) 2015-02-24 2016-01-14 Retaining element and fluid flow engine

Country Status (3)

Country Link
US (1) US10352178B2 (en)
EP (1) EP3061917B1 (en)
DE (1) DE102015203290A1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR102095033B1 (en) * 2017-05-30 2020-03-30 두산중공업 주식회사 Vane ring assembly and compressor and gas turbine including the same
DE102019111211A1 (en) * 2019-04-30 2020-11-05 Rolls-Royce Deutschland Ltd & Co Kg Device for setting a balancing state of a rotating part of a gas turbine engine, a balancing body and a gas turbine engine for an aircraft

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA1114301A (en) 1979-06-27 1981-12-15 Ivor J. Roberts Locking device for blade mounting
GB2156908A (en) 1984-03-30 1985-10-16 Rolls Royce Bladed rotor assembly for gas turbine engine
GB2171150B (en) * 1985-02-12 1989-07-26 Rolls Royce Plc Bladed rotor assembly for a turbomachine
US4859149A (en) 1989-03-10 1989-08-22 General Motors Corporation Blade locking system
GB0102757D0 (en) * 2001-02-03 2001-03-21 Rolls Royce Plc Locking device
FR2832455B1 (en) * 2001-11-22 2004-04-02 Snecma Moteurs DEVICE FOR LOCKING BLADES IN A GROOVE OF A DISC
ITMI20012783A1 (en) * 2001-12-21 2003-06-21 Nuovo Pignone Spa CONNECTION AND LOCKING SYSTEM OF ROTORIAL BLADES OF AN AXIAL COMPRESSOR
DE102004051116A1 (en) 2004-10-20 2006-04-27 Mtu Aero Engines Gmbh Rotor of a turbomachine, in particular gas turbine rotor
US7435055B2 (en) * 2005-03-29 2008-10-14 Siemens Power Generation, Inc. Locking spacer assembly for a turbine engine
US8523529B2 (en) * 2009-11-11 2013-09-03 General Electric Company Locking spacer assembly for a circumferential entry airfoil attachment system
JP5730085B2 (en) * 2011-03-17 2015-06-03 三菱日立パワーシステムズ株式会社 Rotor structure
US8757981B2 (en) * 2011-04-28 2014-06-24 Siemens Aktiengesellschaft Locking spacer assembly for a turbine engine
EP2719866B1 (en) 2012-10-12 2018-12-05 Safran Aero Boosters SA Rotor disk of a turbomachine comprising a lock for blades

Also Published As

Publication number Publication date
DE102015203290A1 (en) 2016-09-29
EP3061917A1 (en) 2016-08-31
US20160245101A1 (en) 2016-08-25
US10352178B2 (en) 2019-07-16

Similar Documents

Publication Publication Date Title
DE1289374B (en) Pipe connection piece for high pressure lines
EP2140114A2 (en) Axial bearing, particularly for a turbocharger
EP2478187B1 (en) Blade fixation with locking device for turbine blades
EP2730843A1 (en) Combustion chamber shingle of a gas turbine
DE112008000447T5 (en) safety valve
EP2873807A1 (en) Cover plate, rotor blade, wheel disc, bolt and gas turbine
EP1584793A2 (en) Turbine blade retaining system
DE19828817C2 (en) Rotor for a turbo machine
EP3061917B1 (en) Retaining element and fluid flow engine
DE102014101416A1 (en) Valve device for a hydraulic door closer
EP2788583B1 (en) Turbine vane with a throttling element
DE102011005405A1 (en) mounting assembly
DE102008060705A1 (en) Horizontally split turbomachine housing
EP3353455B1 (en) Check valve
DE967498C (en) Blade attachment in axial flow machines
DE102010052118A1 (en) steam turbine rotor
EP3312388A1 (en) Pultdach dichtfin
DE10140259C1 (en) Axial turbine for exhaust gas turbocharger has blade foot of each rotor blade secured in axial slot of rotor disc via respective fixing element
EP2873808B1 (en) Rotor-blade group, method and flow engine
DE102004016244B4 (en) Rotor for a turbomachine
WO2015113839A1 (en) Piston for an internal combustion engine
EP3240965B1 (en) Angle valve
EP3546717B1 (en) Seal for waste gas system
EP4130441A1 (en) Device for connecting a pivotable vane of a gas turbine and gas turbine
EP1862638B1 (en) Method for repairing the rotor of a gas turbine and rotor of a gas turbine

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

AX Request for extension of the european patent

Extension state: BA ME

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20170216

RBV Designated contracting states (corrected)

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

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/30 20060101AFI20180208BHEP

Ipc: F01D 5/32 20060101ALI20180208BHEP

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20180319

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

Ref country code: AT

Ref legal event code: REF

Ref document number: 1006310

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180615

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502016001128

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20180606

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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

Ref country code: 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: 20180906

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: 20180606

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: 20180606

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: 20180606

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: 20180906

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: 20180606

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: 20180606

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: 20180606

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: 20180606

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: 20180606

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: 20180907

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: 20180606

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

Ref country code: IS

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

Effective date: 20181006

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: 20180606

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: 20180606

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: 20180606

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: 20180606

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: 20180606

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: 20180606

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: 20180606

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502016001128

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20190307

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: 20180606

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: 20180606

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: 20180606

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: 20190114

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20190131

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: 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: 20180606

Ref country code: BE

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

Effective date: 20190131

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

Ref country code: CH

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

Effective date: 20190131

Ref country code: LI

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

Effective date: 20190131

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: 20190114

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: 20180606

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

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: 20181008

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: 20180606

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: 20160114

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1006310

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210114

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

Ref country code: AT

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

Effective date: 20210114

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

Ref country code: GB

Payment date: 20220125

Year of fee payment: 7

Ref country code: DE

Payment date: 20220120

Year of fee payment: 7

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

Ref country code: FR

Payment date: 20220120

Year of fee payment: 7

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: 20180606

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502016001128

Country of ref document: DE

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

Effective date: 20230114

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: 20230114

Ref country code: DE

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

Effective date: 20230801

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: 20230131