EP3399151B1 - Tôle de protection d'usure pour une aube mobile d'une turbine à gaz - Google Patents

Tôle de protection d'usure pour une aube mobile d'une turbine à gaz Download PDF

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Publication number
EP3399151B1
EP3399151B1 EP18162095.6A EP18162095A EP3399151B1 EP 3399151 B1 EP3399151 B1 EP 3399151B1 EP 18162095 A EP18162095 A EP 18162095A EP 3399151 B1 EP3399151 B1 EP 3399151B1
Authority
EP
European Patent Office
Prior art keywords
blade root
rotor
axial
securing
rotor blade
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
EP18162095.6A
Other languages
German (de)
English (en)
Other versions
EP3399151A1 (fr
Inventor
Martin Pernleitner
Rudolf Stanka
Manfred Dopfer
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 EP3399151A1 publication Critical patent/EP3399151A1/fr
Application granted granted Critical
Publication of EP3399151B1 publication Critical patent/EP3399151B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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
    • 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
    • F04D29/324—Blades
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • 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 present invention relates to a wear protection plate for a blade root of a blade of a gas turbine, in particular an aircraft gas turbine, with a base and two side walls connected to the base, the side walls lying opposite one another and being shaped such that they are essentially complementary to an outer contour of a blade root in question are formed, and wherein the wear protection plate is set up to be received in an installed state between the relevant blade root and a blade root receptacle of a rotor, in particular between the relevant blade root and an axial securing element arranged in the blade root receptacle.
  • the wear protection plate serves in particular to avoid wear on the blade root and on the blade root receptacle, so that after a certain running time of the gas turbine, as a rule only the wear protection plates have to be replaced.
  • the object of the invention is to provide a wear protection plate in which the installation is improved so that damage to the wear protection plate can be prevented.
  • the side walls of the wear protection plate protrude at least at one of their axial ends with a respective side end section over an axial end region of the base, and that a guide section adjoins the axial end region of the base, starting from the base in the direction of the base axial side end portion of the side walls is bent.
  • the guide section facilitates insertion into the blade root receptacle.
  • the wear protection plate can also axially protrude beyond the rotor disk and / or in a groove, in particular Axial groove, the blade root picked up the rotor disc can be prevented.
  • the wear protection plate can be arranged completely within the disc groove and, at the same time, the blade root can be axially flush with the rotor disc on one or both sides without the wear protection plate even protruding in sections over the blade root and / or over the rotor disc.
  • the guide section is bent in such a way that it has essentially the same curvature as a blade root region that comes into contact or is in contact with the guide section.
  • the guide section can have a projected length which corresponds approximately to 0.75 to 1.0 times a radius with which the guide section is bent. As a result, the guide section does not project in the axial direction beyond the axial ends of the side end sections.
  • the guide section can be arranged on an axial insertion of the blade root in such a way that the wear protection plate and the associated blade root can be displaced together in the axial insertion direction relative to the relevant blade root receptacle of the rotor. Due to the above-mentioned interlocking connection or interlocking contact with one another, the wear protection plate is carried along by the rotor blade root when the rotor blade is inserted.
  • the guide section acts as a kind of tab, which rests on the blade root, so that the entire wear protection plate can be moved when the blade root is inserted in the axial direction.
  • the guide section is in particular set up to act when the rotor blade is installed in the rotor. When removing a rotor blade from the rotor, the guide section has no effect and the blade root can be moved separately from the wear protection plate in the axial direction of removal.
  • a rotor for a gas turbine in particular an aircraft gas turbine, with a rotor base body, in particular a rotor blade disk, in which at least one rotor blade root receptacle is formed, in which a rotor blade root of an associated rotor blade is arranged and secured by means of an axial securing element, and with a wear protection plate with a base and two side walls connected to the base, the side walls lying opposite one another in the circumferential direction and being shaped such that they are essentially complementary to an outer contour of the blade root, and wherein the wear protection plate is set up in one installed state between the relevant blade root and the axial securing element, it being proposed that the side walls of the wear protection plate have at least one of their axial ends with a respective Se protrude itenendabterrorism over an axial end portion of the base and adjoins the axial end portion of the base, a guide portion which is bent starting from the base in the direction of the axial side
  • the axial securing element can have a first securing section and a second securing section which are connected to one another by a securing base, the first securing section being designed such that it forms a first stop for the moving blade root in the axial direction, the first securing section and the securing base by a curved section are connected to one another, and the guide section being arranged in the region of the curvature section between the rotor blade root and the axial securing element.
  • first securing section and the securing base are oriented essentially orthogonally to one another, so that the curvature section has an arc length that essentially corresponds to ⁇ / 2 rad, the arc length of the guide section of the wear protection plate being smaller than ⁇ / 2 rad and greater is equal to or equal to ⁇ / 4 rad.
  • the choice of the arc length of the guide section in the specified area can ensure that there is sufficient positive engagement between the guide section and the blade root. This also prevents the guide section from lying in the region of the first securing section between the moving blade root and the first securing section. This ensures direct contact of the blade root with the first securing section.
  • the second securing section of the axial securing element can be designed such that it forms a second stop for the axial securing element on the rotor base body.
  • the axial securing element can be inserted into the blade root receptacle in the axial direction of installation up to the second stop.
  • the first securing section can extend radially outward and the second securing section can extend radially inward.
  • the invention also relates to a gas turbine, in particular an aircraft gas turbine with at least one rotor described above.
  • the rotor can be assigned to the compressor or the turbine, in particular a high-speed turbine or low-pressure turbine.
  • Fan rotating means that the turbine is coupled to the fan via a gearbox and rotates faster than the fan during operation.
  • Low pressure means that there is at least one further turbine downstream of the combustion chamber, which turbine is arranged upstream of the low pressure turbine.
  • Fig. 1 shows in a schematic and greatly simplified sectional view in the sectional plane spanned by the radial direction RR and circumferential direction UR a blade root 10 of a blade not otherwise shown.
  • the blade root 10 is received in a blade root receptacle 12 of a rotor 14.
  • the rotor 14 can be designed as a rotor disk and a plurality of rotor blade root receptacles 12 can be formed along its outer circumference, so that an entire rotor blade ring can be provided for the gas turbine.
  • the blade root 10 has an outer contour 16 which is arranged in an inner contour 18 of the blade root receptacle.
  • the outer contour 16 and the inner contour 18 are essentially complementary to one another.
  • the blade root 10 is in the blade root receptacle 12 in the axial direction AR (substantially orthogonal to the cutting plane of the Fig. 1 ) introduced or removed from this.
  • the axial direction AR corresponds to the direction of the rotor axis of rotation. It is pointed out that the shapes of the outer contour 16 and the inner contour 18 shown are purely qualitative. In particular, the distances or gaps shown between these two contours 16, 18 can also be embodied differently, for example smaller than shown.
  • a wear protection plate 20 can be arranged between the blade root 10 and the blade holder 12.
  • Such a wear protection plate 20 is indicated purely qualitatively by a dashed line. It should be noted that the dashed line is not to be understood to mean that the wear protection plate 20 is an intermittent component. Rather, the wear protection plate refers to the sectional view of FIG Fig. 1 usually an uninterrupted volume of material.
  • the wear protection plate 20 has a shape that is essentially complementary to the blade root 10, in particular complementary to a radially inner region of the blade root 10. From the schematic sectional view of FIG Fig. 1 it can also be seen that the wear protection plate 20 is generally not formed along an entire radial height of the blade root 10.
  • Fig. 2 shows a simplified and schematic perspective view of an embodiment of a wear protection plate 20.
  • the wear protection plate comprises a base 22 and two side walls 24a, 24b.
  • the base 22 and the side walls 24a, 24b can be formed in one piece with one another.
  • the wear protection plate 20 can in particular be formed from a single machined, for example stamped and bent, piece of metal.
  • the side walls 24a, 24b are designed or have an outer shape which is adapted to an outer contour of a blade root (not shown here).
  • the Fig. 1 referenced, in which the side walls 24a, 24b and the base 22 are also designated for the sake of completeness, even if the Fig. 1 not exactly the embodiment of the Fig. 2 shows.
  • the base 22 extends essentially in the axial direction AR and in the circumferential direction UR.
  • the base 22 is formed as a surface in the plane that is spanned by the axial direction AR and the circumferential direction UR (or a tangential direction to the circumferential direction).
  • the base 22 does not necessarily have to be a flat surface, it can also have a curvature in part or in total, for example it can have a shape that is convex radially inward.
  • a guide section 28 is arranged at an axial end or end section 26 of the base 22.
  • the guide section 28 can also be formed in one piece with the base 22.
  • the guide section 28 has a curved or curved shape.
  • the Curvature is concave on the side facing the blade root.
  • the guide section 28 is bent in the direction of the side walls 24a, 24b, in particular in the direction of their side end sections 30a, 30b. Relative to an installation position on a rotor, the guide section 28 is bent radially outward.
  • the side end portions 30a, 30b project in the axial direction AR over the end portion 26 of the base 22.
  • Fig. 3 shows a side plan view of the side wall 24b.
  • the guide section 28 can also be seen in this figure. Since the side end sections 30a, 30b project axially beyond the base 22, it is possible to deform, in particular bend, the guide section 28, which also forms a kind of free end of the base 20. From the Fig. 3 it can also be seen that the guide section 28 is provided in the embodiment only at one axial end of the wear protection plate 20. This axial end can also be referred to as the introducer 32. The opposite axial end can be referred to as the executor 34 of the wear protection plate 20.
  • FIG. 4 An enlarged representation of the guide section 28 can be seen approximately corresponding to that in FIG Fig. 3 area labeled IV.
  • the blade root 10 is indicated by hatching for illustration.
  • the guide section 28 is bent such that its inner radius IR essentially corresponds to an outer radius of the blade root 10 in this area.
  • the blade root 10 bears directly and in the manner of a form fit on the guide section 28 of the wear protection plate 20.
  • the length of the guide section 28 lies in a region which is greater than or equal to 75% of the inner radius IR but is smaller than the inner radius IR or equal to the inner radius IR.
  • Fig. 5 shows a sectional view of the blade root 10, which is arranged or installed in the blade root receptacle 12 of the rotor 14.
  • the wear protection plate 20 is arranged between the blade root receptacle 12 and the blade root 10.
  • an axial securing element 40 is also shown in this example.
  • the axial securing element 40 is arranged between the wear protection plate 20 and the blade root receptacle 12.
  • the axial locking element 40 can also be referred to as an axial locking plate. It comprises a first securing section 42, which is set up to serve as the first axial stop or axial contact surface for the blade root 10.
  • the first securing section 42 is bent radially outward.
  • the axial securing element 40 further comprises a second securing section 44, which serves in particular to form a second axial stop on the rotor 14.
  • the second securing section 44 is bent radially outward. It should be noted that the second securing section 44 in FIG Fig. 5 is illustrated for the sake of clarity, without it being possible to conclude from this that the second securing section 44 must have exactly the shape shown. Rather, other configurations of the second securing section 44 are also conceivable.
  • the axial securing element 40 further comprises a securing base 46, which extends between the first securing section 42 and the second securing section 44, essentially along the axial direction AR.
  • the first securing section 42 is oriented essentially orthogonally to the securing base 46, in particular it extends essentially in the radial direction RR.
  • a transition between the first securing section 42 and the securing base 46 is formed by a curved section 48.
  • the curvature section 48 has an arc length which essentially corresponds to ⁇ / 2 rad.
  • the guide portion 28 of the wear protection plate is arranged or received.
  • the arc length of the guide section 28 of the wear protection plate 20 is less than ⁇ / 2 rad and greater than or equal to ⁇ / 4 rad.
  • the guide section 28 is dimensioned or bent or curved so that its free end 52 does not over the axial End 32 of the blade root 10 protrudes. This ensures that the guide section 28 of the wear protection plate 20 is not arranged or clamped in the area running essentially in the radial direction RR between the first securing section 42 and the rotor blade root 10. It can also be seen that the guide section 28 is dimensioned or bent or curved in such a way that a sufficient positive fit is ensured with the blade root 10, so that when the blade root 10 is inserted into the blade root receptacle 12 in the axial direction, the wear protection plate 20, if appropriate with the blade root 10 to his in the Fig. 5 illustrated end position is moved, in particular is moved relative to the axial securing element 40.
  • the insertion direction runs from right to left.
  • the guide section 28 thus serves in particular to ensure that the wear protection plate 20 can automatically be brought into a desired or correct position relative to the blade root receptacle 12 or to the axial securing element 40 when the blade root 10 is inserted. Accordingly, it can be prevented that the position of the wear protection plate 20 has to be corrected after the blade root 10 has been inserted, as a result of which the risk of damage to the wear protection plate 20 can be minimized and possibly even excluded.

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)

Claims (9)

  1. Tôle de protection contre l'usure (20) pour un pied d'aube mobile (10) d'une aube mobile d'une turbine à gaz, en particulier d'une turbine à gaz d'avion, comportant une base (22) et deux parois latérales (24a, 24b) reliées à la base (22), les parois latérales (24a, 24b) étant opposées et formées de manière à être sensiblement complémentaires à un contour extérieur (16) d'un pied d'aube mobile (10) concerné, et la tôle de protection contre l'usure (20) étant conçue pour être logée dans un état monté entre le pied d'aube mobile (10) concerné et un logement de pied d'aube mobile (12) d'un rotor (14), en particulier entre le pied d'aube mobile (10) concerné et un élément de fixation axial (40) disposé dans le logement de pied d'aube mobile (12), caractérisée en ce que les parois latérales (24a, 24b) font saillie à au moins l'une de leurs extrémités axiales par rapport à une section d'extrémité latérale (30a, 30b) respective par l'intermédiaire d'une section d'extrémité (26) axiale de la base (22) dans une direction qui correspond, lorsque la tôle de protection contre l'usure est montée, à la direction axiale de la turbine à gaz, et en ce qu'une section de guidage (28) est reliée à la zone d'extrémité (26) axiale de la base (22), laquelle section de guidage est incurvée dans la direction des sections d'extrémité latérales (30a, 30b) axiales des parois latérales (24a, 24b), à partir de la base (22).
  2. Tôle de protection contre l'usure selon la revendication 1, caractérisée en ce que la section de guidage (28) est incurvée de manière à présenter sensiblement la même courbure qu'une zone de pied d'aube mobile (50) venant en contact ou en contact avec la section de guidage (28).
  3. Tôle de protection contre l'usure selon la revendication 1 ou 2, caractérisée en ce que la section de guidage (28) a une longueur projetée par rapport à une projection dans la direction axiale (AR), laquelle longueur projetée correspond approximativement à 0,75 à 1,0 fois un rayon (IR) selon lequel la section de guidage (28) est incurvée.
  4. Rotor (14) pour une turbine à gaz, en particulier une turbine à gaz d'avion, comportant un corps de base de rotor, en particulier un disque d'aube mobile, dans lequel au moins un logement de pied d'aube mobile (12) est réalisé, un pied d'aube mobile (10) d'une aube mobile étant disposé dans ledit logement de pied d'aube mobile et fixé au moyen d'un élément de fixation axial (40), et comportant une tôle de protection contre l'usure (20) selon l'une des revendications précédentes.
  5. Rotor selon la revendication 4, caractérisé en ce que l'élément de fixation axial (40) comprend une première section de fixation (42) et une seconde section de fixation (44) reliées par une base de fixation (46), la première section de fixation (42) étant conçue de manière à former une première butée pour le pied d'aube mobile (10) dans la direction axiale (AR), la première section de fixation (42) et la base de fixation (46) étant reliées par une section de courbure (48), et la section de guidage (28) étant disposée dans la zone de la section de courbure (48) entre le pied d'aube mobile (10) et l'élément de fixation axial (40).
  6. Rotor selon la revendication 5, caractérisé en ce que la première section de fixation (42) et la base de fixation (46) sont alignées de manière sensiblement orthogonale l'une par rapport à l'autre, de sorte que la section de courbure (48) ait une longueur d'arc sensiblement égale à π/2 rad, la longueur d'arc de la section de guidage (28) de la tôle de protection contre l'usure (20) étant inférieure à π/2 rad et supérieure ou égale à π/4 rad.
  7. Rotor selon l'une des revendications 5 à 6, caractérisé en ce que la seconde section de fixation (44) de l'élément de fixation axial (40) est conçue de manière à former une seconde butée pour l'élément de fixation axial (40) au niveau du corps de base de rotor (14).
  8. Turbine à gaz, en particulier turbine à gaz d'avion, comportant au moins un rotor (14) selon l'une des revendications 4 à 7.
  9. Turbine à gaz selon la revendication 8, caractérisée en ce que le rotor (14) est associé à un compresseur ou à une turbine, en particulier à une turbine basse pression à rotation rapide.
EP18162095.6A 2017-05-03 2018-03-15 Tôle de protection d'usure pour une aube mobile d'une turbine à gaz Active EP3399151B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102017207445.0A DE102017207445A1 (de) 2017-05-03 2017-05-03 Verschleißschutzblech für eine Laufschaufel einer Gasturbine

Publications (2)

Publication Number Publication Date
EP3399151A1 EP3399151A1 (fr) 2018-11-07
EP3399151B1 true EP3399151B1 (fr) 2020-01-29

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Application Number Title Priority Date Filing Date
EP18162095.6A Active EP3399151B1 (fr) 2017-05-03 2018-03-15 Tôle de protection d'usure pour une aube mobile d'une turbine à gaz

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US (1) US10753213B2 (fr)
EP (1) EP3399151B1 (fr)
DE (1) DE102017207445A1 (fr)
ES (1) ES2775064T3 (fr)

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Publication number Priority date Publication date Assignee Title
DE102019210699A1 (de) * 2019-07-19 2021-01-21 MTU Aero Engines AG Zwischenelement für eine Schaufel-Rotorscheiben-Verbindung bei einem Rotor einer Strömungsmaschine und Rotor für eine Strömungsmaschine
FR3136507A1 (fr) * 2022-06-13 2023-12-15 Safran Aircraft Engines Dispositif de retenue axiale des aubes mobiles d’une turbine BP dans les alvéoles d’un disque de rotor de la turbine BP et procédé de montage de ces aubes mobiles
FR3139361B1 (fr) * 2022-09-01 2024-07-26 Safran Aircraft Engines Clinquant pour aube mobile de turbomachine, ensemble pour rotor comportant un tel clinquant et procédé de montage d’un tel ensemble

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DE889160C (de) * 1950-03-25 1953-09-07 Armstrong Siddeley Motors Ltd Schaufelbefestigung fuer Laeuferscheiben von Kreiselradmaschinen
US4207029A (en) * 1978-06-12 1980-06-10 Avco Corporation Turbine rotor assembly of ceramic blades to metallic disc
US6431835B1 (en) 2000-10-17 2002-08-13 Honeywell International, Inc. Fan blade compliant shim
FR2921409B1 (fr) * 2007-09-25 2009-12-18 Snecma Clinquant pour aube de turbomachine.
FR2951494B1 (fr) * 2009-10-15 2011-12-09 Snecma Clinquant pour aube de turbomachine.
EP2719864A1 (fr) 2012-10-12 2014-04-16 MTU Aero Engines GmbH Insert pour une connexion aube-disque pour un rotor d'une turbomachine et un rotor d'une turbomachine associé
EP2719865A1 (fr) 2012-10-12 2014-04-16 MTU Aero Engines GmbH Insert pour connexions aube-disque de turbomachines
US10415402B2 (en) * 2013-03-13 2019-09-17 United Technologies Corporation Blade wear pads and manufacture methods
DE102013214933A1 (de) 2013-07-30 2015-02-26 MTU Aero Engines AG Verfahren zum Montieren einer Gasturbinenschaufel in einer zugeordneten Aufnahme eines Rotorgrundkörpers
DE102013223583A1 (de) 2013-11-19 2015-05-21 MTU Aero Engines AG Schaufel-Scheiben-Verbund, Verfahren und Strömungsmaschine
FR3027071B1 (fr) * 2014-10-13 2019-08-23 Safran Aircraft Engines Procede d'intervention sur un rotor et clinquant associe

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Also Published As

Publication number Publication date
EP3399151A1 (fr) 2018-11-07
US20180320535A1 (en) 2018-11-08
ES2775064T3 (es) 2020-07-23
US10753213B2 (en) 2020-08-25
DE102017207445A1 (de) 2018-11-08

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