EP3987155B1 - Verfahren zum beschichten einer leitschaufel einer turbomaschine und zugehörige leitschaufel - Google Patents

Verfahren zum beschichten einer leitschaufel einer turbomaschine und zugehörige leitschaufel Download PDF

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Publication number
EP3987155B1
EP3987155B1 EP20785773.1A EP20785773A EP3987155B1 EP 3987155 B1 EP3987155 B1 EP 3987155B1 EP 20785773 A EP20785773 A EP 20785773A EP 3987155 B1 EP3987155 B1 EP 3987155B1
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EP
European Patent Office
Prior art keywords
thickness
coating
grooved zone
zone
vane
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Active
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EP20785773.1A
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English (en)
French (fr)
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EP3987155A1 (de
Inventor
Célia Iglesias Cano
Vincent Marie Jacques Rémi De Carné-Carnavalet
Antoine Hubert Marie Jean Masson
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP3987155A1 publication Critical patent/EP3987155A1/de
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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/11—Two-dimensional triangular

Definitions

  • the invention relates to the general field of turbomachines.
  • the invention relates more particularly to a process for coating a turbine engine stator vane making it possible to optimize the aerodynamic performance of said vane.
  • the invention also relates to a stator vane provided with a coating.
  • a dual-flow turbomachine comprises, at its upstream end, an air inlet supplying a fan which delivers an annular air flow splitting into two flows.
  • Part of the flow is injected into a compressor which powers a turbine driving the fan.
  • the other part of the flow is injected into the atmosphere to provide part of the thrust of the turbomachine, after having passed through a ring of fixed blades arranged downstream of the fan.
  • the crown of fixed vanes called a rectifier (also known by the acronym OGV for “Outlet Guide Valve”), makes it possible to straighten the flow of air at the outlet of the fan in the secondary flow.
  • the stator vanes made of composite material, are manufactured using a known process called "RTM” (Resin Transfer Moulding).
  • the RTM process consists of injecting a liquid resin into layers of dry reinforcing fibers previously preformed to the shape of the blade and placed in a closed mold placed under vacuum. After the molding step, it is known to deposit a metallic reinforcement, in the form of a foil, on the leading edge of the blade in order to protect it from erosion and/or shocks. possible (birds, gravel, ice, sand, etc.). Alternatively, the metal reinforcement is placed on the layers of preformed reinforcing fibers during the step of injecting the resin.
  • a polymer coating with grooves is applied to surfaces exposed to airflow. These grooves are oriented in the flow direction of the air flow and make it possible to reduce the friction generated by the turbulent boundary layers on the surface of the blades exposed to the secondary flow.
  • the document EN 3041375 discloses an example of such a coating.
  • the presence of the grooves makes it possible to reduce between 5 and 10% of the drag of friction generated by the turbulent boundary layers, they can also lead to an increase in friction when it comes to laminar boundary layers.
  • the grooves can generate significant aerodynamic losses if they act on separated boundary layers or more generally on chaotic non-oriented flows.
  • the invention offers a solution to the problems mentioned above, making it possible to limit the friction of the air flow on the surface of a stator vane.
  • a first aspect of the invention relates to a process for coating a turbomachine stator vane comprising a root and a head, an extrados face and an intrados face interconnected by a leading edge and a trailing edge.
  • the aerodynamic performance of the blade is improved.
  • the coating process according to the invention makes it possible to obtain a stator vane having a grooved zone on the surfaces exposed to a turbulent flow and a substantially flat zone, i.e. the paint layer, on the surfaces exposed to a flow. laminar.
  • the presence of said zones on one of the surfaces of the blade makes it possible to reduce the frictional drag generated by the secondary flow during its passage over the exposed surfaces of the blade.
  • the fact that the paint layer is in the continuity of the grooved zone makes it possible to limit the steps in the surface transitions and therefore to limit the aerodynamic losses associated with the presence of such steps.
  • the steps consisting in completely covering the face of the blade with a polymer coating provided with grooves and then proceeding with the removal of the grooves on a determined zone of the polymer coating make it possible to simplify the integration of the polymer coating on the blade.
  • the fact of keeping part of the polymer coating, i.e. the non-grooved zone, on a zone where the grooves are not desired makes it possible to limit the quantity of paint necessary to fill the thickness of polymer coating previously removed. Thus, this makes it possible to reduce manufacturing costs as well as the risks of non-compliance due to the presence of the paint layer.
  • the coating process according to the first aspect of the invention may have one or more additional characteristics among the following, considered individually or according to all the technically possible combinations.
  • the step of removing the grooves is carried out by a sandblasting operation on a part of the polymer coating intended to form the non-grooved zone.
  • the sandblasting operation is carried out at a pressure greater than 2.5 bars.
  • the coating process comprises a step of depositing a protective film on a part of the polymer coating intended to form the grooved zone.
  • a second aspect of the invention relates to a turbomachine stator vane comprising a root and a head, an extrados face and an intrados face interconnected by a leading edge and a trailing edge.
  • stator vane according to the second aspect of the invention may have one or more additional characteristics among the following, considered individually or according to all the technically possible combinations.
  • the polymer coating is made of polyurethane.
  • the paint layer is made of polyurethane.
  • the paint layer extends over the extrados face, along the root of the blade.
  • the paint layer extends over the extrados face, along the leading edge.
  • the invention according to a third aspect relates to a turbomachine stator comprising at least one blade according to the second aspect of the invention.
  • FIG. 1 shows a schematic representation in longitudinal section of a bypass turbomachine 1.
  • a dual-flow turbomachine 1 has a longitudinal axis A and comprises an outer casing 10 inside which are arranged, from upstream to downstream, a fan 12, a low-pressure compressor 14, a high-pressure compressor 16, a chamber combustion chamber 18, a high pressure turbine 20, a low pressure turbine 22 and an exhaust cone 24.
  • An inner casing 28 is arranged in the outer casing 10, around the compressors 14 and 16, of the combustion chamber 18 and turbines 20 and 22.
  • a rectifier 30 extends downstream of the fan 12, between the inner 28 and outer 10 casings, in the region of the compressors 14 and 16.
  • the inner casing 28 divides the flow of air accelerated by the fan 12 between a primary flow Fp which supplies the compressors 14 and 16, and a secondary flow Fs which flows between the inner 28 and outer 10 casings and is thus ejected from the turbomachine 1 after passing through the rectifier 30 to provide part of the thrust.
  • the rectifier 30, also designated by the acronym OGV for "Outlet Guide Vane" makes it possible to straighten the secondary flow Fs at the outlet of the fan 12 and comprises a plurality of fixed vanes 100 arranged in a crown around a ring 32 carried through the inner casing 28.
  • FIG. 2 illustrates a vane 100 of a stator 30 according to a first embodiment of the invention.
  • the blade 100 of the rectifier 30 has a leading edge 101, and a trailing edge 102, extending between a radially inner end 103, called the root of the blade 100, and a radially outer end 104, called the tip of the blade 100.
  • the leading edge 101 and the trailing edge 102 delimit an extrados face 105 and an intrados face 106.
  • the blade 100 is for example manufactured using a molding process called RTM for "Resin Transfer Moulding" during which a resin liquid, preferably of the epoxy type, is injected into layers of dry reinforcing fibers, in particular made of carbon, previously preformed substantially to the shape of the blade 100 and placed in a closed mold placed under vacuum.
  • RTM Resin Transfer Moulding
  • the leading edge 101 is covered with a metal reinforcement 112, for example made of Nickel-Cobalt alloy.
  • the metallic reinforcement 112 is preferably injected onto the preform in layers of reinforcing fibers during the injection of the liquid resin.
  • a film of adhesive is positioned between the metal reinforcement 112 and the preform in order to ensure the maintenance of the metal reinforcement 112 on the leading edge 101.
  • the extrados face 105 is completely covered with a polymer coating 107, for example polyurethane.
  • the polymer coating 107 is fixed to the extrados face by means of an adhesive applied to the leading edge 101.
  • a part 109 of the polymer coating 107 which will be called the grooved zone, comprises a plurality of grooves 108 provided at the level of the part of the blade 100 intended to be exposed to turbulent flows.
  • the grooved zone 109 of generally rectangular shape, is delimited by the head 104 of the blade 100 and the trailing edge 102 so as to cover approximately 75% of the extrados face 105.
  • the grooves 108 also called riblets, have a shape, for example a U-shaped or V-shaped section, and dimensions adapted to the flow conditions of said secondary flow Fs.
  • the grooved zone 109 of the polymer coating 107 has a thickness e1 of between 200 and 300 ⁇ m.
  • the other part 110 of the polymer coating 107 which will be called the non-grooved zone, is substantially flat and covers approximately 25% of the extrados face 105.
  • the non-grooved zone 110 extends along the foot 103 of blade 100 and along the metal reinforcement 112 so as to form an L.
  • the non-grooved zone 110 extends along the flow direction of the secondary flow Fs, ie for the portion which extends along the root 103 of the blade 100, and along a direction perpendicular to the direction of flow of the secondary flow Fs, ie for the portion which extends along the metal reinforcement 112.
  • the non-grooved zone 110 has a thickness e2 of between 100 and 200 ⁇ m.
  • the non-grooved area 110 is covered with a layer of paint 111, for example polyurethane, intended to be exposed to laminar flows.
  • the paint layer 111 has a thickness e3 such that when the paint layer 111 is applied to the non-grooved zone 110, the thickness of the paint layer 111 superimposed on the non-grooved zone 110 of the polymer coating 107 is substantially equal to the thickness e1 of the grooved zone 109 of the polymer coating 107.
  • the layer of paint 111 has a thickness e3 of between 80 and 120 ⁇ m.
  • the intrados face 106 is also covered with a polymer coating 107 and with a layer of paint 111 arranged on the surface of the blade 100 according to the flow conditions of the secondary flow Fs on the intrados face 106.
  • FIG. 3a is a block diagram illustrating the steps of the coating process 200 of the blade 100 of the stator 30 according to one embodiment of the invention. It should be noted that the coating process 200 according to the invention takes place after the manufacture of the blade 100 and the deposition of the metal reinforcement 112.
  • FIG. 3b illustrates part of the stages of the coating process schematized in picture 3a .
  • a polymer coating 107, of thickness e1, having grooves 108 is applied over the entire extrados face 105.
  • a film of glue is used to maintain the polymer coating 107 on the extrados face 105 of the dawn 100.
  • a part 109 of the polymer coating 107 is covered with a protective film, for example made of polymer material.
  • a third step 203 the grooves 108 present on the other part of the polymer coating 107, ie which is not covered by the protective film, are removed so as to obtain a non-grooved zone 110, of thickness e2, and a grooved zone 109.
  • the grooves 108 are removed by a sandblasting operation, preferably at a pressure greater than 2.5 bars.
  • a fourth step 204 the protective film is removed from part 109 of polymer coating 107.
  • the non-grooved zone 110 is coated with a layer of paint 111 of thickness e3 so that the thickness of the layer of paint 111 superimposed on the non-grooved zone 110 is substantially equal to the thickness e1 of the grooved zone 109.
  • the layer of paint 111 of thickness e3 can be obtained by applying one or more layers of paint to the non-grooved zone 110.
  • FIG. 4 illustrates a vane 100 of a stator 30 according to a second embodiment of the invention.
  • the blade 100 according to the second embodiment is identical to the blade 100 according to the first embodiment, except that the grooved 109 and non-grooved 110 zones are arranged in another way on the extrados face 105 of the dawn 100.
  • the grooved zone 109 has a generally rectangular shape and is delimited by the head 104 of the blade 100, the trailing edge 102 and the metal reinforcement 112 so as to cover approximately 75% of the extrados face 105.
  • the zone grooved 109 of the polymer coating 107 has a thickness e1 of between 200 and 300 ⁇ m.
  • the non-grooved zone 110 of generally rectangular shape extends only along the root 103 of the blade 100 so as to cover approximately 20% of the extrados face 105. In this configuration, the non-grooved zone 110 extends along only along the direction of flow of the secondary flow Fs.
  • the non-grooved zone 110 has a thickness e2 of between 100 and 200 ⁇ m.
  • the non-grooved zone 110 is also covered with a layer of paint 111 of thickness e3 so that the layer of paint 111 superimposed on the non-grooved zone 110 has a thickness substantially equal to the thickness e1 of the grooved zone 109.
  • the paint layer 111 has a thickness e3 of between 80 and 120 ⁇ m.
  • the vane 100 of the stator 30 according to the second embodiment is made using the coating process 200 described above.

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

Claims (10)

  1. Verfahren zum Beschichten (200) einer Schaufel (100) eines Gleichrichters (30) für eine Turbomaschine (1) mit einem Fuß (103) und einem Kopf (104), einer Rückseite (105) und einer Vorderseite (106), die durch eine Vorderkante miteinander verbunden sind und eine Hinterkante (102), wobei das Beschichtungsverfahren (200) dadurch gekennzeichnet ist, dass es die folgenden Schritte umfasst:
    - Vollständiges Bedecken (201) einer der Flächen (105, 106) der Schaufel (100) mit einer Polymerbeschichtung (107) der Dicke (e1), die mit Rillen (108) versehen ist,
    - Entfernen (203) der Rillen (108) an einem Teil der Polymerbeschichtung (107) derart, dass die Polymerbeschichtung (107) einen gerillten Bereich (109) und einen ungerillten Bereich (110) aufweist,
    - Beschichten (205) des nicht gerillten Bereichs (110) mit einer Farbschicht (111) mit einer Dicke (e3), so dass die Dicke der Farbschicht (111) auf dem nicht gerillten Bereich (110) im Wesentlichen der Dicke (e1) des gerillten Bereichs (109) entspricht.
  2. Beschichtungsverfahren (200) nach dem vorhergehenden Anspruch, dadurch gekennzeichnet, dass der Schritt des Entfernens (205) der Rillen (108) durch einen Sandstrahlvorgang an einem Teil der Polymerbeschichtung (107) durchgeführt wird, der dazu bestimmt ist, den nicht gerillten Bereich (110) zu bilden.
  3. Beschichtungsverfahren (200) nach dem vorhergehenden Anspruch, dadurch gekennzeichnet, dass der Sandstrahlvorgang mit einem Druck von mehr als 2,5 Bar durchgeführt wird.
  4. Beschichtungsverfahren (200) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass das Beschichtungsverfahren (200) vor dem Schritt des Entfernens (205) einen Schritt des Aufbringens (20) eines Schutzfilms auf einen Teil der Polymerbeschichtung (107) umfasst, der dazu bestimmt ist, die gerillte Zone (109) zu bilden.
  5. Schaufel (100) eines Gleichrichters (30) für eine Turbomaschine (1) mit einem Fuß (103) und einem Kopf (104), einer Rückseite (105) und einer Vorderseite (106), die durch eine Vorderkante (101) und eine Hinterkante (102) miteinander verbunden sind, wobei die Schaufel (100) dadurch gekennzeichnet ist, dass:
    - mindestens eine ihrer Seiten (105, 106) vollständig mit einer Polymerbeschichtung (107) bedeckt ist, die umfasst:
    ∘ einen gerillten Bereich (109) mit einer Dicke (e1),
    ∘ einen ungerillten Bereich (110) mit einer Dicke (e2), die geringer ist als die Dicke (e1) des gerillten Bereichs (109),
    - eine Farbschicht (111) mit einer Dicke (e3), die den ungerillten Bereich (110) bedeckt, so dass die Dicke der Farbschicht (111), die sich auf dem ungerillten Bereich (109) befindet, im Wesentlichen der Dicke (e1) des gerillten Bereichs (109) entspricht.
  6. Schaufel (100) eines Gleichrichters (30) nach dem vorhergehenden Anspruch, dadurch gekennzeichnet, dass die Polymerbeschichtung (107) aus Polyurethan besteht.
  7. Schaufel (100) eines Gleichrichters (30) nach einem der Ansprüche 5 bis 6, dadurch gekennzeichnet, dass die Farbschicht (111) aus Polyurethan besteht.
  8. Schaufel (100) eines Gleichrichters (30) nach einem der Ansprüche 5 bis 7, dadurch gekennzeichnet, dass sich die Farbschicht (111) auf der Rückseite (105) entlang des Fußes (103) der Schaufel (100) erstreckt.
  9. Schaufel (100) eines Gleichrichters (30) nach dem vorhergehenden Anspruch, dadurch gekennzeichnet, dass sich die Farbschicht (111) auf der Rückseite (105) entlang der Vorderkante (101) erstreckt.
  10. Gleichrichter (30) einer Turbomaschine (1), dadurch gekennzeichnet, dass er mindestens eine Schaufel (100) nach einem der Ansprüche 5 bis 9 aufweist.
EP20785773.1A 2019-06-20 2020-06-18 Verfahren zum beschichten einer leitschaufel einer turbomaschine und zugehörige leitschaufel Active EP3987155B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1906647A FR3097452B1 (fr) 2019-06-20 2019-06-20 Procédé de revêtement d’une aube de redresseur de turbomachine, aube de redresseur associée
PCT/FR2020/051055 WO2020254764A1 (fr) 2019-06-20 2020-06-18 Procédé de revêtement d'une aube de redresseur de turbomachine, aube de redresseur associée

Publications (2)

Publication Number Publication Date
EP3987155A1 EP3987155A1 (de) 2022-04-27
EP3987155B1 true EP3987155B1 (de) 2023-08-16

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EP20785773.1A Active EP3987155B1 (de) 2019-06-20 2020-06-18 Verfahren zum beschichten einer leitschaufel einer turbomaschine und zugehörige leitschaufel

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Country Link
US (1) US11898466B2 (de)
EP (1) EP3987155B1 (de)
CN (1) CN114008298B (de)
FR (1) FR3097452B1 (de)
WO (1) WO2020254764A1 (de)

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US3874901A (en) * 1973-04-23 1975-04-01 Gen Electric Coating system for superalloys
US4594761A (en) * 1984-02-13 1986-06-17 General Electric Company Method of fabricating hollow composite airfoils
US5337568A (en) * 1993-04-05 1994-08-16 General Electric Company Micro-grooved heat transfer wall
US6341747B1 (en) * 1999-10-28 2002-01-29 United Technologies Corporation Nanocomposite layered airfoil
FR2860741B1 (fr) * 2003-10-10 2007-04-13 Snecma Moteurs Procede de reparation de pieces metalliques notamment d'aubes de turbine de moteur a turbine a gaz
US20110129351A1 (en) * 2009-11-30 2011-06-02 Nripendra Nath Das Near net shape composite airfoil leading edge protective strips made using cold spray deposition
US20130146217A1 (en) * 2011-12-09 2013-06-13 Nicholas Joseph Kray Method of Applying Surface Riblets to an Aerodynamic Surface
WO2014152636A1 (en) * 2013-03-15 2014-09-25 United Technologies Corporation Selective coating removal or masking for ground path
US10294803B2 (en) * 2015-03-26 2019-05-21 General Electric Company Compositions and methods of deposition of thick environmental barrier coatings on CMC blade tips
US10100656B2 (en) * 2015-08-25 2018-10-16 General Electric Company Coated seal slot systems for turbomachinery and methods for forming the same
FR3041375B1 (fr) * 2015-09-22 2020-01-17 Safran Aircraft Engines Ensemble de circulation d'un flux d'un turboreacteur d'un aeronef
US10450867B2 (en) * 2016-02-12 2019-10-22 General Electric Company Riblets for a flowpath surface of a turbomachine
CN108843402A (zh) * 2018-06-08 2018-11-20 南京赛达机械制造有限公司 一种耐高温钛合金汽轮机叶片

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EP3987155A1 (de) 2022-04-27
US20220235666A1 (en) 2022-07-28
FR3097452B1 (fr) 2021-05-21
US11898466B2 (en) 2024-02-13
CN114008298B (zh) 2023-06-30
FR3097452A1 (fr) 2020-12-25
WO2020254764A1 (fr) 2020-12-24
CN114008298A (zh) 2022-02-01

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