EP3315721B1 - Verstärkung der vorderkante einer laufradschaufel einer strömungsmaschine - Google Patents

Verstärkung der vorderkante einer laufradschaufel einer strömungsmaschine Download PDF

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Publication number
EP3315721B1
EP3315721B1 EP17197595.6A EP17197595A EP3315721B1 EP 3315721 B1 EP3315721 B1 EP 3315721B1 EP 17197595 A EP17197595 A EP 17197595A EP 3315721 B1 EP3315721 B1 EP 3315721B1
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Prior art keywords
blade
point
fin
radially outer
edge
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EP17197595.6A
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English (en)
French (fr)
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EP3315721A1 (de
Inventor
Jean-Louis Romero
Jean-François FREROT
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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    • 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
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • F01D5/288—Protective coatings for 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • 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
    • 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
    • F04D29/38—Blades
    • F04D29/388—Blades characterised by construction
    • 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
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan 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
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/174—Titanium alloys, e.g. TiAl

Landscapes

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

Claims (5)

  1. Turbomaschinenschaufel (8), die sich entlang einer Längsachse (A) der Turbomaschine erstreckt, mit einer aerodynamischen Oberfläche an der Oberseite (28) und einer aerodynamischen Oberfläche an der Unterseite (30), die sich in einer ersten Richtung zwischen einer Vorderkante (8a) und einer Hinterkante (8b), und in einer zweiten Richtung im Wesentlichen senkrecht zur ersten Richtung zwischen einem Fuß (8c) und einem Scheitelpunkt (8d) der Schaufel (8) erstrecken, und mit einer Vorderkantenverstärkung (32), die einen Flügel an der Oberseite (32a), der teilweise die obere aerodynamische Oberfläche (28) bedeckt, und einen Flügel an der an der Unterseite (32b), der teilweise die aerodynamische Oberfläche (30) an der Unterseite der Schaufel (8) bedeckt, umfasst, wobei der Flügel an der Oberseite (32a) eine radial äußere Kante (34) aufweist, die in der Nähe des Scheitelpunkts (8d) der Schaufel (8) angeordnet ist und sich von der Vorderkante (8a) zur Hinterkante (8b) erstreckt, wobei diese radial äußere Kante (34) einen stromaufwärts gelegenen Punkt (34a) umfasst, der mit dem Scheitelpunkt (8d) der Schaufel (8) an der Vorderkante bündig ist, und einen stromabwärts gelegenen Punkt (34b), der radial vom Scheitelpunkt (8d) der Schaufel (8) entfernt ist, wobei sich der stromaufwärtige Punkt am stromaufwärtigen Ende der oberen Kante und der stromabwärtige Punkt am stromabwärtigen Ende der radial äußeren Kante des Flügels befindet und diese radial äußere Kante (34) einen Zwischenpunkt (34c) umfasst, der zwischen dem stromaufwärtigen Punkt (34a) und dem stromabwärtigen Punkt (34b) angeordnet ist, mit dem stromaufwärtigen Punkt (34a), der bündig mit dem Scheitelpunkt (8d) der Schaufel (8) ist, und mit dem stromabwärtigen Punkt (34b) einen ersten Abschnitt (36) der radial äußeren Kante (34) abgrenzt, dadurch gekennzeichnet, dass sich ein zweiter Abschnitt (38) der radial äußeren Kante (34) vom Scheitelpunkt (8d) der Schaufel (8) zum stromabwärtigen Punkt (34b) weg bewegt, um das Eindringen des Flügels (32a, 32b) in eine innere verschleißbare Schicht der Turbomaschine im Falle einer Ablösung des stromabwärtigen Punkts (34b)zu begrenzen, wobei der Zwischenpunkt (34c) in Längsrichtung in gleichem Abstand zum stromaufwärtigen Punkt (34a) und zum stromabwärtigen Punkt (34b) angeordnet ist, wobei der Zwischenpunkt (34c) und der stromabwärtige Punkt (34b) durch einen Abstand (Hl) voneinander getrennt sind, der entlang einer Mittellängsachse (M) des Flügels gemessen wird, d.h. in radialer Richtung (Z), die zwischen 0 und sinα × L ÷4 beträgt,
    wo:
    - L/2 die Länge zwischen dem stromaufwärts gelegenen Punkt (34a) und dem Zwischenpunkt (34c) ist, und
    - α der Winkel ist, der zwischen einer durch den stromaufwärtigen Punkt (34a) und den Zwischenpunkt (34c) der radial äußeren Kante (34) verlaufenden Linie und einer Tangente (T) an der radial äußeren Kante (34) gemessen wird, die parallel zur Längsachse (A) verläuft und durch den Zwischenpunkt (34c) führt.
  2. Schaufel (8) nach einem der vorhergehenden Ansprüche, in welcher der zweite Abschnitt (38) der radial äußeren Kante (34) des Flügels (32a, 32b) konvex gekrümmt ist.
  3. Schaufel (8) nach einem der vorhergehenden Ansprüche, in welcher die Vorderkantenverstärkung (32) aus einem metallischen Werkstoff hergestellt ist.
  4. Anordnung (4) mit einer zentralen Scheibe (6), auf der eine Vielzahl von Schaufeln (8) nach einem der vorhergehenden Ansprüche montiert sind, wobei die Schaufeln (8) gleichmäßig um den Umfang (6a) der zentralen Scheibe (6) verteilt sind und sich im wesentlichen radial in Bezug auf die zentrale Scheibe (6) erstrecken.
  5. Turbomaschine (2) mit einer Baugruppe (4) nach Anspruch 6.
EP17197595.6A 2016-10-28 2017-10-20 Verstärkung der vorderkante einer laufradschaufel einer strömungsmaschine Active EP3315721B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1660479A FR3058181B1 (fr) 2016-10-28 2016-10-28 Renfort de bord d'attaque d'une aube de turbomachine

Publications (2)

Publication Number Publication Date
EP3315721A1 EP3315721A1 (de) 2018-05-02
EP3315721B1 true EP3315721B1 (de) 2022-03-02

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ID=58314355

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EP17197595.6A Active EP3315721B1 (de) 2016-10-28 2017-10-20 Verstärkung der vorderkante einer laufradschaufel einer strömungsmaschine

Country Status (4)

Country Link
US (1) US10316669B2 (de)
EP (1) EP3315721B1 (de)
CN (1) CN108005730B (de)
FR (1) FR3058181B1 (de)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108454829A (zh) * 2018-05-30 2018-08-28 安徽卓尔航空科技有限公司 一种螺旋桨叶片
FR3085300B1 (fr) * 2018-08-31 2022-01-21 Safran Aircraft Engines Aube en materiau composite a film anti-erosion renforce et procede de protection associe
US10746045B2 (en) 2018-10-16 2020-08-18 General Electric Company Frangible gas turbine engine airfoil including a retaining member
US10837286B2 (en) 2018-10-16 2020-11-17 General Electric Company Frangible gas turbine engine airfoil with chord reduction
US11434781B2 (en) 2018-10-16 2022-09-06 General Electric Company Frangible gas turbine engine airfoil including an internal cavity
US10760428B2 (en) 2018-10-16 2020-09-01 General Electric Company Frangible gas turbine engine airfoil
US11149558B2 (en) 2018-10-16 2021-10-19 General Electric Company Frangible gas turbine engine airfoil with layup change
US11111815B2 (en) 2018-10-16 2021-09-07 General Electric Company Frangible gas turbine engine airfoil with fusion cavities
FR3103215B1 (fr) 2019-11-20 2021-10-15 Safran Aircraft Engines Aube de soufflante rotative de turbomachine, soufflante et turbomachine munies de celle-ci
FR3115079B1 (fr) * 2020-10-12 2022-10-14 Safran Aircraft Engines Aube en materiau composite comprenant un bouclier de bord d’attaque, turbomachine comprenant l’aube

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GB1304678A (de) * 1971-06-30 1973-01-24
US5908285A (en) * 1995-03-10 1999-06-01 United Technologies Corporation Electroformed sheath
JP4390026B2 (ja) * 1999-07-27 2009-12-24 株式会社Ｉｈｉ 複合材翼
US7736130B2 (en) * 2007-07-23 2010-06-15 General Electric Company Airfoil and method for protecting airfoil leading edge
US8858182B2 (en) * 2011-06-28 2014-10-14 United Technologies Corporation Fan blade with sheath
FR2987867B1 (fr) * 2012-03-09 2016-05-06 Snecma Aube de turbomachine comportant un insert de protection de la tete de l'aube

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Also Published As

Publication number Publication date
CN108005730A (zh) 2018-05-08
US20180119551A1 (en) 2018-05-03
FR3058181A1 (fr) 2018-05-04
US10316669B2 (en) 2019-06-11
CN108005730B (zh) 2022-07-08
FR3058181B1 (fr) 2018-11-09
EP3315721A1 (de) 2018-05-02

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