FR3106848B1 - Turbomachine blade with leading edge shield - Google Patents

Turbomachine blade with leading edge shield Download PDF

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Publication number
FR3106848B1
FR3106848B1 FR2001093A FR2001093A FR3106848B1 FR 3106848 B1 FR3106848 B1 FR 3106848B1 FR 2001093 A FR2001093 A FR 2001093A FR 2001093 A FR2001093 A FR 2001093A FR 3106848 B1 FR3106848 B1 FR 3106848B1
Authority
FR
France
Prior art keywords
blade
leading edge
turbomachine blade
edge shield
airfoil
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
FR2001093A
Other languages
French (fr)
Other versions
FR3106848A1 (en
Inventor
Guillaume Pascal Jean-Charles Gondre
Charles-Henri Claude Jacky Sullet
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR2001093A priority Critical patent/FR3106848B1/en
Publication of FR3106848A1 publication Critical patent/FR3106848A1/en
Application granted granted Critical
Publication of FR3106848B1 publication Critical patent/FR3106848B1/en
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
    • F01D5/12—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
    • 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
    • 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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

Aube de turbomachine avec bouclier de bord d’attaque Aube (16) de turbomachine, comprenant un pied d’aube (18) et une partie de pale à profil aérodynamique (22) avec un bord d’attaque (30), un bord de fuite (32), un extrados (36) et un intrados (34). La partie de pale à profil aérodynamique (22) s’étend en hauteur d’une jonction (41) avec le pied d’aube (18) jusqu’à un sommet d’aube (42), et comprend un bouclier (38) de bord d’attaque s’étendant, d’un bord inférieur (44) jusqu’à un bord supérieur (46) au sommet d’aube (42), sur seulement une partie de la hauteur (H) de la partie de pale à profil aérodynamique (22). Figure pour l’abrégé : Fig. 2.Turbomachine Blade with Leading Edge Shield A turbomachine blade (16) comprising a blade root (18) and an airfoil blade portion (22) with a leading edge (30), a leak (32), an extrados (36) and an intrados (34). The airfoil blade portion (22) extends in height from a junction (41) with the blade root (18) to a blade tip (42), and includes a shroud (38) of leading edge extending, from a lower edge (44) to an upper edge (46) at the tip of the blade (42), over only part of the height (H) of the blade part airfoil (22). Figure for abstract: Fig. 2.

FR2001093A 2020-02-04 2020-02-04 Turbomachine blade with leading edge shield Active FR3106848B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2001093A FR3106848B1 (en) 2020-02-04 2020-02-04 Turbomachine blade with leading edge shield

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2001093A FR3106848B1 (en) 2020-02-04 2020-02-04 Turbomachine blade with leading edge shield
FR2001093 2020-02-04

Publications (2)

Publication Number Publication Date
FR3106848A1 FR3106848A1 (en) 2021-08-06
FR3106848B1 true FR3106848B1 (en) 2022-08-19

Family

ID=71452343

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2001093A Active FR3106848B1 (en) 2020-02-04 2020-02-04 Turbomachine blade with leading edge shield

Country Status (1)

Country Link
FR (1) FR3106848B1 (en)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5725354A (en) * 1996-11-22 1998-03-10 General Electric Company Forward swept fan blade
US9289816B2 (en) * 2009-01-22 2016-03-22 Ihi Corporation Production method of leading edge reinforcement of fan blade
EP2843193B1 (en) * 2013-08-28 2020-08-12 Safran Aero Boosters SA Composite blade made by additive manufacturing and corresponding manufacturing process
ES2655799T3 (en) * 2014-03-03 2018-02-21 Airbus Helicopters Edge protection layer of aircraft wing elements
GB201512900D0 (en) * 2015-07-22 2015-09-02 Rolls Royce Plc Gas turbine engine
FR3045711B1 (en) 2015-12-21 2018-01-26 Safran Aircraft Engines ATTACK SHIELD

Also Published As

Publication number Publication date
FR3106848A1 (en) 2021-08-06

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