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FR3098188B1 - Method of manufacturing a vortex generator for an aerodynamic wall of an aircraft comprising at least one protected leading edge - Google Patents

Method of manufacturing a vortex generator for an aerodynamic wall of an aircraft comprising at least one protected leading edge Download PDF

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Publication number
FR3098188B1
FR3098188B1 FR1907338A FR1907338A FR3098188B1 FR 3098188 B1 FR3098188 B1 FR 3098188B1 FR 1907338 A FR1907338 A FR 1907338A FR 1907338 A FR1907338 A FR 1907338A FR 3098188 B1 FR3098188 B1 FR 3098188B1
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FR
France
Prior art keywords
vortex generator
aircraft
leading edge
manufacturing
aerodynamic wall
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
FR1907338A
Other languages
French (fr)
Other versions
FR3098188A1 (en
Inventor
Sandrine Andre
Erwan Krier
Oliveira Grégory De
Thomas Bourdieu
Adrien Bas
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.)
Airbus Operations SAS
Original Assignee
Airbus Operations 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 Airbus Operations SAS filed Critical Airbus Operations SAS
Priority to FR1907338A priority Critical patent/FR3098188B1/en
Publication of FR3098188A1 publication Critical patent/FR3098188A1/en
Application granted granted Critical
Publication of FR3098188B1 publication Critical patent/FR3098188B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
    • 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
    • Y02T50/10—Drag reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Procédé de fabrication d’un générateur de tourbillons pour une paroi aérodynamique d’un aéronef comprenant au moins un bord d’attaque protégé, générateur de tourbillons pour une paroi aérodynamique d’un aéronef comprenant moins un bord d’attaque protégé et aéronef équipé d’au moins un tel générateur de tourbillons L'invention a pour objet un procédé de fabrication d’un générateur de tourbillons (40) pour une paroi aérodynamique (42) d’un aéronef, ledit générateur de tourbillons présentant au moins un bord d’attaque (48), caractérisé en ce que le générateur de tourbillons (40) est réalisé en matériau composite et en ce que le procédé de fabrication comprend une étape de positionnement d’au moins un élément de protection (58) sur au moins une partie du bord d’attaque (48). Figure 6Method of manufacturing a vortex generator for an aerodynamic wall of an aircraft comprising at least one protected leading edge, vortex generator for an aerodynamic wall of an aircraft comprising at least one protected leading edge and aircraft equipped with 'at least one such vortex generator The subject of the invention is a method of manufacturing a vortex generator (40) for an aerodynamic wall (42) of an aircraft, said vortex generator having at least one edge of attack (48), characterized in that the vortex generator (40) is made of a composite material and in that the manufacturing process comprises a step of positioning at least one protective element (58) on at least a part of the leading edge (48). Figure 6

FR1907338A 2019-07-02 2019-07-02 Method of manufacturing a vortex generator for an aerodynamic wall of an aircraft comprising at least one protected leading edge Active FR3098188B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1907338A FR3098188B1 (en) 2019-07-02 2019-07-02 Method of manufacturing a vortex generator for an aerodynamic wall of an aircraft comprising at least one protected leading edge

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1907338 2019-07-02
FR1907338A FR3098188B1 (en) 2019-07-02 2019-07-02 Method of manufacturing a vortex generator for an aerodynamic wall of an aircraft comprising at least one protected leading edge

Publications (2)

Publication Number Publication Date
FR3098188A1 FR3098188A1 (en) 2021-01-08
FR3098188B1 true FR3098188B1 (en) 2021-10-29

Family

ID=68425044

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1907338A Active FR3098188B1 (en) 2019-07-02 2019-07-02 Method of manufacturing a vortex generator for an aerodynamic wall of an aircraft comprising at least one protected leading edge

Country Status (1)

Country Link
FR (1) FR3098188B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110194941A1 (en) * 2010-02-05 2011-08-11 United Technologies Corporation Co-cured sheath for composite blade
FR2978931B1 (en) * 2011-08-10 2014-05-09 Snecma METHOD FOR PRODUCING A PROTECTIVE REINFORCEMENT ON THE EDGE OF A BLADE
FR3008920B1 (en) * 2013-07-29 2015-12-25 Safran METHOD FOR MANUFACTURING A BLADE IN COMPOSITE MATERIAL WITH INTEGRATED METAL ATTACK FRAME FOR AERONAUTICAL GAS TURBINE ENGINE
US10723445B2 (en) * 2017-05-16 2020-07-28 Rohr, Inc. Strake for aircraft propulsion system nacelle

Also Published As

Publication number Publication date
FR3098188A1 (en) 2021-01-08

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