FR3147792B1 - Partie tournante d’un recepteur de turbomachine munie d’un dispositif d’antigivrage - Google Patents

Partie tournante d’un recepteur de turbomachine munie d’un dispositif d’antigivrage

Info

Publication number
FR3147792B1
FR3147792B1 FR2303612A FR2303612A FR3147792B1 FR 3147792 B1 FR3147792 B1 FR 3147792B1 FR 2303612 A FR2303612 A FR 2303612A FR 2303612 A FR2303612 A FR 2303612A FR 3147792 B1 FR3147792 B1 FR 3147792B1
Authority
FR
France
Prior art keywords
rotating part
cone
icing device
turbomachine
receiver equipped
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
FR2303612A
Other languages
English (en)
Other versions
FR3147792A1 (fr
Inventor
Emmanuel David Urbain Hoolodor
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 FR2303612A priority Critical patent/FR3147792B1/fr
Priority to PCT/FR2024/050471 priority patent/WO2024213850A2/fr
Publication of FR3147792A1 publication Critical patent/FR3147792A1/fr
Application granted granted Critical
Publication of FR3147792B1 publication Critical patent/FR3147792B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/20—Constructional features
    • B64C11/205—Constructional features for protecting blades, e.g. coating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/047—Heating to prevent icing
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/512—Hydrophobic, i.e. being or having non-wettable properties
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/608—Microstructure

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

TITRE : PARTIE TOURNANTE D’UN RECEPTEUR DE TURBOMACHINE MUNIE D’UN DISPOSITIF D’ANTIGIVRAGE Un aspect de l’invention concerne une partie tournante d’un récepteur de turbomachine (10) d’aéronef comprenant : un arbre de rotation (20) d’axe de rotation X,un cône (30) monté à une extrémité de l’arbre de rotation (20) et comportant une surface externe (30A) et une surface interne (30B), etune pluralité d’hélices (40) agencées à l’aval du cône (30), réparties circonférentiellement autour de l’axe de rotation X et comprenant chacune une surface amont (40A) et une surface aval (40B), La partie tournante d’un récepteur de turbomachine (10) comporte un dispositif d’antigivrage (60) du cône (30) et des hélices (40) comprenant un revêtement antigivre (64) superhydrophobe déposé sur la surface externe (30A) du cône (30), et au moins sur la surface amont (40A) des hélices (40). Figure à publier avec l’abrégé : Figure 2
FR2303612A 2023-04-12 2023-04-12 Partie tournante d’un recepteur de turbomachine munie d’un dispositif d’antigivrage Active FR3147792B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR2303612A FR3147792B1 (fr) 2023-04-12 2023-04-12 Partie tournante d’un recepteur de turbomachine munie d’un dispositif d’antigivrage
PCT/FR2024/050471 WO2024213850A2 (fr) 2023-04-12 2024-04-10 Partie tournante d'un recepteur de turbomachine munie d'un dispositif d'antigivrage

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2303612 2023-04-12
FR2303612A FR3147792B1 (fr) 2023-04-12 2023-04-12 Partie tournante d’un recepteur de turbomachine munie d’un dispositif d’antigivrage

Publications (2)

Publication Number Publication Date
FR3147792A1 FR3147792A1 (fr) 2024-10-18
FR3147792B1 true FR3147792B1 (fr) 2026-01-02

Family

ID=87137041

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2303612A Active FR3147792B1 (fr) 2023-04-12 2023-04-12 Partie tournante d’un recepteur de turbomachine munie d’un dispositif d’antigivrage

Country Status (2)

Country Link
FR (1) FR3147792B1 (fr)
WO (1) WO2024213850A2 (fr)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2756254B1 (fr) * 1996-11-27 1999-01-29 Eurocopter France Dispositif de chauffage d'un profil aerodynamique
US7938368B2 (en) * 2008-04-07 2011-05-10 United Technologies Corporation Nosecone ice protection system for a gas turbine engine
CN101704410A (zh) * 2009-12-03 2010-05-12 上海交通大学 用于飞机防冰除冰的纳米超疏水表面及其制备方法
US20160114883A1 (en) * 2014-10-23 2016-04-28 The Boeing Company Actively-controlled superhydrophobic surfaces
CN207111247U (zh) * 2017-06-13 2018-03-16 中国航发商用航空发动机有限责任公司 航空发动机自加热防冰系统

Also Published As

Publication number Publication date
FR3147792A1 (fr) 2024-10-18
WO2024213850A3 (fr) 2025-01-09
WO2024213850A2 (fr) 2024-10-17

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