EP2983989A1 - Aircraft element requiring an anti-icing treatment - Google Patents

Aircraft element requiring an anti-icing treatment

Info

Publication number
EP2983989A1
EP2983989A1 EP14727579.6A EP14727579A EP2983989A1 EP 2983989 A1 EP2983989 A1 EP 2983989A1 EP 14727579 A EP14727579 A EP 14727579A EP 2983989 A1 EP2983989 A1 EP 2983989A1
Authority
EP
European Patent Office
Prior art keywords
edge section
nacelle
aircraft
superhydrophobic
aircraft element
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.)
Withdrawn
Application number
EP14727579.6A
Other languages
German (de)
French (fr)
Inventor
Audrey RIQUET
Caroline COAT-LENZOTTI
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 Nacelles SAS
Original Assignee
Aircelle SA
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 Aircelle SA filed Critical Aircelle SA
Publication of EP2983989A1 publication Critical patent/EP2983989A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/512—Hydrophobic, i.e. being or having non-wettable properties

Definitions

  • the present invention relates to the field of aircraft elements requiring treatment against frost.
  • An aircraft is propelled by one or more propulsion units each comprising a turbojet engine housed in a nacelle.
  • a nacelle generally has a substantially tubular structure surrounding the turbojet and comprises a leading edge section constituting an air inlet upstream of the engine and a trailing edge section comprising, from upstream to downstream of the nacelle, a median section intended to surround the blower of said turbojet and a downstream section surrounding the combustion chamber of the turbojet and which may be equipped with thrust reversal means, the upstream and downstream of the nacelle being defined by reference to the direction of flow of the air flow in the nacelle in direct jet operation, the upstream of the nacelle corresponding to a part of the nacelle through which the flow enters, and the downstream corresponding to an ejection zone of said air flow.
  • the air intake comprises, on the one hand, an inlet lip adapted to allow optimal capture to the turbojet of the air necessary to supply the blower and the internal compressors of the turbojet engine, and other on the other hand, a downstream structure to which the lip is attached and intended to properly channel the air towards the fan blades.
  • the assembly is attached upstream of a fan casing belonging to the middle section of the assembly.
  • aircraft elements with a leading edge are subject to ice accretion. This is for example the air intake lip of a nacelle, a radome, a leading edge of a wing or a horizontal or vertical empennage.
  • a defrosting device makes it possible periodically to clean the zone subjected to the formation of ice or gunk, typically by heating or by mechanical means, in order to remove said ice or frost, while an anti-ice device
  • the purpose of icing is to prevent the formation of ice or frost by continuously heating the area.
  • nacelle air inlet lip for turbojet or turboprop When the element of the aircraft to be treated against icing is a nacelle air inlet lip for turbojet or turboprop, such devices are, in known manner, made by drawing hot gases in the turbojet compressor or by producing them by compression or heating, and redirecting them on the surface of the air inlet lip of the nacelle.
  • such a device requires a hot air supply duct system between the turbojet engine or the turboprop engine and the air inlet, as well as a system for evacuating hot air inside the engine. air intake lip. This increases the mass of the propulsion unit, which is undesirable.
  • an electric de-icing or anti-icing device uses sets of heating resistors, implanted at the level of the air intake lip near the outer surface and electrically powered.
  • turbojet engines having an unducted fan downstream of the nacelle and to reduce fuel consumption, require treatment against frost on the one hand on the inner surface of the nacelle, and on the other hand on the surface external of said nacelle to prevent ice blocks from crossing the blades of the non-ttled fan.
  • the energy consumption of the frost treatment devices is thus further increased for this type of turbojet engine.
  • the present invention aims to overcome the aforementioned drawbacks, and relates for this purpose to an aircraft element comprising a leading edge section and a trailing edge section, said leading edge section comprising at least one device anti-icing device, said aircraft element being remarkable in that the trailing edge section comprises at least one superhydrophobic surface.
  • the water droplets from the deicing or anti-icing process from the leading edge section adhere more on the surface downstream of said leading edge section, and it is then avoided to refreeze the runoff, at least at the superhydrophobic surface.
  • the anti-icing device is an anti-icing device
  • the surface to be heated is reduced compared to that of the prior art, which makes it possible to reduce the energy consumption of said device and, when the Frost treatment device is a defrosting device, the frequency of heating cycles is reduced compared to that of the prior art, it also reduces the energy consumption of said device.
  • the superhydrophobic feature of the trailing edge section significantly reduces the energy consumption of said frost treatment device.
  • the aircraft element is a nacel for the aircraft turbojet or turboprop engine, the leading edge section comprising an air intake lip. and the trailing edge section comprising a middle section including an inner surface and a radially remote outer surface of said inner surface, said inner surface comprising at least one superhydrophobic surface.
  • the outer surface of the nacelle further comprises at least one superhydrophobic surface.
  • this nacelle is particularly intended to support a turbojet engine of the "Open Rotor" type, a turbojet engine whose fan is not faired and is positioned downstream of said turbojet engine;
  • the superhydrophobic surface is obtained by a surface treatment process.
  • surface treatment provides good erosion resistance.
  • cost of obtaining these perhydrophobic surfaces is very significantly reduced compared to obtaining hydrophobic surfaces by coatings;
  • the surface treatment process is preferably a method of pulverizing an organometallic complex. This method is advantageously applicable whatever the nature of the surface to be treated;
  • the superhydrophobic surface of the air inlet lip is obtained by chemical reaction between a fatty acid and said surface of the air intake lip.
  • This method is very advantageous with respect to the method of spraying an organometallic complex when the surface to be treated is a metal surface, such as the air intake lip of the nacelle;
  • the nacelle according to the invention can support a turbojet of the "Open Rotor" type.
  • Figure 1 shows a propellant assembly known from the prior art
  • Figure 2 is a longitudinal sectional view of the air inlet lip of the nacelle and a portion of the trailing edge section.
  • identical or similar references denote identical or similar members or sets of members.
  • aircraft element comprising a leading edge section and a trailing edge section any element of an aircraft having an aerodynamic profile.
  • such an aircraft element can be constituted by the wings of an aircraft, the rear tail (horizontal and vertical), turbojet engine nacelles or turboprop.
  • FIG. 1 showing a propulsion assembly 1.
  • Such an assembly comprises a pylon 3 to which is suspended a nacelle 5 supporting a turbojet engine 7.
  • the nacelle 5 comprises a leading edge section 9 constituted by an air inlet lip 10, and a trailing edge section 11 comprising a central section 1 3 of the nacelle constituted by a fixed hood 1 5, and a downstream section 1 7 of the nacelle constituted by a hood 1 9 can house the thrust reversal means.
  • FIG. 2 schematically illustrating, in longitudinal section, the air intake lip 10 extended by the cover 15 comprising an inner surface 21 in contact with a cold air flow F through the nacelle and an outer surface 23 radially remote from said inner surface.
  • the air inlet lip 10 is typically separated from the fixed hood 15 by an annular wall 25.
  • the air intake lip 10 receives a frost treatment device (not shown), consisting for example of a deicing or anti-icing device, pneumatic or electric.
  • a frost treatment device (not shown), consisting for example of a deicing or anti-icing device, pneumatic or electric.
  • the trailing edge section comprising the cover 15, positioned downstream of the zone of the heat-treated nacelle, is superhydrophobic.
  • the hydrophobic characterization of a material is done by measuring the contact angle between its flat surface and a drop of water placed on its surface: the standard materials have an angle of less than 90 °, the hydrophobic materials have a ng the com between 90 ° and 1 50 ° and superhydrophobic materials have an angle greater than 150 °.
  • At least a portion of the inner surface 21 of the cover 15 is superhydrophobic.
  • the inner surface 21 of the hood 15 of the nacelle is made superhydrophobic by any surface treatment method.
  • the method used to make the bucket perhydrophobic is a n process of spraying an organometallic complex on the surface to be treated.
  • the outer surface 23 of the cover 15 is also made superhydrophobic, for example by said organometallic sputtering method. This makes it possible to make the nacelle compatible with an "open rotor" type rboreactor, that is to say having an unsheathed fan at its downstream section.
  • the air inlet metal lip 10 of the nacelle is also superhydrophobic.
  • the air inlet lip can be made superhydrophobic by any surface treatment process.
  • the outer surface 27 of the air inlet lip 10 can be spray-treated with an organometallic complex or can be made superhydrophobic by reacting a fatty acid and said outer surface 27.
  • the perhydroophobic su the air intake lip makes it very advantageous to use a piezoelectric component deicing device.
  • Defrosting by piezoelectric component consists in vibrating the surface to be defrosted to break and evacuate the small layers of ice accumulated on the lip.
  • these surfaces are obtained by a surface treatment process. This advantageously makes it possible, unlike the hydrophobic coatings known from the prior art, to considerably increase the erosion resistance of the treated surface and to substantially reduce the cost of treating these surfaces.

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

Abstract

The present invention relates to an aircraft element including a leading edge section (9) and a trailing edge section (11), said leading edge section including at least one anti-icing treatment device. Said aircraft element is characterized in that the trailing edge section (11) includes at least one superhydrophobic surface (21, 23).

Description

Élément d'aéronef nécessitant un traitement contre le givre  Aircraft Element Requiring Frost Treatment
La présente invention concerne le domaine des éléments d'aéronefs nécessitant un traitement contre le givre. The present invention relates to the field of aircraft elements requiring treatment against frost.
Un aéronef est propulsé par un ou plusieurs ensemble propulsifs comprenant chacun un turboréacteur logé dans une nacelle.  An aircraft is propelled by one or more propulsion units each comprising a turbojet engine housed in a nacelle.
Une nacelle présente de manière générale une structure sensiblement tubulaire entourant le turboréacteur et comprend une section de bord d'attaque constituant une entrée d'air en amont du moteur et une section de bord de fuite comprenant, depuis l'amont vers l'aval de la nacelle, une section médiane destinée à entourer la soufflante dudit turboréacteur et une section aval entourant la chambre de combustion du turboréacteur et qui peut être équipée de moyens d'inversion de poussée, l'amont et l'aval de la nacelle étant définis par référence au sens d'écoulement du flux d'air dans la nacelle en fonctionnement jet direct, l'amont de la nacelle correspondant à une partie de la nacelle par laquelle le flux pénètre, et l'aval correspondant à une zone d'éjection dudit flux d'air.  A nacelle generally has a substantially tubular structure surrounding the turbojet and comprises a leading edge section constituting an air inlet upstream of the engine and a trailing edge section comprising, from upstream to downstream of the nacelle, a median section intended to surround the blower of said turbojet and a downstream section surrounding the combustion chamber of the turbojet and which may be equipped with thrust reversal means, the upstream and downstream of the nacelle being defined by reference to the direction of flow of the air flow in the nacelle in direct jet operation, the upstream of the nacelle corresponding to a part of the nacelle through which the flow enters, and the downstream corresponding to an ejection zone of said air flow.
L'entrée d'air comprend, d'une part, une lèvre d'entrée adaptée pour permettre la captation optimale vers le turboréacteur de l'air nécessaire à l'alimentation de la soufflante et des compresseurs internes du turboréacteur, et d'autre part, une structure aval sur laquelle est rapportée la lèvre et destinée à canaliser convenablement l'air vers les aubes de soufflante. L'ensemble est rattaché en amont d'un carter de soufflante appartenant à la section médiane de l'ensemble.  The air intake comprises, on the one hand, an inlet lip adapted to allow optimal capture to the turbojet of the air necessary to supply the blower and the internal compressors of the turbojet engine, and other on the other hand, a downstream structure to which the lip is attached and intended to properly channel the air towards the fan blades. The assembly is attached upstream of a fan casing belonging to the middle section of the assembly.
Lors d'une phase de vol d'un aéronef, il est fréquent que les conditions climatiques en altitude entraînent une formation de givre à différents endroits de l'aéronef.  During a flight phase of an aircraft, it is common that the climatic conditions at altitude cause frost formation at different locations on the aircraft.
D'une manière générale, les éléments d'aéronefs présentant un bord d'attaque sont sujets à l'accrétion de givre. Il s'agit par exemple de la lèvre d'entrée d'air d'une nacelle, d'un radôme, d'un bord d'attaque d'une aile ou d'un empennage horizontal ou vertical.  In general, aircraft elements with a leading edge are subject to ice accretion. This is for example the air intake lip of a nacelle, a radome, a leading edge of a wing or a horizontal or vertical empennage.
Par exemple, une telle formation de givre sur le bord d'attaque de la nacelle du turboréacteur est inacceptable, car elle peut entraîner des modifications du profil aérodynamique de la nacelle, ou peut aussi endommager le turboréacteur dans le cas d'arrachement de blocs de glace qui se sont formés en amont sur la lèvre d'entrée d'air de la nacelle. Afin d'éviter l'accumulation de glace ou de givre entraînant les inconvénients précités, on équipe généralement ces éléments de l'aéronef sujets à l'accrétion de givre ou de glace de dispositifs de dégivrage ou d'anti- givrage. For example, such a frost formation on the leading edge of the nacelle of the turbojet engine is unacceptable, since it may lead to changes in the aerodynamic profile of the nacelle, or may also damage the turbojet engine in the case of tearing of the engine blocks. ice that formed upstream on the air intake lip of the nacelle. In order to avoid the accumulation of ice or frost causing the aforementioned drawbacks, these elements of the aircraft subject to the accretion of frost or ice of deicing or anti-icing devices are generally equipped.
Un dispositif de dégivrage permet de nettoyer de façon périodique la zone assujettie à la formation de glace ou de g ivre, typiquement par chauffage ou par moyen mécanique, afin d'éliminer ladite glace ou ledit givre, tandis qu'un dispositif d'anti-givrage a pour but d'empêcher la formation de glace ou de givre en réchauffant continuellement ladite zone.  A defrosting device makes it possible periodically to clean the zone subjected to the formation of ice or gunk, typically by heating or by mechanical means, in order to remove said ice or frost, while an anti-ice device The purpose of icing is to prevent the formation of ice or frost by continuously heating the area.
Lorsque l'élément de l'aéronef à traiter contre le givre est une lèvre d'entrée d'air de nacelle pour turboréacteur ou turbopropulseur, de tels dispositifs sont, de manière connue, réalisés en prélevant des gaz chauds dans le compresseur du turboréacteur ou en les produisant par compression ou chauffage, et en les redirigeant sur la surface de la lèvre d'entrée d'air de la nacelle.  When the element of the aircraft to be treated against icing is a nacelle air inlet lip for turbojet or turboprop, such devices are, in known manner, made by drawing hot gases in the turbojet compressor or by producing them by compression or heating, and redirecting them on the surface of the air inlet lip of the nacelle.
Toutefois, un tel dispositif nécessite un système de conduits d'amenée d'air chaud entre le turboréacteur ou le turbopropulseur et l'entrée d'air, ainsi qu'un système d'évacuation de l'air chaud à l'intérieur de la lèvre d'entrée d'air. Ceci augmente la masse de l'ensemble propulsif, ce qui n'est pas souhaitable.  However, such a device requires a hot air supply duct system between the turbojet engine or the turboprop engine and the air inlet, as well as a system for evacuating hot air inside the engine. air intake lip. This increases the mass of the propulsion unit, which is undesirable.
Ces inconvénients ont pu être palliés en recourant à des systèmes de dégivrage ou d'anti-givrage électriques. On pourra notamment citer le document E P 1 845 018, bien que de nombreux autres documents se rapportent au dégivrage électrique et à ses développements.  These disadvantages could be overcome by using deicing or anti-icing systems. In particular, document E P 1 845 018 may be cited, although many other documents relate to electric de-icing and its developments.
La mise en œuvre d'un dispositif de dégivrage ou d'anti-givrage électrique utilise des ensembles de résistances chauffantes, implantés au niveau de la lèvre d'entrée d'air à proximité de la surface externe et alimentés électriquement.  The implementation of an electric de-icing or anti-icing device uses sets of heating resistors, implanted at the level of the air intake lip near the outer surface and electrically powered.
Cependant, que ce soit dans le cas de dispositifs de dégivrage ou d'antigivrage, pneumatique ou électrique, un inconvénient commun à ces dispositifs de traitement contre le g ivre est la consommation excessive d'énergie.  However, whether in the case of de-icing or anti-ice, pneumatic or electrical devices, a common disadvantage of these devices for treating drunkenness is the excessive consumption of energy.
De plus, les turboréacteurs du type « Open Rotor », turboréacteurs présentant une soufflante non carénée en aval de la nacelle et permettant de réduire la consommation de carburant, nécessitent un traitement contre le givre d'une part sur la surface intérieure de la nacelle, et d'autre part sur la surface extérieure de ladite nacelle afin d'éviter que des blocs de glace ne traversent les pales de la soufflante non carénée. La consommation en énergie des dispositifs de traitement contre le givre se trouve donc encore accrue pour ce type de turboréacteur. In addition, jet engines of the "Open Rotor" type, turbojet engines having an unducted fan downstream of the nacelle and to reduce fuel consumption, require treatment against frost on the one hand on the inner surface of the nacelle, and on the other hand on the surface external of said nacelle to prevent ice blocks from crossing the blades of the non-faired fan. The energy consumption of the frost treatment devices is thus further increased for this type of turbojet engine.
II existe donc un besoin de réduire considérablement la consommation énergétique de ces dispositifs de traitement contre le givre, sans en affecter les performances de dégivrage ou d'antigivrage.  There is therefore a need to significantly reduce the energy consumption of these anti-icing devices, without affecting deicing or anti-icing performance.
La présente invention vise à pallier les inconvénients précités, et se rapporte à cet effet à un élément d'aéronef comprenant une section de bord d'attaque et une section de bord de fuite, ladite section de bord d'attaque comprenant au moins un dispositif de traitement contre le givre, ledit élément d'aéronef étant remarquable en ce que la section de bord de fuite comprend au moins une surface superhydrophobe.  The present invention aims to overcome the aforementioned drawbacks, and relates for this purpose to an aircraft element comprising a leading edge section and a trailing edge section, said leading edge section comprising at least one device anti-icing device, said aircraft element being remarkable in that the trailing edge section comprises at least one superhydrophobic surface.
Ainsi, en prévoyant au moins une surface superhydrophobe en aval de la section équipée du dispositif de traitement contre le givre, les gouttelettes d'eau issues du processus de dégivrage ou d'anti-givrage provenant de la section de bord d'attaque n'adhèrent plus sur la surface en aval de ladite section de bord d'attaque, et on évite alors de recongeler le ruissellement, au moins au niveau de la surface superhydrophobe.  Thus, by providing at least one superhydrophobic surface downstream of the section equipped with the frost treatment device, the water droplets from the deicing or anti-icing process from the leading edge section adhere more on the surface downstream of said leading edge section, and it is then avoided to refreeze the runoff, at least at the superhydrophobic surface.
Par conséquent, lorsque le dispositif de traitement contre le givre est un dispositif d'anti-givrage, la surface à chauffer est réduite par rapport à celle de l'art antérieur, ce qui permet de réduire la consommation énergétique dudit dispositif et, lorsque le dispositif de traitement contre le givre est un dispositif de dégivrage, la fréquence de cycles de chauffe est diminuée par rapport à celle de l'art antérieur, ce qu i permet également de rédu ire la consommation en énergie dudit dispositif.  Therefore, when the anti-icing device is an anti-icing device, the surface to be heated is reduced compared to that of the prior art, which makes it possible to reduce the energy consumption of said device and, when the Frost treatment device is a defrosting device, the frequency of heating cycles is reduced compared to that of the prior art, it also reduces the energy consumption of said device.
Ainsi, quel que soit le type de dispositif de traitement contre le givre, la caractéristique superhydrophobe de la section de bord de fuite permet de réduire considérablement la consommation en énergie dudit dispositif de traitement contre le givre.  Thus, regardless of the type of frost treatment device, the superhydrophobic feature of the trailing edge section significantly reduces the energy consumption of said frost treatment device.
Selon un mode de réal isation préféré mais non l im itatif de l'invention, l'élément d'aéronef est une nacel le pour turboréacteu r ou turbopropulseur d'aéronef, la section de bord d'attaque comprenant une lèvre d'entrée d'air et la section de bord de fuite comprenant une section médiane comprenant une surface interne et une surface externe radialement éloignée de ladite surface interne, ladite surface interne comprenant au moins une surface superhydrophobe. According to a preferred but non-imitative embodiment of the invention, the aircraft element is a nacel for the aircraft turbojet or turboprop engine, the leading edge section comprising an air intake lip. and the trailing edge section comprising a middle section including an inner surface and a radially remote outer surface of said inner surface, said inner surface comprising at least one superhydrophobic surface.
Selon des caractéristiques toutes optionnelles de la présente invention :  According to all the optional features of the present invention:
- la surface externe de la nacelle comprend en outre au moins une surface superhydrophobe. En prévoyant une nacelle comprenant à la fois une surface interne et une surface externe superhydrophobes, cette nacelle est particulièrement destinée à supporter un turboréacteur du type « Open Rotor », turboréacteur dont la soufflante n'est pas carénée et est positionnée en aval dudit turboréacteur ;  - The outer surface of the nacelle further comprises at least one superhydrophobic surface. By providing a nacelle comprising both an inner surface and a superhydrophobic outer surface, this nacelle is particularly intended to support a turbojet engine of the "Open Rotor" type, a turbojet engine whose fan is not faired and is positioned downstream of said turbojet engine;
- la l èvre d ' en trée d ' a i r co m pre nd a u m oi ns u ne su rface superhydrophobe, ce qui permet d'adapter la nacelle avec un dispositif de dégivrage par composant piézo-électrique ;  - the l 'en d'en trée d'a i r co m pre nd u m o u ns u su superhydrophobic surface, which allows to adapt the nacelle with a defrosting device by piezoelectric component;
- la surface superhydrophobe est obtenue par un procédé de traitement de surface. Contrairement aux revêtements hydrophobes, le traitement de surface permet de présenter une bonne résistance à l'érosion. De plus, le coût d 'obtention de ces surfaces su perhydrophobes est très sensiblement réduit par rapport à l'obtention de surfaces hydrophobes par revêtements ;  the superhydrophobic surface is obtained by a surface treatment process. In contrast to hydrophobic coatings, surface treatment provides good erosion resistance. In addition, the cost of obtaining these perhydrophobic surfaces is very significantly reduced compared to obtaining hydrophobic surfaces by coatings;
- le procédé de traitement de surface est de préférence un procédé de pu lvérisation d'un complexe organométallique. Ce procédé s'applique avantageusement quelle que soit la nature de la surface à traiter ;  the surface treatment process is preferably a method of pulverizing an organometallic complex. This method is advantageously applicable whatever the nature of the surface to be treated;
- la surface superhydrophobe de la lèvre d'entrée d'air est obtenue par réaction chimique entre un acide gras et ladite surface de la lèvre d'entrée d'air. Ce procédé est très avantageux par raport au procédé de pulvérisation d'un complexe organométallique lorsque la surface à traiter est une surface métallique, telle que la lèvre d'entrée d'air de la nacelle ;  the superhydrophobic surface of the air inlet lip is obtained by chemical reaction between a fatty acid and said surface of the air intake lip. This method is very advantageous with respect to the method of spraying an organometallic complex when the surface to be treated is a metal surface, such as the air intake lip of the nacelle;
- la nacelle selon l'invention peut supporter un turboréacteur du type « Open Rotor ».  the nacelle according to the invention can support a turbojet of the "Open Rotor" type.
D'autres caractéristiques et avantages de la présente invention apparaîtront à la lecture de la description qui va suivre et à l'examen des figures ci-annexées, dans lesquelles : Other characteristics and advantages of the present invention will appear on reading the description which follows and on examining the appended figures, in which:
- La figure 1 représente un ensemble propulsif connu de l'art antérieur ; La figure 2 est une vue en coupe longitudinale de la lèvre d'entrée d'air de la nacelle et d'une partie de la section de bord de fuite. S u r l ' en sem bl e d es fig u res , d es référen ces id entiq u es ou analogues désignent des organes ou ensembles d'organes identiques ou analogues. - Figure 1 shows a propellant assembly known from the prior art; Figure 2 is a longitudinal sectional view of the air inlet lip of the nacelle and a portion of the trailing edge section. In other respects, identical or similar references denote identical or similar members or sets of members.
Dans la présente description, on entend par élément d'aéronef comprenant une section de bord d'attaque et une section de bord de fuite tout élément d'un aéronef présentant un profil aérodynamique. In this description, the term aircraft element comprising a leading edge section and a trailing edge section any element of an aircraft having an aerodynamic profile.
A titre d'exemple, un tel élément d'aéronef peut être constitué par les ailes d'un avion , les empennages arrières (horizontal et vertical), les nacelles de turboréacteur ou turbopropulseur.  For example, such an aircraft element can be constituted by the wings of an aircraft, the rear tail (horizontal and vertical), turbojet engine nacelles or turboprop.
Dans la suite de la description , on a choisi de se référer, à titre d'exemple illustratif non limitatif, à une nacelle pour turboréacteur d'aéronef.  In the remainder of the description, reference is made, by way of non-limiting illustrative example, to a nacelle for an aircraft turbojet engine.
On se réfère à la figure 1 , représentant un ensemble propulsif 1 . Un tel ensemble comprend un pylône 3 auquel est suspendue une nacelle 5 supportant un turboréacteur 7.  Referring to Figure 1, showing a propulsion assembly 1. Such an assembly comprises a pylon 3 to which is suspended a nacelle 5 supporting a turbojet engine 7.
La nacelle 5 comprend une section de bord d'attaque 9 constituée par une lèvre d'entrée d'air 10, et une section de bord de fuite 1 1 comprenant une section médiane 1 3 de la nacelle constituée par un capot fixe 1 5, et une section aval 1 7 de la nacelle constituée par un capot 1 9 pouvant abriter des moyens d'inversion de poussée.  The nacelle 5 comprises a leading edge section 9 constituted by an air inlet lip 10, and a trailing edge section 11 comprising a central section 1 3 of the nacelle constituted by a fixed hood 1 5, and a downstream section 1 7 of the nacelle constituted by a hood 1 9 can house the thrust reversal means.
On se réfère à la figure 2, illustrant schématiquement, en coupe longitudinale, la lèvre d'entrée d'air 1 0 prolongée par le capot 15 comprenant une surface interne 21 en contact avec un fl ux d'a ir froid F traversant la nacelle, et une surface externe 23 radialement éloignée par rapport à ladite surface interne.  Referring to Figure 2, schematically illustrating, in longitudinal section, the air intake lip 10 extended by the cover 15 comprising an inner surface 21 in contact with a cold air flow F through the nacelle and an outer surface 23 radially remote from said inner surface.
Comme représenté, la lèvre d'entrée d'air 10 est typiquement séparée du capot fixe 15 par une paroi annulaire 25.  As shown, the air inlet lip 10 is typically separated from the fixed hood 15 by an annular wall 25.
La lèvre d'entrée d'air 10 reçoit un dispositif de traitement contre le givre (non représenté), constitué par exemple par un dispositif de dégivrage ou d'antigivrage, pneumatique ou électrique. Selon l'invention, la section de bord de fuite comprenant le capot 15, positionné en aval de la zone de la nacelle traitée thermiquement, est superhydrophobe. The air intake lip 10 receives a frost treatment device (not shown), consisting for example of a deicing or anti-icing device, pneumatic or electric. According to the invention, the trailing edge section comprising the cover 15, positioned downstream of the zone of the heat-treated nacelle, is superhydrophobic.
La caractérisation hydrophobique d'un matériau se fait en mesurant l'angle de contact entre sa surface plane et une goutte d'eau posée sur sa surface : les matériaux standards ont un angle inférieur à 90°, les matériaux hyd rophobes ont u n a ng l e com pris entre 90° et 1 50° et les matériaux superhydrophobes ont un angle supérieur à 150°.  The hydrophobic characterization of a material is done by measuring the contact angle between its flat surface and a drop of water placed on its surface: the standard materials have an angle of less than 90 °, the hydrophobic materials have a ng the com between 90 ° and 1 50 ° and superhydrophobic materials have an angle greater than 150 °.
Plus précisément, au moins une portion de la surface interne 21 du capot 15 est superhydrophobe.  More specifically, at least a portion of the inner surface 21 of the cover 15 is superhydrophobic.
La surface interne 21 du capot 15 de la nacelle est rendue superhydrophobe par tout procédé de traitement de surface.  The inner surface 21 of the hood 15 of the nacelle is made superhydrophobic by any surface treatment method.
A titre d'exemple non limitatif, le procédé utilisé pour rendre la nacelle su perhydrophobe est u n procédé de pulvérisation d'un complexe organométallique sur la surface à traiter.  By way of non-limiting example, the method used to make the bucket perhydrophobic is a n process of spraying an organometallic complex on the surface to be treated.
Selon une variante, la surface externe 23 du capot 15 est également rendue superhydrophobe par exemple par ledit procédé de pulvérisation organométallique. Cela permet de rendre la nacelle compatible avec u n tu rboréacteur de type « open rotor » , c'est-à-dire présentant une soufflante non carénée au niveau de sa section aval.  According to one variant, the outer surface 23 of the cover 15 is also made superhydrophobic, for example by said organometallic sputtering method. This makes it possible to make the nacelle compatible with an "open rotor" type rboreactor, that is to say having an unsheathed fan at its downstream section.
Optionnellement, la lèvre métallique d'entrée d'air 10 de la nacelle est également superhydrophobe. Comme précédemment, la lèvre d'entrée d'air peut être rendue superhydrophobe par tout procédé de traitement de surface.  Optionally, the air inlet metal lip 10 of the nacelle is also superhydrophobic. As before, the air inlet lip can be made superhydrophobic by any surface treatment process.
La surface externe 27 de la lèvre d'entrée d'air 10 peut être traitée par pulvérisation d'un complexe organométal l ique ou peut être rendue superhydrophobe par réaction d'un acide gras et de ladite surface externe 27. Le caractère su perhyd rophobe de l a lèvre d 'entrée d 'a i r permet très avantageusement d'utiliser un dispositif de dégivrage par composant piézoélectrique.  The outer surface 27 of the air inlet lip 10 can be spray-treated with an organometallic complex or can be made superhydrophobic by reacting a fatty acid and said outer surface 27. The perhydroophobic su the air intake lip makes it very advantageous to use a piezoelectric component deicing device.
Le dégivrage par composant piézo-électrique consiste à faire vibrer la surface à dégivrer pour casser et évacuer les faibles couches de glace accumulées sur la lèvre.  Defrosting by piezoelectric component consists in vibrating the surface to be defrosted to break and evacuate the small layers of ice accumulated on the lip.
Le dégivrage par composant piézo-électrique est notamment décrit plus en détails dans le brevet européen publié sous le numéro EP 2 209 715 et appartenant au demandeur. Ainsi, l'utilisation d'une surface superhydrophobe en complément d'un dispositif de dégivrage mécanique de type piézo-électrique permet de faciliter le décrochage de la glace, en ce que la force d'adhésion de la glace sur la paroi de l'élément à dégivrer est réduite. Defrosting by piezoelectric component is in particular described in more detail in the European patent published under the number EP 2 209 715 and belonging to the applicant. Thus, the use of a superhydrophobic surface in addition to a mechanical de-icing device of the piezoelectric type makes it easier to unhook the ice, in that the adhesion force of the ice on the wall of the element to defrost is reduced.
Quelles que soient les méthodes d'obtention de surfaces superhydrophobes, ces surfaces sont obtenues par un procédé de traitement de surface. Cela permet avantageusement, contrairement aux revêtements hydrophobes connus de l'art antérieur, d'accroître considérablement la résistance à l'érosion de la surface traitée et de réduire sensiblement le coût de traitement de ces surfaces.  Whatever the methods for obtaining superhydrophobic surfaces, these surfaces are obtained by a surface treatment process. This advantageously makes it possible, unlike the hydrophobic coatings known from the prior art, to considerably increase the erosion resistance of the treated surface and to substantially reduce the cost of treating these surfaces.
Grâce à la présente i nvention , en prévoyant des surfaces superhydrophobes en complément de dispositifs de traitement contre le givre, on réduit considérablement la consommation énergétique de ces dispositifs de traitement contre le givre. With the present invention, by providing superhydrophobic surfaces in addition to anti-icing devices, the energy consumption of these anti-icing devices is considerably reduced.
Enfin, comme il va de soi, l'invention ne se limite pas aux seules formes de réalisation décrites ci-dessus uniquement à titre d'exemples illustratifs, mais elle embrasse au contraire toutes les variantes faisant intervenir les équivalents techniques des moyens décrits ainsi que leurs combinaisons si celles-ci entrent dans le cadre de l'invention. Finally, it goes without saying that the invention is not limited to the embodiments described above solely as illustrative examples, but on the contrary embraces all the variants involving the technical equivalents of the means described as well as their combinations if they fall within the scope of the invention.

Claims

REVENDICATIONS
1 . Élément d'aéronef comprenant une section de bord d'attaque (9) et une section de bord de fuite (1 1 ), ladite section de bord d'attaque comprenant au moins un d ispositif de traitement contre le g ivre, caractérisé en ce que la section de bord de fuite (1 1 ) comprend au moins une surface superhydrophobe (21 , 23). 1. Aircraft element comprising a leading edge section (9) and a trailing edge section (11), said leading edge section comprising at least one anti-drunk treatment device, characterized in that the trailing edge section (1 1) comprises at least one superhydrophobic surface (21, 23).
2. Élément d'aéronef selon la revendication 1 , caractérisé en ce qu'il s'agit d'une nacelle (5) pour turboréacteur ou turbopropulseur d'aéronef, la section de bord d'attaque (9) comprenant une lèvre d'entrée d'air (10) et la section de bord de fuite (1 1 ) comprenant une section médiane (13) comprenant une surface interne (21 ) et une surface externe (23) radialement éloignée de ladite surface interne, ladite surface interne (21 ) comprenant a u mo i n s u n e su rface superhydrophobe. 2. Aircraft element according to claim 1, characterized in that it is a nacelle (5) for an aircraft turbojet or turboprop engine, the leading edge section (9) comprising a lip of air inlet (10) and the trailing edge section (1 1) comprising a middle section (13) comprising an inner surface (21) and an outer surface (23) radially remote from said inner surface, said inner surface ( 21) comprising at least one superhydrophobic surface.
3. Élément d'aéronef selon la revendication 2, caractérisé en ce que la surface externe (23) comprend en outre au moins une surface superhydrophobe. 3. Aircraft element according to claim 2, characterized in that the outer surface (23) further comprises at least one superhydrophobic surface.
4. Élément d'aéronef selon l'une quelconque des revendications 2 ou 3, caractérisé en ce que la lèvre d'entrée d'air (10) comprend au moins une surface superhydrophobe. 4. Aircraft element according to any one of claims 2 or 3, characterized in that the air intake lip (10) comprises at least one superhydrophobic surface.
5. Élément d'aéronef selon l'une quelconque des revendications 1 à 4, caractérisé en ce que ladite surface superhydrophobe (21 , 23) est obtenue par un procédé de traitement de surface. 5. Aircraft element according to any one of claims 1 to 4, characterized in that said superhydrophobic surface (21, 23) is obtained by a surface treatment method.
6. Élément d'aéronef selon la revendication 5, caractérisé en ce q u e l edit procédé de tra itement de su rface est u n procédé de pulvérisation d'un complexe organométallique. 6. Aircraft element according to claim 5, characterized in that the surface treatment method is a method of spraying an organometallic complex.
7. Élément d'aéronef selon les revendications 4 et 5, caractérisé en ce que la surface hydrophobe de la lèvre d'entrée d'air (10) est obtenue par réaction chimique entre un acide gras et ladite surface de la lèvre d'entrée d'air. Aircraft element according to Claims 4 and 5, characterized in that the hydrophobic surface of the air intake lip (10) is obtained by chemical reaction between a fatty acid and said surface of the inlet lip. air.
8. Élément d'aéronef selon l'une quelconque des revendications 1 à 7, caractérisé en ce qu'il supporte un turboréacteur du type « Open Rotor ». 8. Aircraft element according to any one of claims 1 to 7, characterized in that it supports a turbojet of the type "Open Rotor".
EP14727579.6A 2013-04-09 2014-04-08 Aircraft element requiring an anti-icing treatment Withdrawn EP2983989A1 (en)

Applications Claiming Priority (2)

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FR1353165A FR3004165B1 (en) 2013-04-09 2013-04-09 AIRCRAFT ELEMENT REQUIRING TREATMENT AGAINST FROZEN
PCT/FR2014/050838 WO2014167237A1 (en) 2013-04-09 2014-04-08 Aircraft element requiring an anti-icing treatment

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FR3004165B1 (en) 2015-03-27
US20160023771A1 (en) 2016-01-28

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