EP2864200A1 - Electrical heating unit for a de-icing device - Google Patents

Electrical heating unit for a de-icing device

Info

Publication number
EP2864200A1
EP2864200A1 EP13744612.6A EP13744612A EP2864200A1 EP 2864200 A1 EP2864200 A1 EP 2864200A1 EP 13744612 A EP13744612 A EP 13744612A EP 2864200 A1 EP2864200 A1 EP 2864200A1
Authority
EP
European Patent Office
Prior art keywords
resistive
heating assembly
electric heating
conducting
nacelle
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Withdrawn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
EP13744612.6A
Other languages
German (de)
French (fr)
Inventor
Marc Gerome
Xavier Cazuc
David Pereira
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 EP2864200A1 publication Critical patent/EP2864200A1/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Withdrawn legal-status Critical Current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
    • 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
    • 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
    • B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49002—Electrical device making
    • Y10T29/49082—Resistor making
    • Y10T29/49083—Heater type

Definitions

  • the present invention relates to an electric heater assembly for a device for deicing a turbojet nacelle air inlet lip.
  • the invention also relates to a nacelle air intake lip for a turbojet engine equipped with such an electric heating assembly.
  • the invention also relates to a turbojet engine nacelle equipped with an electric heater assembly according to the invention.
  • the invention relates to a method of manufacturing such an electric heater assembly.
  • An aircraft is propelled by one or more propulsion units each comprising a turbojet engine housed in a substantially tubular nacelle.
  • a nacelle generally has a substantially tubular structure surrounding the turbojet engine and comprises, an air inlet upstream of the engine, a median section intended to surround a fan of said turbojet engine and a downstream section surrounding the combustion chamber of the turbojet engine and which can be equipped with means of thrust reversal.
  • 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.
  • ice can form on the nacelle, in particular at the external surface of the air inlet lip.
  • the presence of ice or frost changes the aerodynamic properties of the air intake and disturbs the flow of air to the blower.
  • a solution for de-icing or deglazing the outer surface is to prevent ice from forming on this outer surface by keeping the surface concerned at a sufficient temperature.
  • it is known, for example from document US 4,688,757, to draw hot air at the compressor of the turbojet engine and to bring it to the level of the air inlet lip in order to heat the walls.
  • such a device requires a hot air supply duct system between the turbojet engine and the inlet air, as well as a system for evacuating the hot air at the air intake lip. This increases the mass of the propulsion unit, which is undesirable.
  • the object of the present invention is to solve the disadvantages of the prior art, that is to say that it has the aim of proposing an electric heating assembly for a deicing device, the integration of which together inside a turbojet nacelle lip is relatively easy and performed directly during the manufacturing phase of said lip.
  • the present invention relates to an electric heating assembly for a device for deicing a turbojet nacelle air inlet lip, comprising at least one current conducting portion and at least one resistive portion, said assembly wherein the resistive portion comprises a plurality of adjacent lamellae spaced apart from one another and connected to the common conductive portion of current so as to form at least one recess in said resistive portion.
  • the electric heating assembly matches the complex shape of the air intake lip, and can therefore easily be integrated therein. It is thus possible to achieve large carpets, which reduces the number of carpets needed for cover a desired surface of the air inlet lip. Also, an electric heating assembly according to the invention can cover about 1/6 th of the surface of the air inlet lip, which reduces the integration time in the lip of such an assembly.
  • the lamellae are spaced substantially uniformly along the current conducting portion.
  • the resistive portion comprises at least one heating layer each comprising at least one resistive element and at least one insulating element superimposed on said at least one resistive element.
  • the resistive portion comprises two heating layers.
  • each resistive layer may be powered independently of one another.
  • the current-conducting portion comprises at least one phase-conducting element associated with at least one neutral conductive element or "earth".
  • the at least one resistive element comprises at least one resistive coil having a first end connected to said phase conducting element and a second end connected to said neutral conducting element.
  • the current conducting portion comprises at least one side adjacent to one of the sides of the resistive portion.
  • the invention also relates to a nacelle air inlet lip for a turbojet, said lip being remarkable in that it comprises at least one electric heating assembly according to the invention.
  • the invention also relates to the turbo-jet engine which is remarkable in that it comprises at least one de-icing device comprising at least one electric heating assembly according to the invention powered by at least one electrical power source.
  • the invention relates to a method for manufacturing an electric heating assembly according to the invention, the method being remarkable in that it comprises the following steps aimed at:
  • FIG. 1 schematically illustrates an electric heating assembly according to the invention, in top view
  • FIG. 2 is a cross-sectional view of a lamella of the electric heating assembly
  • FIG. 3 is a longitudinal sectional view of the assembly according to the invention, illustrating the resistive elements positioned on the current diffuser portion;
  • FIGS. 4a and 4b show the connection between the electric heating assembly and an induction feed of a de-icing device
  • FIG. 6 is an isometric view of an air intake lip portion of a turbojet engine nacelle equipped with the electric heating assembly according to the invention.
  • the electric heating assembly 1 has a substantially rectangular geometry in the form of a comb having a portion current conductor 3 to which are attached a plurality of lamellae 5 or teeth, along a side C of the assembly 1.
  • the lamellae 5 form a resistive portion 7 of the electric heating assembly 1.
  • the lamellae shown in FIG. 1 are of substantially rectangular shape with regular spacing along the C side of the current conducting portion 3.
  • the lamellae 5 are spaced along several sides of the current-conducting portion 3.
  • the geometry of a lamella is likely to be modified according to the geometry of the part to which the electric heating assembly is integrated. More particularly, the radius of curvature of the part to which the electric heating assembly is intended determines the shape and dimensions of a lamella.
  • a lamella can thus adopt a rectangular, triangular, trapezoidal shape, etc.
  • the distance between two slats between them is also variable, depending on the needs of the room.
  • the electric heating assembly according to the invention is, according to a preferred embodiment, intended to be integrated with a composite, monolithic or sandwich air intake lip, of a turbojet engine nacelle.
  • the heater assembly may also equipulate other areas of the nacelle.
  • such a set is not limited to an application in the field of aeronautics either.
  • Figure 2 shows a rectangular shape, in cross-section.
  • the lamella 5 comprises two superimposed heating layers 9 and 11, each comprising a resistive element 13 surmounted on either side of an insulating element 15.
  • the resistive element 1 3 is made of an electrically conductive metal material, and the insulating element 15 is made for example from a fold of glass.
  • the resistive elements and the insulating elements may be made of any other material respectively electrically conductive and insulating.
  • the maintenance between a resistive element 13 and an insulating element is achieved by adhesive means such as glue 17 for example.
  • adhesive means such as glue 17 for example.
  • the number of heating layers can be adapted according to the needs of the skilled person.
  • the insulating element 15 receives on its upper face a conductive element 19, for example and as shown, a P-phase conductive wire element, associated with a conductive element 21, for example and, as shown, an element wired neutral conductor N.
  • phase conductor P and the neutral conductor N are grouped along the same side 22 of the insulating element 15.
  • phase and neutral conductors are connected to a power source 23 of a deicing device.
  • the power source is housed in or near the air intake lip (not shown) inside the nacelle.
  • the source of supply can still be housed in the fuselage of the aircraft.
  • the power source 23 is situated in the extension of the side 22 of the isolating element ant 1.
  • the power source is located in the extension of the side perpendicular to said side C.
  • phase and neutral conductors pass, between the power source 23 and the electric heating assembly 1, inside a flexible element 24, for example made of a material of the Kapton® type.
  • the resistive element 13 adopts a serpentine shape, one of whose ends is connected to the phase conductor P and the other of its ends is connected to the neutral conductor N.
  • the tracks of the serpenti n are pa ral ralel, which q u i advantageously reduces significantly the inductive loop surface formed by the coil.
  • the shape of the resistive elements is adapted according to the geometry of the lamellae of the assembly.
  • the resistive elements may have a shape other than that previously described and shown in FIG.
  • the resistive elements 13 are connected to the same phase conductor and neutral conductor. They are thus fed in parallel. Each heating layer is equipped with resistive elements 13 as previously described.
  • each heating layer is electrically independent of each other, i.e. each layer can be powered simultaneously or independently of each other, depending on the required heating intensity. .
  • the independent power supply of each of the layers of the electric heating assembly makes it possible to diffuse heat to the lip in "degraded" mode, in the event of a malfunction of one of the layers.
  • the electric heating assembly 1 is produced according to the manufacturing method according to the invention.
  • an insulating first element is placed on a first insulating element, typically a glass bend, a resistive element, which is covered by a second insulating element, so as to form a heating layer and a resistive portion.
  • a conductive element is also positioned between the two insulating elements so as to form a conductive portion of the electric heating assembly.
  • This process step is iterated until the desired number of layers are obtained.
  • the positioning of the resistive elements on the insulating elements depends on the geometry of the zone of the part intended to support the electric heating assembly.
  • the cutting step is then carried out using tools known from the prior art.
  • the electric heating assembly is positioned flat and portions dud it are cut together so as to form recesses 25 in the resistive portion 7.
  • each of the recesses 25 may adopt a specific shape different from the other recesses of the assembly, as shown in FIG. 5.
  • the electric heating assembly 1 is then adapted to be easily integrated with an air inlet lip 27 of a nacelle, as shown in FIG. 6. When the electric heating assembly is positioned in the lip 27, the spacing between two adjacent lamellae is substantially constant.
  • the method of integrating an electric heater assembly for a defrosting device into the air intake lip of a nacelle is simplified.
  • the presence of recesses between the slats reduces the integration time in the lip.
  • the presence of recesses between the lamellae also considerably facilitates the insertion of the electric heating assembly into the lip of the nacelle, while allowing said assembly to conform to the geometrical shape of said lip.
  • the integration of such a heater assembly can advantageously be carried out during the manufacturing phase of the air intake lip of the nacelle.
  • an electrical heating assembly according to the invention may allow to cover up to about 1/6 th of the air inlet lip of the nacelle, thereby avoid having to manually position segment by segment many smaller heating sets, as is the case according to the prior art.
  • the invention is not limited to the embodiments of this electric heating assembly, this nacelle integrating such a set or the method of manufacturing such a set, described above as examples, but it embraces on the contrary all variants, including, and only by way of example, those where the electric heating assembly is integrated with a leading edge of a wing or empennage, a "Winglet", from the radome, or from other parts of the powertrain or helicopter.

Landscapes

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

Abstract

The present invention relates to an electrical heating unit (1) for a device for de-icing an air-intake lip of a turbofan nacelle, including at least one current-conducting portion (3) and at least one resistive portion (7). Said unit is characterised in that the resistive portion includes a plurality of adjacent blades (5) which are separated from one another and each of which is connected to the common current-conducting portion (3) so as to form a recess (25) in said resistive portion (7).

Description

Ensemble électrique chauffant pour dispositif de dégivrage  Electric heater assembly for defrosting device
La présente invention se rapporte à un ensemble électrique chauffant pour dispositif de dégivrage d'une lèvre d'entrée d'air de nacelle de turboréacteur. L'invention concerne également une lèvre d'entrée d'air de nacelle pour turboréacteur équipée d'un tel ensemble électrique chauffant. L'invention se rapporte encore à une nacelle pour turboréacteur équipée d'un ensemble électrique chauffant selon l'invention. Enfin, l'invention concerne un procédé de fabrication d'un tel ensemble électrique chauffant. The present invention relates to an electric heater assembly for a device for deicing a turbojet nacelle air inlet lip. The invention also relates to a nacelle air intake lip for a turbojet engine equipped with such an electric heating assembly. The invention also relates to a turbojet engine nacelle equipped with an electric heater assembly according to the invention. Finally, the invention relates to a method of manufacturing such an electric heater assembly.
Un avion est propulsé par un ou plusieurs ensemble propulsifs comprenant chacun un turboréacteur logé dans une nacelle sensiblement tubulaire.  An aircraft is propelled by one or more propulsion units each comprising a turbojet engine housed in a substantially tubular nacelle.
Une nacelle présente de manière générale une structure sensiblement tubulaire entourant le turboréacteur et comprend, une entrée d'air en amont du moteur, une section médiane destinée à entourer une 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.  A nacelle generally has a substantially tubular structure surrounding the turbojet engine and comprises, an air inlet upstream of the engine, a median section intended to surround a fan of said turbojet engine and a downstream section surrounding the combustion chamber of the turbojet engine and which can be equipped with means of thrust reversal.
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.
En vol, (et au sol) selon les conditions de température, de pression et d'humidité, de la glace peut se former sur la nacelle, notamment au niveau de la surface externe de la lèvre d'entrée d'air. La présence de glace ou de givre modifie les propriétés aérodynamiques de l'entrée d'air et perturbe l'acheminement de l'air vers la soufflante.  In flight, (and on the ground) according to the conditions of temperature, pressure and humidity, ice can form on the nacelle, in particular at the external surface of the air inlet lip. The presence of ice or frost changes the aerodynamic properties of the air intake and disturbs the flow of air to the blower.
Une solution pour dégivrer ou déglacer la surface externe consiste à éviter que de la glace ne se forme sur cette surface externe en maintenant la surface concernée à une température suffisante. Ainsi, il est connu par exemple du document US 4 688 757, de prélever de l'air chaud au niveau du compresseur du turboréacteur et de l'amener au niveau de la lèvre d'entrée d'air afin de réchauffer les parois. Toutefois, un tel dispositif nécessite un système de conduits d'amenée d'air chaud entre le turboréacteur et l'entrée d'air, ainsi qu'un système d'évacuation de l'air chaud au niveau de la lèvre d'entrée d'air. Ceci augmente la masse de l'ensemble propulsif, ce qui n'est pas souhaitable. A solution for de-icing or deglazing the outer surface is to prevent ice from forming on this outer surface by keeping the surface concerned at a sufficient temperature. Thus, it is known, for example from document US 4,688,757, to draw hot air at the compressor of the turbojet engine and to bring it to the level of the air inlet lip in order to heat the walls. However, such a device requires a hot air supply duct system between the turbojet engine and the inlet air, as well as a system for evacuating the hot air at the 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 électriques. On pourra notamment citer le document EP 1 845 01 8 bien que de nombreux autres documents se rapportent au dégivrage électrique et à ses développements. La mise en oeuvre d'un dispositif de dég ivrage électrique util ise des ensembles de résistances chauffantes, également appelés tapis chauffants, implantés au niveau de la lèvre d'entrée d'air à proximité de la surface externe et alimentés électriquement par une alimentation électrique.  These disadvantages could be overcome by using electrical de-icing systems. In particular, document EP 1 845 01 8 may be mentioned, although many other documents relate to electrical deicing and its developments. The implementation of an electrical degumming device utilizes sets of heating resistors, also called heating mats, located at the air intake lip near the outer surface and electrically powered by a power supply. .
La géométrie extrêmement courbée de la lèvre d'entrée d'air d'une nacelle exige l'utilisation de plusieurs tapis chauffants indépendants pour permettre de recouvrir segment par segment la totalité de la surface de la lèvre d'entrée d'air de la nacelle. Cette solution technique est décrite dans le document EP 1 715 159 qui divulgue un ensemble chauffant constitué par une pluralité de bandes rapportées dans la zone à traiter contre le givre.  The extremely curved geometry of the air inlet lip of a nacelle requires the use of several independent heating mats to allow segment-by-segment coverage of the entire surface of the aerial inlet lip of the nacelle. . This technical solution is described in document EP 1 715 159 which discloses a heating assembly consisting of a plurality of strips reported in the area to be treated against frost.
Cette opération d'intégration se trouve être particulièrement longue et fastidieuse, du fait qu'elle est réalisée manuellement.  This integration operation is particularly long and tedious, because it is performed manually.
La présente invention a pour but de résoudre les inconvénients de l'art antérieur, c'est-à-d ire q u'el le a pou r but de proposer u n ensemble électrique chauffant pour dispositif de dégivrage, dont l'intégration dudit ensemble à l'intérieur d'une lèvre de nacelle de turboréacteur est relativement aisée et réalisée directement pendant la phase de fabrication de ladite lèvre.  The object of the present invention is to solve the disadvantages of the prior art, that is to say that it has the aim of proposing an electric heating assembly for a deicing device, the integration of which together inside a turbojet nacelle lip is relatively easy and performed directly during the manufacturing phase of said lip.
A cet effet, la présente invention se rapporte à un ensemble électrique chauffant pour dispositif de dégivrage d'une lèvre d'entrée d'air de nacelle de turboréacteur, comprenant au moins une portion conductrice de courant et au moins une portion résistive, ledit ensemble électrique chauffant étant remarquable en ce que la portion résistive comprend une pluralité de lamelles adjacentes espacées entre elles et chacune rel iée à la portion conductrice commune de courant de façon à former au moins un évidement dans ladite portion résistive.  For this purpose, the present invention relates to an electric heating assembly for a device for deicing a turbojet nacelle air inlet lip, comprising at least one current conducting portion and at least one resistive portion, said assembly wherein the resistive portion comprises a plurality of adjacent lamellae spaced apart from one another and connected to the common conductive portion of current so as to form at least one recess in said resistive portion.
Ainsi, en prévoyant des lamelles espacées, l'ensemble électrique chauffant épouse la forme complexe de la lèvre d'entrée d'air, et peut par conséquent aisément y être intégré. Il est ainsi possible de réaliser des tapis de grande taille, ce qui permet de réduire le nombre de tapis nécessaires pour recouvrir une surface souhaitée de la lèvre d'entrée d'air. Aussi, un ensemble électrique chauffant selon l'invention permet de recouvrir environ 1 /6eme de la surface de la lèvre d'entrée d'air, ce qui permet de réduire le temps d'intégration dans la lèvre d'un tel ensemble. Thus, by providing spaced lamellae, the electric heating assembly matches the complex shape of the air intake lip, and can therefore easily be integrated therein. It is thus possible to achieve large carpets, which reduces the number of carpets needed for cover a desired surface of the air inlet lip. Also, an electric heating assembly according to the invention can cover about 1/6 th of the surface of the air inlet lip, which reduces the integration time in the lip of such an assembly.
Selon une caractéristique optionnelle de l'invention, les lamelles sont espacées de man ière sensiblement régulière le long de l a portion conductrice de courant.  According to an optional feature of the invention, the lamellae are spaced substantially uniformly along the current conducting portion.
La portion résistive comprend au moins une couche chauffante comprenant chacune au moins un élément résistif et au moins un élément isolant superposé audit au moins un élément résistif.  The resistive portion comprises at least one heating layer each comprising at least one resistive element and at least one insulating element superimposed on said at least one resistive element.
Préférentiellement, la portion résistive comprend deux couches chauffantes.  Preferably, the resistive portion comprises two heating layers.
Avantageusement, chaque couche résistive peut être alimentée indépendamment l'une de l'autre.  Advantageously, each resistive layer may be powered independently of one another.
Selon un autre aspect de l'invention, la portion conductrice de courant comprend au moins un élément conducteur de phase associé à au moins un élément conducteur neutre ou « terre ».  According to another aspect of the invention, the current-conducting portion comprises at least one phase-conducting element associated with at least one neutral conductive element or "earth".
Ledit au moins un élément résistif comprend au moins un serpentin résistif comprenant une première extrémité reliée audit élément conducteur de phase et une deuxième extrémité reliée audit élément conducteur neutre.  The at least one resistive element comprises at least one resistive coil having a first end connected to said phase conducting element and a second end connected to said neutral conducting element.
Selon une autre caractéristique de l'ensemble selon l'invention, la portion conductrice de courant comprend au moins un côté adjacent à l'un des côtés de la portion résistive.  According to another characteristic of the assembly according to the invention, the current conducting portion comprises at least one side adjacent to one of the sides of the resistive portion.
L'invention se rapporte également à une lèvre d'entrée d'air de nacelle pour turboréacteur, ladite lèvre étant remarquable en ce qu'elle comprend au moins un ensemble électrique chauffant selon l'invention.  The invention also relates to a nacelle air inlet lip for a turbojet, said lip being remarkable in that it comprises at least one electric heating assembly according to the invention.
L'invention concerne aussi u ne nacel le pou r turboréacteu r remarquable en ce qu'elle comprend au moins un dispositif de dégivrage comprenant au moins un ensemble électrique chauffant selon l'invention alimenté par au moins une source d'alimentation électrique.  The invention also relates to the turbo-jet engine which is remarkable in that it comprises at least one de-icing device comprising at least one electric heating assembly according to the invention powered by at least one electrical power source.
Enfin, l'invention se rapporte à un procédé de fabrication d'un ensemble électrique chauffant se l on l 'invention, led it procédé étant remarquable en ce qu'il comprend les étapes suivantes visant à :  Finally, the invention relates to a method for manufacturing an electric heating assembly according to the invention, the method being remarkable in that it comprises the following steps aimed at:
- positionner au moins un élément résistif entre au moins deux éléments isolants de façon à former au moins une couche chauffante comprenant au moins une portion résistive ; - positionner au moins un élément conducteur entre au moins deux éléments isolants de façon à former au moins une portion conductrice de l'ensemble électrique chauffant ; positioning at least one resistive element between at least two insulating elements so as to form at least one heating layer comprising at least one resistive portion; positioning at least one conductive element between at least two insulating elements so as to form at least one conductive portion of the electric heating assembly;
- relier lesdites portions résistives et conductrices ; - découper partiellement lesdites couches de façon à former au moins deux lamelles de lad ite portion résistive, lesdites lamelles étant espacées entre elles par un évidement.  - Connect said resistive and conductive portions; partially cutting said layers so as to form at least two lamellae of said resistive portion, said lamellae being spaced apart by a recess.
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 illustre schématiquement un ensemble électrique chauffant selon l'invention, en vue de dessus ;  - Figure 1 schematically illustrates an electric heating assembly according to the invention, in top view;
- la figure 2 est une vue en coupe transversale d'une lamelle de l'ensemble électrique chauffant ;  - Figure 2 is a cross-sectional view of a lamella of the electric heating assembly;
- la figure 3 est une vue en coupe longitudinale de l'ensemble selon l'invention, illustrant les éléments résistifs positionnés sur la portion diffuseur de courant ;  - Figure 3 is a longitudinal sectional view of the assembly according to the invention, illustrating the resistive elements positioned on the current diffuser portion;
- les figures 4a et 4b représentent la liaison entre l'ensemble électrique chauffant et une sou rce d'al imentation d'u n dispositif de dégivrage ;  FIGS. 4a and 4b show the connection between the electric heating assembly and an induction feed of a de-icing device;
- la figure 5 illustre l'ensemble électrique chauffant en vue de dessus ;  - Figure 5 illustrates the electric heating assembly in a view from above;
- la figure 6 est une vue isométrique d'une portion de lèvre d'entrée d'air d'une nacelle de turboréacteur équipée de l'ensemble électrique chauffant selon l'invention.  FIG. 6 is an isometric view of an air intake lip portion of a turbojet engine nacelle equipped with the electric heating assembly according to the invention.
Sur l'ensemble des figures, des références identiques ou analogues désignent des organes ou ensembles d'organes identiques ou analogues.  Throughout the figures, identical or similar references designate the same or similar organs or sets of members.
On se réfère à la figure 1 , illustrant schématiquement en vue de dessus l'ensemble électrique chauffant selon l'invention.  Referring to Figure 1, schematically illustrating a top view of the electric heating assembly according to the invention.
L'ensemble électrique chauffant 1 adopte une géométrie sensiblement rectangulaire en forme de peigne présentant une portion conductrice de courant 3 à laquelle sont solidaires une pluralité de lamelles 5 ou dents, le long d'un côté C de l'ensemble 1 . The electric heating assembly 1 has a substantially rectangular geometry in the form of a comb having a portion current conductor 3 to which are attached a plurality of lamellae 5 or teeth, along a side C of the assembly 1.
Les lamelles 5 forment une portion résistive 7 de l'ensemble électrique chauffant 1 .  The lamellae 5 form a resistive portion 7 of the electric heating assembly 1.
Les lamelles représentées en figure 1 sont de forme sensiblement rectang u l a ire, rég u l ièrement espacées, le long d u côté C de l a portion conductrice de courant 3.  The lamellae shown in FIG. 1 are of substantially rectangular shape with regular spacing along the C side of the current conducting portion 3.
Selon une alternative non représentée sur les figures, les lamelles 5 sont espacées le long de plusieurs côtés de la portion conductrice de courant 3.  According to an alternative not shown in the figures, the lamellae 5 are spaced along several sides of the current-conducting portion 3.
Par ailleurs, la géométrie d'une lamelle est susceptible d'être modifiée en fonction de la géométrie de la pièce à laquelle l'ensemble électrique chauffant est intégré. Plus particulièrement, le rayon de courbure de la pièce à laquelle l'ensemble électrique chauffant est destiné détermine la forme et les dimensions d'une lamelle. Une lamelle peut ainsi adopter une forme rectangulaire, triangulaire, trapézoïdale, etc.  Moreover, the geometry of a lamella is likely to be modified according to the geometry of the part to which the electric heating assembly is integrated. More particularly, the radius of curvature of the part to which the electric heating assembly is intended determines the shape and dimensions of a lamella. A lamella can thus adopt a rectangular, triangular, trapezoidal shape, etc.
En outre, la distance qui sépare deux lamelles entre elles est également variable, selon les besoins de la pièce.  In addition, the distance between two slats between them is also variable, depending on the needs of the room.
A cet effet, on précise que l'ensemble électrique chauffant selon l'invention est, selon un mode de réalisation préféré, destiné à être intégré à une lèvre d'entrée d'air composite, monolithique ou sandwich, d'une nacelle de turboréacteur. Bien entendu , l'ensemble chauffant peut également équ iper d'autres zones de la nacelle. De plus, un tel ensemble ne se restreint pas non plus à une application dans le domaine de l'aéronautique.  For this purpose, it is specified that the electric heating assembly according to the invention is, according to a preferred embodiment, intended to be integrated with a composite, monolithic or sandwich air intake lip, of a turbojet engine nacelle. . Of course, the heater assembly may also equipulate other areas of the nacelle. Moreover, such a set is not limited to an application in the field of aeronautics either.
La fig u re 2 i l l u stre u n e l a melle 5 rectangulaire, en coupe transversale. La lamelle 5 comprend deux couches chauffantes 9 et 1 1 superposées, chacune comprenant un élément résistif 13 surmonté de part et d'autre d'un élément isolant 15.  Figure 2 shows a rectangular shape, in cross-section. The lamella 5 comprises two superimposed heating layers 9 and 11, each comprising a resistive element 13 surmounted on either side of an insulating element 15.
Typiquement, l'élément résistif 1 3 est réalisé grâce à un matériau métallique conducteur d'électricité, et l'élément isolant 15 est quant à lui réalisé par exemple à partir d'un pli de verre.  Typically, the resistive element 1 3 is made of an electrically conductive metal material, and the insulating element 15 is made for example from a fold of glass.
Bien sûr, les éléments résistifs et les éléments isolants peuvent être réalisés en tout autre matériau respectivement conducteur d'électricité et isolant.  Of course, the resistive elements and the insulating elements may be made of any other material respectively electrically conductive and insulating.
Le maintien entre un élément résistif 13 et un élément isolant est réalisé grâce à des moyens adhésifs tels que de la colle 17 par exemple. Le nombre de couches chauffantes peut être adapté en fonction des besoins de l'homme du métier. The maintenance between a resistive element 13 and an insulating element is achieved by adhesive means such as glue 17 for example. The number of heating layers can be adapted according to the needs of the skilled person.
On se reporte à présent à la figure 3, illustrant l'ensemble électrique chauffant en coupe longitudinale.  Referring now to Figure 3, illustrating the electric heating assembly in longitudinal section.
L'élément isolant 15 reçoit sur sa face supérieure un élément conducteur 19, par exem ple et com me représenté , u n él ém ent fil a i re conducteur de phase P, associé à un élément conducteur 21 , par exemple et comme représenté, un élément filaire conducteur neutre N.  The insulating element 15 receives on its upper face a conductive element 19, for example and as shown, a P-phase conductive wire element, associated with a conductive element 21, for example and, as shown, an element wired neutral conductor N.
Le conducteur de phase P et le conducteur neutre N sont regroupés le long d'un même côté 22 de l'élément isolant 15.  The phase conductor P and the neutral conductor N are grouped along the same side 22 of the insulating element 15.
On se réfère aux figures 4a et 4b. Les conducteurs de phase et neutre sont reliés à une source d'alimentation 23 d'un dispositif de dégivrage.  Referring to Figures 4a and 4b. The phase and neutral conductors are connected to a power source 23 of a deicing device.
La source d'alimentation est logée dans la lèvre d'entrée d'air (non représentée) ou à proximité, à l'intérieur de la nacelle.  The power source is housed in or near the air intake lip (not shown) inside the nacelle.
La source d'al imentation peut encore indifféremment être logée dans le fuselage de l'avion.  The source of supply can still be housed in the fuselage of the aircraft.
Selon le mode de réalisation représenté sur la figure 4a, la source d'alimentation 23 est située dans le prolongement du côté 22 de l 'élément isol ant 1 5. Selon une variante représentée en figure 4b, la source d'alimentation est située dans le prolongement du côté perpendiculaire audit côté C.  According to the embodiment shown in FIG. 4a, the power source 23 is situated in the extension of the side 22 of the isolating element ant 1. According to a variant represented in FIG. 4b, the power source is located in the extension of the side perpendicular to said side C.
Les conducteurs de phase et neutre transitent, entre la source d'alimentation 23 et l'ensemble électrique chauffant 1 , à l'intérieur d'un élément flexible 24, par exemple réalisé dans une matière du type Kapton®.  The phase and neutral conductors pass, between the power source 23 and the electric heating assembly 1, inside a flexible element 24, for example made of a material of the Kapton® type.
On revient à la figure 3. L'élément résistif 13 adopte une forme de serpentin, dont une de ses extrémités est reliée au conducteur de phase P et l'autre de ses extrémités est rel iée au conducteur neutre N . Les pistes du serpenti n sont pa ral lèles, ce q u i permet avantag eusement de réd u i re considérablement la surface de boucle inductrice formée par le serpentin.  Returning to FIG. 3, the resistive element 13 adopts a serpentine shape, one of whose ends is connected to the phase conductor P and the other of its ends is connected to the neutral conductor N. The tracks of the serpenti n are pa ral ralel, which q u i advantageously reduces significantly the inductive loop surface formed by the coil.
Toutefois, il est à noter que la forme des éléments résistifs est adaptée en fonction de la géométrie des lamelles de l'ensemble. Ainsi, les éléments résistifs peuvent avoir une forme autre que celle précédemment décrite et représentée sur la figure 3.  However, it should be noted that the shape of the resistive elements is adapted according to the geometry of the lamellae of the assembly. Thus, the resistive elements may have a shape other than that previously described and shown in FIG.
Les éléments résistifs 13 sont connectés au même conducteur de phase et conducteur neutre. Ils sont ainsi alimentés en parallèle. Chaque couche chauffante est équipée d'éléments résistifs 13 tels que précédemment décrits. The resistive elements 13 are connected to the same phase conductor and neutral conductor. They are thus fed in parallel. Each heating layer is equipped with resistive elements 13 as previously described.
Ainsi, chaque couche chauffante est électriquement indépendante l 'u ne de l 'autre, c'est-à-dire que chaque couche peut être alimentée simultanément ou indépendamment l'une de l'autre, en fonction de l'intensité de chauffage nécessaire.  Thus, each heating layer is electrically independent of each other, i.e. each layer can be powered simultaneously or independently of each other, depending on the required heating intensity. .
Par ailleurs, l'alimentation indépendante de chacune des couches de l'ensemble électrique chauffant permet de diffuser de la chaleur à la lèvre en mode « dégradé », en cas de dysfonctionnement d'une des couches.  Moreover, the independent power supply of each of the layers of the electric heating assembly makes it possible to diffuse heat to the lip in "degraded" mode, in the event of a malfunction of one of the layers.
On se réfère à présent à la figure 5, illustrant l'ensemble électrique chauffant selon l'invention, en vue de dessus, disposé à plat.  Referring now to Figure 5, illustrating the electric heating assembly according to the invention, in plan view, disposed flat.
L'ensemble électrique chauffant 1 est réalisé selon le procédé de fabrication selon l'invention.  The electric heating assembly 1 is produced according to the manufacturing method according to the invention.
Pou r cel a , on positionne sur u n prem ier él ément isolant, typiquement un pli de verre, un élément résistif, que l'on recouvre par un second élément isolant, de façon à former une couche chauffante et une portion résistive. On positionne également un élément conducteur entre les deux éléments isolants de façon à former u ne portion conductrice de l'ensemble électrique chauffant. On relie ensuite lesdites portions résistives et conductrices.  For this, an insulating first element is placed on a first insulating element, typically a glass bend, a resistive element, which is covered by a second insulating element, so as to form a heating layer and a resistive portion. A conductive element is also positioned between the two insulating elements so as to form a conductive portion of the electric heating assembly. These resistive and conductive portions are then connected.
On itère cette étape du procédé jusqu'à l'obtention du nombre de couches voulues. On obtient alors l'ensemble électrique chauffant, présentant une forme sensiblement parallélépipédique.  This process step is iterated until the desired number of layers are obtained. This gives the electric heating assembly, having a substantially parallelepiped shape.
Il est important de noter que le positionnement des éléments résistifs sur les éléments isolants dépend de la géométrie de la zone de la pièce destinée à supporter l'ensemble électrique chauffant.  It is important to note that the positioning of the resistive elements on the insulating elements depends on the geometry of the zone of the part intended to support the electric heating assembly.
On réalise ensuite l'étape de découpage grâce à un outillage connu de l'art antérieur. Pour cela, on positionne l'ensemble électrique chauffant à plat et on découpe des portions dud it ensemble de façon à former des évidements 25 dans la portion résistive 7.  The cutting step is then carried out using tools known from the prior art. For this, the electric heating assembly is positioned flat and portions dud it are cut together so as to form recesses 25 in the resistive portion 7.
Les évidements permettent d'une part l'intégration aisée de l'ensemble électrique dans la pièce à équiper, et d'autre part une couverture maximale de la surface de ladite pièce. A cet effet, chacun des évidements 25 peut adopter une forme spécifique différente des autres évidements de l'ensemble, comme représenté sur la figure 5. L'ensemble électrique chauffant 1 est alors apte à être intégré aisément à une lèvre d'entrée d'air 27 d'une nacelle, comme représenté en figure 6. Lorsque l'ensemble électrique chauffant est positionné dans la lèvre 27, l'espacement entre deux lamelles adjacentes est sensiblement constant. The recesses allow on the one hand the easy integration of the electrical assembly into the part to be equipped, and on the other hand a maximum coverage of the surface of said part. For this purpose, each of the recesses 25 may adopt a specific shape different from the other recesses of the assembly, as shown in FIG. 5. The electric heating assembly 1 is then adapted to be easily integrated with an air inlet lip 27 of a nacelle, as shown in FIG. 6. When the electric heating assembly is positioned in the lip 27, the spacing between two adjacent lamellae is substantially constant.
G râce à la présente invention, l e procédé d'intégration d'un ensemble électrique chauffant pour dispositif de dégivrage dans la lèvre d'entrée d'air d'une nacelle est simplifié. With the present invention, the method of integrating an electric heater assembly for a defrosting device into the air intake lip of a nacelle is simplified.
En effet, la présence d'évidements entre les lamelles permet de réduire le temps d'intégration dans la lèvre. La présence d'évidements entre les lamelles facil ite également considérablement l'insertion de l'ensemble électrique chauffant dans la lèvre de la nacelle, tout en permettant audit ensemble d'épouser la forme géométriq ue de lad ite lèvre . En outre, l'intégration d'un tel ensemble de chauffe peut avantageusement être réalisée pendant la phase de fabrication de la lèvre d'entrée d'air de la nacelle.  Indeed, the presence of recesses between the slats reduces the integration time in the lip. The presence of recesses between the lamellae also considerably facilitates the insertion of the electric heating assembly into the lip of the nacelle, while allowing said assembly to conform to the geometrical shape of said lip. In addition, the integration of such a heater assembly can advantageously be carried out during the manufacturing phase of the air intake lip of the nacelle.
Enfin , un ensemble électrique chauffant selon l'invention peut permettre de recouvrir jusqu'à environ 1 /6eme de la lèvre d'entrée d'air de la nacelle, ce qui permet d'éviter d'avoir à positionner manuellement segment par segment de nombreux ensembles de chauffe de taille inférieure, comme il est le cas selon l'art antérieur. Finally, an electrical heating assembly according to the invention may allow to cover up to about 1/6 th of the air inlet lip of the nacelle, thereby avoid having to manually position segment by segment many smaller heating sets, as is the case according to the prior art.
Comme il va de soi, l'invention ne se limite pas aux seules formes de réalisation de cet ensemble électrique chauffant, de cette nacelle intégrant un tel ensemble ou du procédé de fabrication d'un tel ensemble, décrites ci- dessus à titre d'exemples, mais elle embrasse au contraire toutes les variantes, et notamment, et uniquement à titre d'exemple, celles où l'ensemble électrique chauffant est intégré à un bord d'attaque d'une aile ou d'un empennage, d'une « winglet », du radô m e , o u e n co re d e pa l es d e tu rbopropulseur ou d'hélicoptère. As goes without saying, the invention is not limited to the embodiments of this electric heating assembly, this nacelle integrating such a set or the method of manufacturing such a set, described above as examples, but it embraces on the contrary all variants, including, and only by way of example, those where the electric heating assembly is integrated with a leading edge of a wing or empennage, a "Winglet", from the radome, or from other parts of the powertrain or helicopter.

Claims

REVENDICATIONS
1 . Ensemble électrique chauffant (1 ) pour dispositif de dégivrage d'une lèvre d'entrée d'air (27) de nacelle de turboréacteur, comprenant au moins une portion conductrice de courant (3) et au moins une portion résistive (7), caractérisé en ce que la portion résistive comprend une pluralité de lamelles (5) adjacentes espacées entre elles et chacune reliée à la portion conductrice commune de courant (3), de façon à former au mo ins u n évidement (25) dans ladite portion résistive (7). 1. Electrical heating assembly (1) for de-icing device for an air inlet lip (27) for a turbojet engine nacelle, comprising at least one current conducting portion (3) and at least one resistive portion (7), characterized in that the resistive portion comprises a plurality of adjacent lamellae (5) spaced apart from each other and each connected to the common current conducting portion (3), so as to form at least one recess (25) in said resistive portion (7). ).
2. Ensemble électrique chauffant (1 ) selon la revendication 1 , caractérisé en ce que les lamelles (5) sont espacées de manière sensiblement régulière le long de la portion conductrice de courant (3). 2. Electrical heating assembly (1) according to claim 1, characterized in that the lamellae (5) are spaced substantially uniformly along the current-conducting portion (3).
3. Ensemble électrique chauffant (1 ) selon l'une quelconque des revendications 1 ou 2, caractérisé en ce que la portion résistive (7) comprend au moins une couche chauffante (9, 1 1 ) comprenant chacune au moins un élément résistif (13) et au moins un élément isolant (15) superposé audit au moins un élément résistif. 3. Electric heating assembly (1) according to any one of claims 1 or 2, characterized in that the resistive portion (7) comprises at least one heating layer (9, 1 1) each comprising at least one resistive element (13). ) and at least one insulating element (15) superimposed on said at least one resistive element.
4. Ensemble électrique chauffant (1 ) selon l'une quelconque des revendications 1 à 3, caractérisé en ce que la portion résistive (7) comprend deux couches chauffantes (9, 1 1 ). 4. Electric heating assembly (1) according to any one of claims 1 to 3, characterized in that the resistive portion (7) comprises two heating layers (9, 1 1).
5. Ensemble électrique chauffant (1 ) selon la revendication 4, caractérisé en ce q ue chaq ue couche résistive (9, 1 1 ) est al imentée indépendamment l'une de l'autre. Electric heating assembly (1) according to claim 4, characterized in that each resistive layer (9, 1 1) is fed independently of one another.
6. Ensemble électrique chauffant (1 ) selon l'une quelconque de revendications 1 à 5, caractérisé en ce que la portion conductrice de courant (3) comprend au moins un élément conducteur de phase (P) associé à au moins un élément conducteur neutre (N) ou « terre ». 6. Electric heating assembly (1) according to any one of claims 1 to 5, characterized in that the current-conducting portion (3) comprises at least one phase-conducting element (P) associated with at least one neutral conductive element (N) or "earth".
7. Ensemble électrique chauffant (1 ) selon la revendication 6, caractérisé en ce que ledit au moins un élément résistif (13) comprend au moins un serpentin résistif comprenant une première extrémité reliée audit élément conducteur de phase (P) et une deuxième extrémité reliée audit élément conducteur neutre (N). 7. Electrical heating assembly (1) according to claim 6, characterized in that said at least one resistive element (13) comprises at least one resistive coil comprising a first end connected to said phase conducting element (P) and a second end connected to said neutral conducting element (N).
8. Ensemble électrique chauffant (1 ) selon l'une quelconque des revendications 1 à 7, caractérisé en ce que la portion conductrice de courant8. Electric heating assembly (1) according to any one of claims 1 to 7, characterized in that the current conducting portion
(3) comprend au moins un côté (C) adjacent à l'un des côtés de la portion résistive (7). (3) comprises at least one side (C) adjacent to one side of the resistive portion (7).
9. Lèvre d 'entrée d 'a i r (27) de n acel l e pou r tu rboréacteu r caractérisée en ce qu 'el le com prend au moins u n ensem ble électriq ue chauffant (1 ) selon l'une quelconque des revendications 1 à 8. 9. Air intake lip (27) of the same type, characterized in that it comprises at least one heating electric unit (1) according to any one of claims 1 to 9. 8.
10. Nacelle pour turboréacteur caractérisée en ce qu'elle comprend au moins un d ispositif de dég ivrage comprenant au moins un ensemble électrique chauffant (1 ) selon l'une quelconque des revend ications 1 à 8 alimenté par au moins une source d'alimentation électrique (23). 10. Nacelle for a turbojet engine characterized in that it comprises at least one dewatering device comprising at least one electric heating assembly (1) according to any one of claims 1 to 8 powered by at least one power source electric (23).
1 1 . Procédé de fabrication d'un ensemble électrique chauffant (1 ) défini selon l'une quelconque des revendications 1 à 8, caractérisé en ce qu'il comprend les étapes suivantes visant à : 1 1. Process for manufacturing an electric heating assembly (1) defined according to any one of Claims 1 to 8, characterized in that it comprises the following steps aimed at:
- positionner au moins un élément résistif (13) entre au moins deux éléments isolants (1 5) de façon à former au moins une couche chauffante (9, 1 1 ) comprenant au moins une portion résistive (7) ;  positioning at least one resistive element between at least two insulating elements so as to form at least one heating layer comprising at least one resistive portion;
- positionner au moins un élément conducteur (19, 21 ) entre au moins deux éléments isolants (15) de façon à former au moins une portion conductrice (3) de l'ensemble électrique chauffant - positioning at least one conductive element (19, 21) between at least two insulating elements (15) so as to form at least one conductive portion (3) of the electric heating assembly
(1 ) ; (1);
- relier lesdites portions résistives et conductrices ;  - Connect said resistive and conductive portions;
- découper partiellement lesdites couches (9, 1 1 ) de façon à former au moins deux lamelles (5) de ladite portion résistive (7), lesd ites lamel les étant espacées entre elles pa r u n évidement (25).  - Partially cutting said layers (9, 1 1) so as to form at least two lamellae (5) of said resistive portion (7), said lamel being spaced apart from each other by recess (25).
EP13744612.6A 2012-06-25 2013-06-24 Electrical heating unit for a de-icing device Withdrawn EP2864200A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1255982A FR2992291B1 (en) 2012-06-25 2012-06-25 HEATED ELECTRICAL ASSEMBLY FOR DEFROSTING DEVICE
PCT/FR2013/051464 WO2014001696A1 (en) 2012-06-25 2013-06-24 Electrical heating unit for a de-icing device

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EP (1) EP2864200A1 (en)
CN (1) CN104395193A (en)
BR (1) BR112014031696A2 (en)
CA (1) CA2876959A1 (en)
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US20150136752A1 (en) 2015-05-21
BR112014031696A2 (en) 2017-06-27
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FR2992291A1 (en) 2013-12-27
WO2014001696A1 (en) 2014-01-03
CN104395193A (en) 2015-03-04
CA2876959A1 (en) 2014-01-03

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