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.

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• 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)

Applications Claiming Priority (2)

Publications (1)

Family

ID=47191847

Family Applications (1)

Country Status (8)

Families Citing this family (1)

Citations (1)

Family Cites Families (11)

• 2012
  • 2012-06-25 FR FR1255982A patent/FR2992291B1/fr active Active
• 2013
  • 2013-06-24 WO PCT/FR2013/051464 patent/WO2014001696A1/fr active Application Filing
  • 2013-06-24 CA CA2876959A patent/CA2876959A1/fr not_active Abandoned
  • 2013-06-24 BR BR112014031696A patent/BR112014031696A2/pt not_active IP Right Cessation
  • 2013-06-24 EP EP13744612.6A patent/EP2864200A1/fr not_active Withdrawn
  • 2013-06-24 CN CN201380033411.4A patent/CN104395193A/zh active Pending
  • 2013-06-24 RU RU2015101581A patent/RU2015101581A/ru not_active Application Discontinuation
• 2014
  • 2014-12-19 US US14/578,079 patent/US20150136752A1/en not_active Abandoned

Patent Citations (1)

Non-Patent Citations (1)

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