BE1024761B1 - AXIAL TURBOMACHINE COMPRESSOR DEFROSTING DAWN - Google Patents

Abstract

The invention relates to an axial turbomachine defrosting blade (26), in particular a blade (26) placed in a separation spout at the inlet of a low-pressure turbojet compressor. The blade (26) comprises a de-icing device and an outer surface (27) intended to be in contact with the annular flow (18) of the turbomachine. The outer surface (27) has a leading edge (32), a trailing edge, a lower surface (36) and an extrados surface (50) extending from the leading edge (32) to the trailing edge . The defrosting device includes a heating electrical conductor (44) that forms the leading edge (44) of the outer surface of the blade (26) to defrost said leading edge (32). The electrical conductor may be an electrical wire or a tape.

Description

(73) Holder (s):

SAFRAN AERO BOOSTERS S.A.

4041, HERSTAL (MILMORT)

Belgium (72) Inventor (s):

DE VRIENDT Olivier 4690 BASSENGE Belgium (54) DEFROSTING VANE OF AXIAL TURBOMACHINE COMPRESSOR (57) The invention relates to a de-icing blade (26) of axial turbomachine, in particular a blade (26) placed in a separation nozzle at the inlet of the low compressor pressure of turbofan. The blade (26) comprises a deicing device and an external surface (27) intended to be in contact with the annular flow (18) of the turbomachine. The outer surface (27) has a leading edge (32), a trailing edge, a lower surface (36) and a lower surface (50) which extend from the leading edge (32) to the trailing edge . The deicing device includes an electric heating conductor (44) which forms the leading edge (44) of the outer surface of the blade (26) to defrost said leading edge (32). The electrical conductor can be an electrical wire or a strip.

M:

BELGIAN INVENTION PATENT

FPS Economy, SMEs, Middle Classes & Energy

Publication number: 1024761 Deposit number: BE2016 / 5891

Intellectual Property Office International Classification: F01D 25/02 B64D 15/12 F02C 7/047 Date of issue: 06/28/2018

The Minister of the Economy,

Having regard to the Paris Convention of March 20, 1883 for the Protection of Industrial Property;

Considering the law of March 28, 1984 on patents for invention, article 22, for patent applications introduced before September 22, 2014;

Given Title 1 “Patents for invention” of Book XI of the Code of Economic Law, article XI.24, for patent applications introduced from September 22, 2014;

Having regard to the Royal Decree of 2 December 1986 relating to the request, the issue and the maintenance in force of invention patents, article 28;

Given the patent application received by the Intellectual Property Office on November 30, 2016.

Whereas for patent applications falling within the scope of Title 1, Book XI of the Code of Economic Law (hereinafter CDE), in accordance with article XI. 19, §4, paragraph 2, of the CDE, if the patent application has been the subject of a search report mentioning a lack of unity of invention within the meaning of the §ler of article XI.19 cited above and in the event that the applicant does not limit or file a divisional application in accordance with the results of the search report, the granted patent will be limited to the claims for which the search report has been drawn up.

Stopped :

First article. - It is issued to

SAFRAN AERO BOOSTERS S.A., Route de Liers 121, 4041 HERSTAL (MILMORT) Belgium;

represented by

LECOMTE Didier, P.O. Box 1623, 1016, LUXEMBOURG;

a Belgian invention patent with a duration of 20 years, subject to the payment of the annual fees referred to in article XI.48, §1 of the Code of Economic Law, for: AUBE DEGIVRANTE DE COMPRESSEUR DE TURBOMACHINE AXIALE.

INVENTOR (S):

DE VRIENDT Olivier, Rue du Brouck 21, 4690, BASSENGE;

PRIORITY (S):

DIVISION:

divided from the basic application: filing date of the basic application:

Article 2. - This patent is granted without prior examination of the patentability of the invention, without guarantee of the merit of the invention or of the accuracy of the description thereof and at the risk and peril of the applicant (s) ( s).

Brussels, 06/28/2018, By special delegation:

BE2016 / 5891

Description

DEFROST VANE OF AXIAL TURBOMACHINE COMPRESSOR

Technical area

The invention relates to the field of electric defrosting of a turbomachine. More specifically, the invention relates to a turbomachine blade with an electric deicing and anti-icing device. The invention also relates to an axial turbomachine, in particular an aircraft turbojet or an aircraft turboprop.

Prior art

The electrical devices allow a turbojet to be defrosted without physical circulation of fluid. In this way the internal flow is preserved, and the need to draw hot gas from the high pressure compressor is eliminated. In addition, this solution simplifies the intake of calories since the oil or gas pipes are eliminated; just like their risk of leaks. Furthermore, the control means become more reliable and simpler, and the thermal efficiency can be improved.

Document US5281091 A discloses a turbofan with a separation nozzle facing the blower. The separation spout contains an annular row of vanes embodying a compressor inlet rectifier. Each blade is connected to an ice formation control system which heats it via an internal electrical conductor. This conductor describes a serpentine with several round trips in the dawn. Thus, the control system tends to defrost the lower surface and the leading edge of the blade. However, the effectiveness remains limited.

Summary of the invention

Technical problem

The object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the invention aims to improve the defrosting of a turbomachine blade. The invention also aims

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BE2016 / 5891 to offer a simple, resistant, light, economical, reliable, easy to produce, convenient to maintain, easy to inspect, and performance-saving solution.

Technical solution

The subject of the invention is a defrosting blade of a turbomachine, in particular for a turbomachine compressor, the blade comprising a deicing device and an external surface intended to be in contact with a flow of the turbomachine, the external surface including: an edge d attack, a trailing edge, a lower surface and an upper surface which extend from the leading edge to the trailing edge; remarkable in that the deicing device comprises an electrical heating conductor capable of defrosting the blade which forms the leading edge of the outer surface of the blade.

According to advantageous modes of the invention, the blade can include one or more of the following characteristics, taken individually or according to all possible technical combinations:

- The electrical conductor is an electrical wire, possibly of round or triangular section.

- The electrical conductor is an external electrical track, in particular in the form of a ribbon.

- The electrical conductor at least partially forms the lower surface and / or at least partially forms the upper surface.

- The electrical conductor includes an outer film with carbon fibers and / or carbon nanotubes.

- The electrical conductor comprises aluminum, possibly in nanopowder or aluminum oxynitride.

- The leading edge includes a radially internal end and a radially external end which are electrically connected by the electrical conductor and which are in contact with the flow of the turbomachine.

- The thickness EC of the electrical conductor represents between 5% and 75%, or between 10% and 50%, or between 20% and 30% of the thickness EA of the blade.

- The axial length of the electrical conductor represents between 1% and 10%, or between 2% and 7%, or between 3% and 5% of the length of the chord of the blade.

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- The blade includes an upstream groove in which the electrical conductor is arranged.

- The groove is adjusted to the downstream face of the electrical conductor, and / or extends downstream of the electrical conductor.

- The blade includes an electrical insulator downstream of the electrical conductor.

- The blade includes a body which forms the majority of the lower surface and / or the upper surface, and which supports the electrical conductor.

- The body includes a thermal conductor which is inside the body, and which is capable of performing a heat exchange with the electrical conductor.

- The body is made of a metallic material, in particular aluminum or titanium.

- The body is made of a composite material, in particular with an organic matrix.

- The wire is free of sheath and / or includes a single strand.

- The cross section of the electrical conductor is circular, ellipsoidal or cam.

- The electrical conductor is able to defrost the leading edge.

- The electrical conductor forms an electrical resistance heater.

- The electrical conductor is an electrically conductive material. Its electrical resistivity is less than: 1 * 10 ^Λ (-5) Q * m; or 1 * 10 ^Λ (-6) Q * m; or1 * 10 ^A (-7) Q * m; or 3 * 10 ^A (-8) Q * m. Electrical resistivities are considered at 25 ° C.

- The electrical conductor is able to defrost the blade when an electrical voltage less than or equal to: 10KV, or 1KV, or 100V, or 10V is applied across its terminals.

- The electrical conductor extends over the entire radial height of the leading edge.

- The thickness of the electrical conductor is between 1% and 10%, or between 2% and 7%, or between 3% and 5% of the length of the blade of the blade.

- The electrical insulator has an electrical resistivity greater than: 1 * 10 ^A (3) Q * m; or 1 * 10 ^A (9) Q * m; or1 * 10 ^A (15) Q * m. it can be a polymer.

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- The electrical insulation extends over the entire radial height of the electrical conductor.

- The rope is a medium rope.

- The thickness EA can be an average thickness of the blade in the flow of the turbomachine.

- The body supports the electrical conductor over the majority of its radial height, or over substantially the entire height of the electrical conductor.

- The body is full; and / or at an axial distance from the leading edge of the outer surface of the blade.

- The blade and / or the conductor is / are each in one piece.

- The leading edge is protruding, and / or includes a radius less than or equal to: 1.00 mm, or 0.30 mm, or 0.10 mm, or 0.03 mm, or 0.01 mm. The radius is notably measured upstream.

The invention also relates to a turbomachine,

Axial turbomachine, in particular a turbojet engine, comprising a deicing system with an annular row of blades, remarkable in that at least one, or more or each blade of the annular row is a deicing blade according to the invention, preferably each blade defrosting is full.

According to an advantageous embodiment of the invention, the turbomachine comprises a separation nozzle with a separation edge, and an annular wall forming the separation edge, the blades being axially inside said annular wall. According to an advantageous embodiment of the invention, the turbomachine comprises a stator supporting said blades or the turbomachine comprises a rotor supporting said blades.

According to an advantageous embodiment of the invention, at least one blade of the annular row comprises an electrical connection axially spaced from its leading edge, and which is electrically connected to one, or to several, or to each electrical conductor forming a blade leading edge of the directory row. According to an advantageous embodiment of the invention, the annular row comprises at least fifty or at least one hundred blades.

In general, the advantageous modes of each object of the invention are also applicable to the other objects of the invention. To the extent of

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BE2016 / 5891 5 possible, each object of the invention can be combined with the other objects. The objects of the invention can also be combined with the embodiments of the description, which in addition can be combined with one another.

Benefits

According to the invention, the leading edge of the outer surface of the blade is formed by an electrically conductive and therefore heating material. The choice of material also makes it possible to reinforce this leading edge so as to protect it against erosion and against possible ingestion, which makes the device more durable. Furthermore, an adequate electrical resistivity of the electrical conductor is accompanied by a reduction in section, and therefore by a reduction.

The resistive section of the electrical conductor allows defrosting or preventing the formation of frost in altitude conditions, despite a temperature of -50 ° C accompanied by a flow of humid air at 800km / h.

By powering the electrical conductor, the temperature of the leading edge in flight can be brought to at least: 20 ° C, or 50 ° C, or 100 ° C. Thus, the risks associated with formation and the presence of frost are reduced.

Brief description of the drawings

FIG. 1 represents an axial turbomachine according to the invention.

FIG. 2 is a diagram of a compressor with a turbomachine deicing system according to the invention.

FIG. 3 illustrates a defrosting separation nozzle according to the invention.

Figure 4 is a blade section along the axis 4-4 according to a first embodiment of the invention.

Figure 5 is a blade section along the axis 4-4 according to a second embodiment of the invention.

Figure 6 is a blade section along the axis 4-4 according to a third embodiment of the invention.

The figure is a blade section along the axis 4-4 according to a third embodiment of the invention.

Description of the embodiments

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In the following description, the terms internal and external refer to a positioning relative to the axis of rotation of an axial turbomachine. The axial direction corresponds to the direction along the axis of rotation of the turbomachine. The radial direction is perpendicular to the axis of rotation.

Upstream and downstream are in reference to the main flow direction of the flow in the turbomachine. The dimensions of the blades are in reference to the portion of the blade which is immersed in an axial flow of the turbomachine.

Figure 1 shows in a simplified manner an axial turbomachine. In this specific case, it is a double-flow turbojet engine. The turbojet engine 2 comprises a first level of compression, called a low-pressure compressor 5, a second level of compression, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10. In operation, the power mechanical of the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 5 and 6. The latter comprise several rows of rotor blades associated with rows of stator blades. The rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until the inlet of the combustion chamber 8.

An inlet fan commonly designated as a fan or blower 16 is coupled to the rotor 12 and generates an air flow which is divided into a primary flow 18 passing through the various above-mentioned levels of the turbomachine, and into a secondary flow 20 passing through a duct annular (partially shown) along the machine to then join the primary flow at the turbine outlet. The blower can be of the non-faired type, for example with double counter-rotating rotor, possibly downstream. The secondary flow can be accelerated so as to generate a thrust reaction for the flight of an aircraft. The primary 18 and secondary 20 flows are annular, coaxial and interlocking flows.

FIG. 2 is a sectional view of a compressor of an axial turbomachine such as that of FIG. 1. The compressor can be a low pressure compressor 5. One can observe there a part of the fan 16 and the separation nozzle 22 of the primary flow 18 and secondary flow 20. The rotor 12 comprises several rows of rotor blades 24, in this case three.

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BE2016 / 5891 7

The low pressure compressor 5 comprises several rectifiers, in this case four, which each contain a row of stator vanes 26.

The rectifiers are associated with the fan 16 or a row of rotor blades to straighten the air flow, so as to convert the speed of the flow into static pressure. The stator vanes 26 extend essentially radially from an outer casing. Advantageously, the blades of the same row are identical.

The separation spout 22 forms the inlet of the compressor 5. The spout 22 includes a deicing system 28. This system 28 is associated with the stator vanes 26 îo arranged in the separation spout 22, for example those arranged in the outer shell 30 which is fixed in the spout 22. The present teaching is detailed in relation to stator vanes 26, however it could be applied to rotor blades of the compressor, as to the blades of the fan.

Figure 3 outlines the deicing system 28 of the turbomachine. Although only one blade is shown, the following description can apply to all the blades in the corresponding annular row.

The stator vane 26 has an external surface TJ which is in contact with the primary flow 18. The external surface TJ forms the leading edge 32, the trailing edge

34, the lower surface 36 and the upper surface of the blade 26. These last two surfaces both extend from the leading edge 32 to the trailing edge 34 over the entire radial height and / or the entire axial length of the 'blade 26. Optionally, an internal ferrule 38 is suspended under the blades 26 and surrounds the axis of rotation 14.

The deicing system 28 includes a voltage source 40, such as a battery.

It can be specific to the turbomachine, or be replaced by an electrical circuit of the aircraft receiving the turbojet. The system 28 may also include a switch 42; and / or a control unit with a computer.

The system 28 includes a heated electrical conductor 44 forming the leading edge 32 of the blade 26. The electrical conductor 44 forms a deicing device associated with the blade. It forms a heating resistor when it is electrically supplied by the voltage source 40 and when its switch 42

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BE2016 / 5891 is closed. It extends from foot to head of dawn 26, that is to say that it touches the outer ring 30 and the inner ring 38.

The voltage source 40 can be common to all the vanes 26 of the annular row, just like the switch 42. According to a variant, the switch can control a group of blades, or each blade receives a switch so that power independently.

Furthermore, the blade 26 may include an electrical connection 46 forming an internal return. This link 46 closes the loop towards the voltage source 40.

It can be axially spaced from the leading edge 32 and in particular from the electric heating element. The linear electrical resistance of the link 46 is at least: 2, or, 5, or 10, or 100 times less than that of the electrical conductor 44. Each blade 26 may include an own electrical connection 46. Alternatively, the link is common to a group of blades, or to all the blades in the row. For example, the connection can extend along the circumference, possibly in the inner ring 38.

Figure 4 is a blade section along the axis 4-4 plotted in Figure 3. The present section then forms an aerodynamic profile 48 of the blade 26, where the lower surface 36 and the upper surface 50 appear, which delimit the body 52 of the blade 26 which supports the electrical conductor 44. The electrical connection 46 is visible, at a distance from the external surface 27 of the blade 26. The primary flow 18 and the axis of rotation 14 are apparent.

The electrical conductor 44 forms the leading edge 32. It is of round section, so that it generally forms a cylinder, for example bent so as to follow the curvatures in the space of the leading edge 32. The conductor electrical 44 may be a metallic electrical wire, for example aluminum, copper or steel, or a mixture of these materials. Aluminum can be an alloy. It can be in the form of a nanopowder, or aluminum oxynitride.

It can be a single-stranded wire, and in particular free of insulating sheath in order to thin it according to the thickness of the blade, and so that its electrical material touches the primary flow 18 to bring calories as close as possible the upstream tip of the leading edge 32.

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BE2016 / 5891 9

The electrical conductor 44 extends substantially over the lower surface 36 and / or over the upper surface 50. It can form at least: 1%, or 3% or 5% of at least one or each of these two surfaces ( 36; 50).

The thickness EC of the electrical conductor represents between 15% and 45% of the thickness EA of the blade 26. For example, the thickness EA is less than or equal to: 5mm, or 3mm. The thickness EA can be the maximum thickness of the blade 26, or in particular of its portion arranged in the flow 18. The thickness EA of the blade 26 can be the maximum thickness of each profile 48. The length axial of the electrical conductor 44 represents between 1% and 10%, or between 2% and 7%, or between 3% and 5% of the length of the rope 54 of the blade 26, or of the axial length of the dawn. Each length can be an average length.

The body 52 can be made of a metallic material, in particular aluminum or titanium. It can be produced by additive manufacturing using a powder-based layer. The body 52 forms a support for the electrical conductor 44.

The blade 26, and in particular the body 52 has an upstream groove 56 in which the electrical conductor 44 is disposed. The groove 56 runs along the leading edge 32, but remains apart because of the axial thickness of the electrical conductor 44. It marries the electrical conductor 44. Their surfaces at their interface are generally complementary.

Since the body 52 can be made of an electrically conductive material, the blade 26 can include an electrical insulator 58; for example a layer at the body / conductor interface. It can be a polymer. Its function is to avoid any short circuit.

FIG. 5 represents an aerodynamic profile 148 of the blade 126 according to a second embodiment of the invention. This figure 5 shows the numbering of the previous figures for identical or similar elements, the number being however incremented by 100. Specific numbers are used for the elements specific to this embodiment.

The blade 126 according to the second embodiment is substantially identical to that of the first embodiment, it however differs by the presence of a thermal conductor 160 which is inside the body 152. The thermal conductor 160 forms a heart coated by the body 152 and by the conductor

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BE2016 / 5891 electrical 144, for example so as to be isolated from circular flow 118. The thermal conductor 160 may be in thermal contact with the electrical conductor 144, or at least extract calories therefrom.

The groove 156 is adjusted to the downstream face of the electrical conductor 144, and extends downstream to accommodate the thermal conductor 160. A layer of electrical insulation (not shown) can be added to avoid short circuits, its thickness remains thin for allow heat exchange.

The thermal conductivity of the material of the thermal conductor 160 can be higher than that of the material of the body 152, for example at least: two or five or twenty or fifty times greater. This increases the thermal conduction of calories from the electrical conductor 144 towards the trailing edge 134.

The thermal conductor 160 can extend over the majority or over the entire height of the blade 126, and / or over 10% to 70% of the axial length of the blade 126.

Thus, the body 152 can be made of a composite material, in particular with an organic matrix such as epoxy, polyamide, or PEEK. It can include a fibrous reinforcement, such as carbon fibers, or glass fibers. The body can be an electrical insulator. The trailing edge 134 can be electrically isolated from the leading edge 132.

FIG. 6 represents an aerodynamic profile 248 of the blade 226 according to a third embodiment of the invention. This figure 6 shows the numbering of the previous figures for identical or similar elements, the number being however incremented by 200.

The blade 226 according to the second embodiment is substantially identical to that of the first embodiment, it differs however in the cross section of the conductor 244, and therefore in that of the complementary groove 256. Insulation 258 can follow adaptation.

The electrical conductor 244 has a polygon section, for example in a diamond shape. Its upstream tip forms the leading edge 232, and its downstream tip is embedded in the groove 256 for better support. Dawn polygon shapes are possible, such as a pentagon or a triangle. In the latter case, the groove can be removed and replaced by a flat face in axial support against an upstream face of the body of the blade.

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FIG. 7 represents an aerodynamic profile 348 of the blade 326 according to a fourth embodiment of the invention. This figure 7 shows the numbering of the previous figures for the same or similar elements, the number being however incremented by 300. Specific numbers are used for the elements specific to this embodiment.

The electrical conductor 344 is an electrical track which forms the leading edge 332. It can form a ribbon astride this edge 332, and extends over the lower surface and / or the upper surface. In particular, the conductor 344 can be a strip with an edge forming the leading edge 332, and extending either along the lower surface 336 or according to the upper surface

350.

In profile, the electrical conductor 344 has two branches 362 pinching the lower side and the upper side of the blade 326. These branches 362 can be of different axial lengths. The material of the body 352 can correspond to that presented in relation to the second embodiment.

The electrical conductor 344 may include a film with carbon fibers and / or carbon nanotubes. The film can form the branches 362.

It can be printed on the leading edge 332. Its thickness EC can be less than or equal to: 5%, or 1% of the thickness EA of the blade 326. Its thickness EC can be the thickness of a branch 362. Its thickness EC can be constant.

The teachings of different embodiments can be applied to the other embodiments. The blades presented from the second to the fourth embodiment can each form an annular row of identical blades, said rows being able to be used in the rotary machines described in relation to FIGS. 1 to 3.

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Claims (20)

Claims 1. Defrosting blade (26; 126; 226; 326) of a turbomachine (2), in particular for a turbomachine compressor (2), the blade (26; 126; 226; 326) comprising a deicing device and an external surface (27 ) intended to be in contact with a flow of the turbomachine (2), the external surface (27) including: - a leading edge (32; 132; 232; 332), - a trailing edge (34; 134), - a lower surface (36; 336) and a lower surface (50; 350) which extend from the leading edge (32; 132; 232; 332) to the trailing edge (34; 134); characterized in that the deicing device comprises an electric heating conductor (44; 144; 244; 344) capable of defrosting the blade (26; 126; 226; 326) which forms the leading edge (32; 132; 232; 332) of the outer surface (27) of the blade (26; 126; 226; 326). 2. Defrosting blade (26; 126; 226) according to claim 1, characterized in that the electrical conductor (44; 144; 244) is an electric wire, possibly of round or triangular section. 3. Defrosting blade (26; 126; 226) according to claim 1, characterized in that the electrical conductor (344) is an external electrical track, in particular in the form of a ribbon. 4. Defrosting blade (26; 126; 226; 326) according to one of claims 1 to 3, characterized in that the electrical conductor (44; 144; 244; 344) at least partially forms the lower surface (36; 336 ) and / or at least partially forms the upper surface (50; 350). 5. Defrosting blade (26; 126; 226; 326) according to one of claims 1 to 4, characterized in that the electrical conductor (44; 144; 244; 344) comprises an outer film with carbon fibers and / or carbon nanotubes. 2016/5891 BE2016 / 5891 13 6. Defrosting blade (26; 126; 226; 326) according to one of claims 1 to 5, characterized in that the electrical conductor (44; 144; 244; 344) comprises aluminum, optionally in nanopowder or aluminum oxynitride. 5 7. Defrosting blade (26; 126; 226; 326) according to one of claims 1 to 6, characterized in that the leading edge (32; 132; 232; 332) comprises an inner radially end and a radially end external which are electrically connected by the electrical conductor (44; 144; 244; 344) and which are in contact with the flow of the turbomachine (2). îo 8. Defrosting blade (26; 126; 226; 326) according to one of claims 1 to 7, characterized in that the thickness EC of the electrical conductor (44; 144; 244; 344) represents between 5% and 75%, or between 10% and 50%, or between 20% and 30% of the thickness EA of the blade. 9. Defrosting blade (26; 126; 226; 326) according to one of claims 1 to 8, 15 characterized in that the axial length of the electrical conductor (44; 144; 244; 344) represents between 1% and 10%, or between 2% and 7%, or between 3% and 5% of the length of the chord (54) of the blade. 10. Defrosting blade (26; 126; 226) according to one of claims 1 to 9, characterized in that it comprises an upstream groove (56; 156; 256) in 20 which is arranged the electrical conductor (44; 144; 244). 11. Defrosting blade (26; 126; 226) according to claim 10, characterized in that the groove (56; 156; 256) is adjusted to the downstream face of the electrical conductor (44; 144; 244), and / or extends downstream of the electrical conductor. 25 12. Deicing icing (26; 226) according to one of claims 1 to 11, characterized in that it comprises an electrical insulator (58: 258) downstream of the electrical conductor (44; 244). 13. Defrosting blade (26; 326) according to one of claims 1 to 12, characterized in that it comprises a body (52; 152; 352) which forms the 2016/5891 BE2016 / 5891 14 majority of the lower surface (36; 336) and / or the upper surface (50; 350), and which supports the electrical conductor. 14. Defrosting blade (126) according to claim 12, characterized in that the body (152) comprises a thermal conductor (160) which is inside the 5 body, and which is capable of performing a heat exchange with the electrical conductor (144). 15. Defrosting blade (26; 126; 326) according to one of claims 12 to 13, characterized in that the body (52; 152; 352) is made of a metallic material, in particular aluminum or titanium. îo 16. Defrosting blade (26; 126; 326) according to one of claims 12 to 13, characterized in that the body (52; 152; 352) is made of a composite material, in particular with an organic matrix. 17. Axial turbomachine (2), in particular a turbojet engine, comprising a deicing system (28) with an annular row of blades, characterized in 15 that at least one, or more or each blade of the annular row is a de-icing blade (26; 126; 226; 326) according to one of claims 1 to 16, preferably each de-icing blade is full. 18. axial turbomachine (2) according to claim 17, characterized in 20 that it comprises a separation spout (22) with a separation edge, and an annular wall forming the separation edge, the blades (26; 126; 226; 326) being axially inside said annular wall. 19. Axial turbomachine (2) according to one of claims 17 to 18, characterized in that it comprises a stator supporting the said blades 25 (26; 126; 226; 326) or that it comprises a rotor (12) supporting said blades. 20. Axial turbomachine (2) according to one of claims 17 to 19, characterized in that at least one blade (26; 126; 226; 326) of the annular row comprises an electrical connection (46) at an axial distance from 2016/5891 BE2016 / 5891 15 its leading edge (32; 132; 232; 332), and which is electrically connected to one, or to several, or to each electrical conductor (44; 144; 244; 344) forming a leading edge (32; 132; 232; 332) of dawn of the directory row. BE2016 / 5891 BE2016 / 5891 B E2016 / 5891 „..« «WW '« WWW' BE2016 / 5891 134 BE2016 / 5891 332,362 2016/5891 BE2016 / 5891 Abridged DEFROST VANE OF AXIAL TURBOMACHINE COMPRESSOR The invention relates to a de-icing blade (26) of an axial turbomachine, in particular a blade (26) placed in a separation nozzle at the inlet of 5 low pressure compressor of turbofan engine. The blade (26) comprises a deicing device and an external surface (27) intended to be in contact with the annular flow (18) of the turbomachine. The outer surface (27) has a leading edge (32), a trailing edge, a lower surface (36) and a lower surface (50) which extend from the leading edge (32) to the edge of the surface. flight. The deicing device includes a heated electrical conductor (44) which forms the leading edge (44) of the outer surface of the blade (26) to defrost said leading edge (32). The electrical conductor can be an electrical wire or a strip.