Rotating part of a turbomachine receiver equipped with an anti-icing device
A superhydrophobic anti-icing coating and de-icing heating mat combination in turbomachine receivers address the complexity and mass distribution issues of existing systems, providing efficient and balanced icing prevention.
Patent Information
- Application Number
- FR2023003612
- Authority / Receiving Office
- FR · FR
- Patent Type
- Patents
- Current Assignee / Owner
- Filing Date
- 2023-04-12
- Publication Date
- 2026-01-02
- Estimated Expiration
- 2043-04-12
AI Technical Summary
Existing turbomachine receivers have complex architectures and significant rotating masses due to separate de-icing and anti-icing devices, leading to unbalanced mass distribution and potential breakage risks from ice formation.
Implementing a superhydrophobic anti-icing coating on the cone and propellers, combined with a de-icing heating mat and reduced power supply components, to minimize mass and simplify the architecture while effectively combating icing.
The solution reduces the rotating mass and simplifies the architecture, minimizing unbalanced effects and ice-related risks while maintaining effective icing prevention.
Smart Images
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Abstract
Description
Title of the invention: ROTATING PART FROM A TURBOMACHINE RECEIVER EQUIPPED WITH AN ANTI-FREEZE DEVICE TECHNICAL FIELD OF THE INVENTION
[0001] The present invention relates to the field of aircraft turbomachinery and more particularly to the rotating part of the receivers of a turbomachine.
[0002] The present invention relates more particularly to devices for combating frost on the rotating part of the receivers of a turbomachine. TECHNOLOGICAL BACKGROUND OF THE INVENTION
[0003] Aircraft turbomachinery such as turbojets and turboprops have receivers comprising a rotating part. More specifically, the rotating part of the receivers of a turbojet corresponds to the fan, and the rotating part of the receivers of a turboprop corresponds to its propellers. Typically, the rotating part of a receiver comprises an outer cone and movable blades, or propellers, arranged downstream of the cone.
[0004] The rotating part of a turbomachine receiver 10 according to the prior art as shown in [Fig. 1] comprises: - a rotation shaft 20 with axis of rotation X axially delimited between an upstream end 20A and a non-visible downstream end, - a cone 30 mounted at the upstream end 20A of the rotation shaft 20 and comprising an external surface 30A and an internal surface 30B, - a plurality of helices 40 arranged downstream of the cone 30, distributed circumferentially around the axis of rotation X and each comprising an upstream surface 40A and a downstream surface 40B, and - a de-icing device 50 for the propellers 40 comprising a heating mat 52 arranged on the upstream surface 40A of the propellers 40. - an anti-icing device 60 for the cone 30 comprising a heating mat 62 arranged on the external surface 30A of the cone 30, - a 700 power supply device, and - a mechanical reinforcement 80 arranged inside the cone 30, bearing against the internal surface 30B of the cone 30 and connected to the electronic control unit 710 of the feeding device 700.
[0005] The de-icing device 50 makes it possible to remove the layer of ice formed on the upstream surface 40A of the propellers 40. More specifically, the de-icing device 50 is activated only after the formation of a layer of ice, for example after a Period of inactivity of the aircraft's turbomachine in an area where the temperature is low. The anti-icing device 60 prevents the formation of an ice layer on the external surface 30A of the cone 30. More specifically, the anti-icing device 60 is continuously activated to prevent the formation of frost, for example, during the operation of the aircraft's turbomachine at low temperatures.
[0006] Ice formation on the rotating part of a turbomachine receiver 10 adds mass to the spinner 30 and the propellers 40, potentially leading to poor mass distribution around the axis of rotation X. Ice formation can also cause ice fragments to be ejected at high speed by centrifugal force into the rotating part of a turbomachine receiver 10, potentially resulting in breakage. Therefore, the presence of a de-icing device 50 and an anti-icing device 60 is essential for the proper functioning of the rotating part of an aircraft turbomachine receiver 10.
[0007] Each heating mat 52, 62 comprises a plurality of heating elements configured for defrosting the propellers 40 and de-icing the cone 30. The power supply device 700 provides the power supply to the heating elements of the heating mats 52, 62 and manages the power transmitted to the heating elements of the heating mats 52, 62.
[0008] More specifically, the power supply device 700 comprises: - an electronic control unit 710 arranged on the upstream end 20A of the rotation shaft 20 and configured to manage the power distributed to each heating mat 52, 62, - a connecting harness 720 linking the electronic control unit 710 to each of the propellers 40 for the power supply of the heating mats 52, 62, and - a rotating transformer 712 mounted movably in rotation around the rotation shaft 20 for the transfer of electrical energy from a fixed reference frame to a rotating reference frame.
[0009] The rotating part of a turbomachine receiver 10 incorporating such de-icing devices 50 and anti-icing devices 60 has a complex architecture given the various elements required for the operation of the heating mats 52, 62. Furthermore, the onboard mass of the power supply device 700 is relatively large because the electronic control unit 710, the connecting harness 720, and the transformer 712 are sized to transfer sufficient electrical power for the operation of the de-icing device 50 for the propellers 40 and the anti-icing device 60 for the spinner 30. In addition, the electronic control unit 710, the transformer 712, and the connecting harness 720 form a Rotating mass during operation of the rotating part of a turbomachine receiver 10. However, since the rotating mass is significant, imperfect mass balancing around the axis of rotation X causes mass distribution problems, also known as unbalance effects. Indeed, the greater the rotating mass, the more pronounced the unbalance effects.
[0010] In addition, such a rotating part of a turbomachine receiver must include two separate devices to combat icing on the cone 30 and the propellers 40, which complicates its architecture. Summary of the invention
[0011] The invention offers a solution to the problems mentioned above, by proposing a rotating part of an aircraft turbomachine receiver equipped with an anti-icing device ensuring effective anti-icing of the cone and propellers while minimizing the mass carried on the turbomachine.
[0012] A first aspect of the invention relates to a rotating part of an aircraft turbomachine receiver comprising: - a rotation shaft with an X-axis of rotation, - a cone mounted at one end of the rotating shaft and comprising an external surface and an internal surface, and - a plurality of helices arranged downstream of the cone, distributed circumferentially around the axis of rotation X and each comprising an upstream surface and a downstream surface.
[0013] The rotating part of a turbomachine receiver according to the invention includes an anti-icing device for the cone and propellers comprising a superhydrophobic anti-icing coating deposited on the external surface of the cone, and at least on the upstream surface of the propellers.
[0014] A turbomachine receiver according to the invention makes it possible to combat icing on the spinner and propellers by means of a single device. Thanks to the use of a superhydrophobic anti-icing coating for the anti-icing device, the onboard mass is reduced and the architecture of the anti-icing means according to the invention is simplified. Indeed, the fact that the anti-icing device is in the form of a layer of a specific superhydrophobic material makes it possible to avoid the need for a transformer for the transfer of the electrical energy required for the operation of the anti-icing device.
[0015] Advantageously, the rotating part of a turbomachine receiver includes a cone and propeller de-icing device comprising a de-icing heating mat arranged between the anti-icing coating of the anti-icing device and, respectively, the external surface of the cone and the upstream surface of each propeller. This device makes it possible to eliminate any layer of ice formed on the external surface of the cone and the upstream surface of the propellers, without requiring too much electrical power since it only intervenes in addition to the anti-icing device.
[0016] Preferably, the rotating part of a turbomachine receiver includes a heating mat power supply device comprising at least two electrical storage boxes arranged on the internal surface of the cone.
[0017] Advantageously, the power supply device comprises two electrical storage boxes diametrically opposed to each other. Such an arrangement of the two electrical storage boxes allows the mass to be distributed uniformly within the cone.
[0018] Preferably, each electrical storage unit is electrically powered by an external rotor generator arranged on the rotating shaft.
[0019] Preferably, the rotating part of a turbomachine receiver includes a mechanical reinforcement arranged inside the cone, bearing against each electrical storage box and connected to the rotating shaft to hold each electrical storage box in position in the cone.
[0020] Advantageously, the mechanical reinforcement comprises at least two branches, each delimited between a first and a second end, along which: - the branches are joined to each other at their first end, and - each branch is supported against one of the electrical storage boxes at its second end.
[0021] Preferably, the rotating part of a turbomachine receiver includes a control means for the heating mat of the defrosting device connected to a temperature sensor. Such a feature allows the activation and deactivation of the heating mat to be controlled according to the temperature measured by the sensor.
[0022] Advantageously, the rotating part of an aircraft turbomachine receiver includes a power electronics box and at least one linking harness electrically connecting the power electronics box to the propellers.
[0023] Advantageously, the rotating part of an aircraft turbomachine receiver includes a power electronics box and at least one linking harness electrically connecting the power electronics box to the electrical storage box.
[0024] A second aspect of the invention relates to an aircraft turbomachine comprising a rotating part of a turbomachine receiver according to the invention.
[0025] The invention and its various applications will be better understood by reading the following description and examining the accompanying figures. BRIEF DESCRIPTION OF THE FIGURES
[0026] Other advantages and features of the invention will become apparent from the following description, illustrated by the figures in which: - The [Fig. 1] is a schematic representation of the rotating part of a turbomachine receiver comprising a de-icing device and an anti-icing device according to the prior art; - Fig. 2 is a schematic representation of the rotating part of a turbomachine receiver comprising a de-icing device and an anti-icing device according to the invention. DETAILED DESCRIPTION
[0027] An example of an embodiment of the rotating part of an aircraft turbomachine receiver according to the invention is described in detail below, with reference to the accompanying drawings. This example illustrates the features and advantages of the invention.
[0028] Unless otherwise specified, the same element appearing on different figures has a unique reference.
[0029] For the purposes of understanding the invention, the radial, tangential, and axial orientations of the RTA frame shown in the figures shall be adopted, the tangent T and axial A axes of which extend in a horizontal plane in the orientation shown in the figures. The axial axis A is parallel to an axis of rotation X of a rotating shaft of the rotating part of a turbomachine receiver. The upstream to downstream end of the rotating part of a turbomachine receiver is oriented along the axial axis A of the RTA frame.
[0030] In the description, the terms "upstream" and "downstream" are defined with respect to the direction of airflow from the air inlet of the turbomachine to the air outlet of the turbomachine. The terms "internal" and "external" are defined with respect to the X-axis; the term "external surface" refers to the surface facing the axis of rotation X, as opposed to the term "external surface" which refers to the surface axially opposite the X-axis.
[0031] Figure 2 represents a rotating part of a turbomachine receiver 10 according to certain embodiments comprising: - a rotation shaft 20 with axis of rotation X axially delimited between an upstream end 20A and a non-visible downstream end, - a cone 30 mounted at the upstream end 20A of the rotation shaft 20 and comprising an external surface 30A and an internal surface 30B, - a plurality of helices 40 arranged downstream of the cone 30, distributed circumferentially around the axis of rotation X and each comprising an upstream surface 40A and a downstream surface 40B, - an anti-icing device 60 for the cone 30 and propellers 40 comprising a superhydrophobic anti-icing coating 64 deposited on the external surface 30A of the cone 30, and at least on the upstream surface 40A of the propellers 40, - a defrosting device 50 comprising a heating mat 52 for defrosting the cone 30 and the propellers 40 arranged between the anti-frost coating 64 of the anti-frost device 60 and, respectively, the external surface 30A of the cone 30 and the downstream surface 40A of each propeller 40, and - a 700 power supply device.
[0032] The anti-icing device 60 according to the invention is in the form of a superhydrophobic anti-icing coating 64 corresponding to a layer of material whose physical properties considerably limit the adhesion capacity of microdroplets or droplets of an aqueous solution, such as water, to the surface of the material, also considerably reducing the possibility of the formation of an ice layer on the surface of the material. Indeed, a superhydrophobic material comprises microreliefs, or nanometric roughnesses, for example produced by laser, so as to form a contact angle between the microdroplets or droplets and the surface of the material greater than 150°.
[0033] However, under certain extreme conditions, for example during prolonged exposure of the rotating part of a turbomachine 10 to extreme cold, the superhydrophobic property of the anti-icing coating 64 may be lost and cause a thin layer of frost to appear on the surface of the anti-icing coating 64. Such a situation may require the use of the auxiliary de-icing device 50 provided to remove the thin layer of frost formed on the surface of the anti-icing coating 64 and thus restore the superhydrophobic property of the anti-icing coating 64.
[0034] The de-icing device 50 according to an embodiment of the invention in the form of a heating mat 52 is an auxiliary device whose operation is required only in the case where a layer of ice has formed on the anti-icing coating 64 of the cone and / or propellers 40.
[0035] The heating mat 52 of the defrosting device 50 comprises a plurality of heating elements configured for defrosting the propellers 40 and the cone 30. The power supply device 700 provides the power supply to the heating elements of the heating mats 52, 62 and manages the power transmitted to the heating elements of the heating mat 52.
[0036] More specifically, the power supply device 700 comprises: - at least two electrical storage boxes 714 arranged on the internal surface 30A of cone 30, - an external rotor generator 716 arranged on the rotating shaft and configured to electrically power each electrical storage unit 714, - a 718 power electronics box, - a first connecting harness 720 comprising a first and a second arm 722, 724 each electrically connecting the electronic power box 718 to the propellers 40 for the power supply of the heating elements of the heating mat 52 of the de-icing device 50 of the propellers 40, and - a second linking harness 730 comprising a first and second arm 732, 734 each electrically connecting the power electronic box 718 to one of the electrical storage boxes 714.
[0037] Each electrical storage unit 714 of the power supply device 700 corresponds to a battery, for example an NMC (Nickel Manganese Cobalt) battery or a supercapacitor. The battery or supercapacitor has, for example, an energy storage capacity of approximately 2 kWh (kilowatt-hours) and a total mass of approximately 15 kg (kilograms). Preferably, the power supply device 700 comprises two electrical storage units 714 diametrically opposed to each other, that is, each electrical storage unit 714 is arranged at one of the two ends of a straight line passing through the center of a circle in a cross-section of the cone 30. Such an arrangement of the electrical storage units 714 in the cone 30 makes it possible to distribute the mass uniformly within the cone 30 and avoid unbalanced effects.
[0038] According to some embodiments, the rotating part of a turbomachine receiver comprises at least two thermal cushions, not shown, each arranged between the internal surface 30A of the cone 30 and an electrical storage box 714. The presence of thermal cushions improves thermal conduction between the cone 30 and the storage box 714 and thus allows heat to be transmitted outside the cone 30.
[0039] The generator 716 of the power supply device 700 can be a three-phase, external-rotor, permanent-magnet generator. The generator 716 is configured to draw electrical energy from the rotating shaft 20 so as to generate a continuous power of approximately 40 kW (kilowatts) to power the electrical storage boxes 714. The use of an external-rotor generator 716, compared to the use of an internal-rotor generator, has the advantage of providing higher mass power densities while minimizing the size of the generator 716. Advantageously, the mass of the generator 716 is approximately 10 kg for a power density of approximately 4 kW / kg (kilowatts per kilogram). According to some embodiments, the generator 716 has a cylindrical shape with a diameter of approximately 140mm (millimeter) and an axial length of approximately 100mm.
[0040] The power electronics unit 718 of the power supply device 700 is configured to manage the charging of the electrical storage units 714, the distribution of electrical current to the heating elements of the heating mat 52 of the defrosting device 50, and the rectification of the alternating voltage supplied by the generator 716. In some embodiments, the power electronics unit 718 includes a control means for the heating mat 52 of the defrosting device 50, connected to a temperature sensor and configured to activate and deactivate the heating mat 52 according to the temperature measured by the sensor. Advantageously, the mass of the power electronics unit 718 is approximately 5 kg. In some embodiments, the power electronics unit 718 has a cylindrical shape with a diameter of approximately 200 mm and an axial length of approximately 80 mm.
[0041] Thus, the mass of the power supply device 700 is significantly reduced compared to that of the defrosting and anti-icing devices of the prior art, because the power supply device 700 described above is configured to provide intermittent power to the auxiliary defrosting device 50. Indeed, since the anti-icing device 60 is in the form of an anti-icing coating 64, it does not require any power supply. Consequently, the entire power supply device 700 is modified and resized compared to that of the prior art. Furthermore, the transformer 712, initially present in the cone 30 of the rotating part of a turbomachine receiver 10 according to the prior art, has been eliminated, resulting in a mass saving of approximately 40 kg and a reduction in the overall dimensions inside the cone 30.
[0042] According to some embodiments, the rotating part of a turbomachine receiver 10 includes a mechanical reinforcement 80 arranged inside the cone 30, bearing against each of the two electrical storage boxes 714 and connected to the rotating shaft 20 to hold each electrical storage box 714 in position in the cone 30.
[0043] According to an embodiment of the mechanical reinforcement 80 illustrated in [Fig. 2], the mechanical reinforcement 80 comprises a first branch 82, a second branch 84, and a third branch 86, each delimited between a first end 82A, 84A, 86A and a second end 82B, 84B, 86B. The three branches 82, 84, 86 are arranged such that: - the first, second and third branches 82, 84, 86 are joined to each other at their first end 82A, 84A, 86A, the first and second branches 82, 84 are each supported against one of the electrical storage boxes 714 at their second end 82B, 84B, and the third branch 86 is connected to the power electronic box 718 at its second end.
[0044] According to an alternative embodiment of the mechanical reinforcement 80, not shown, the mechanical reinforcement 80 comprises two branches 82, 84, each delimited between a first 82A, 84A and a second end 82B, 84B. Each of the two branches 82, 84 is arranged so that: - Branch 82, 84 is connected to the power electronics box 718 at its first end 82A, 84A, and - branch 82, 84 is supported against one of the electrical storage boxes 714 at its second end 82B, 84B.
[0045] The frost-fighting means according to the invention has a relatively low on-board mass and a simple architecture, in particular thanks to the use of a superhydrophobic anti-frost coating 64 for the anti-icing device 60. Such an anti-icing device 60 can be supplemented by the use of an auxiliary de-icing device 50 activated only under extreme temperature conditions.
Claims
Demands
1. Rotating part of an aircraft turbomachine receiver (10) comprising: - a rotating shaft (20) with axis of rotation X, - a cone (30) mounted at one end of the rotating shaft (20) and having an external surface (30A) and an internal surface (30B), and - a plurality of propellers (40) arranged downstream of the cone (30), distributed circumferentially around the axis of rotation X and each comprising an upstream surface (40A) and a downstream surface (40B), characterized in that it comprises: - an anti-icing device (60) for the cone (30) and the propellers (40) comprising a superhydrophobic anti-icing coating (64) deposited on the external surface (30A) of the cone (30), and at least on the upstream surface (40A) of the propellers (40), and - a device for auxiliary de-icing (50) of the cone (30) and of the propellers (40) comprising a de-icing heating mat (52) arranged between the anti-icing coating (64) of the anti-icing device (60) and,respectively, the external surface (30A) of the cone (30) and the upstream surface (40A) of each helix (40).
2. Rotating part of a turbomachine receiver (10) according to claim 1, characterized in that it comprises a heating mat power supply device (700) comprising at least two electrical storage boxes (714) arranged on the internal surface (30A) of the cone (30).
3. Rotating part of a turbomachine receiver (10) according to claim 2, characterized in that the power supply device (700) comprises two electrical storage boxes (714) diametrically opposed to each other.
4. Rotating part of a turbomachine receiver (10) according to claim 2 or 3, characterized in that each electrical storage box (714) is electrically powered by an external rotor generator (716) arranged on the rotating shaft (20).
5. Rotating part of a turbomachine receiver (10) according to any one of the preceding claims in combination with claim 2, characterized in that it comprises a mechanical reinforcement (80) arranged inside the cone (30), bearing against each electrical storage box (714) and connected to the rotating shaft (20).
6. Rotating part of a turbomachine receiver (10) according to claim 5, characterized in that: - the mechanical reinforcement (80) comprises at least two branches (82, 84, 86) each delimited between a first end (82A, 84A, 86A) and a second end (82B, 84B, 86B), - the branches (82, 84, 86) are fixed to each other at their first end (82A, 84A, 86A), and - each branch (82, 84, 86) is supported against one of the electrical storage boxes (714) at their second end (82B, 84B, 86B).
7. Rotating part of a turbomachine receiver (10) according to any one of the preceding claims, characterized in that it comprises a control means for the heating mat (52) of the defrosting device (50) connected to a temperature sensor.
8. Aircraft turbomachine, characterized in that it comprises a rotating part of a turbomachine receiver (10) according to any one of the preceding claims.