ROTORCRAFT PROVIDED WITH A YAW MOTION CONTROL SYSTEM HAVING A DUCTED ROTOR AND AN ICE PROTECTION SYSTEM

Abstract

A rotorcraft provided with a yaw motion control system comprising a fairing and a rotor provided with blades, the blades being arranged in the fairing and able to rotate about an axis of rotation of the rotor, the fairing comprising a casing defining an air stream, the air stream extending in a direction of flow of the air within the fairing from an intake section towards an outlet section. The rotorcraft comprises an ice protection system comprising at least one grille arranged upstream of the air stream in the air flow direction, the grille facing the intake section parallel to the axis of rotation and the casing, no grille facing at least one unprotected section of the intake section in a direction parallel to the axis of rotation.

Claims

1. A rotorcraft provided with a yaw motion control system with a ducted rotor, the system comprising a fairing and a rotor provided with blades, the blades being arranged in the fairing and able to rotate about an axis of rotation of the rotor, the fairing comprising a casing defining an air stream around the axis of rotation, the air stream extending in a direction of flow of the air within the fairing from an intake section towards an outlet section, wherein the rotorcraft comprises an ice protection system for the system, the ice protection system comprising at least one grille arranged upstream of the air stream in the air flow direction, the grille facing the intake section and the casing parallel to the axis of rotation, no grille facing at least one unprotected section of the intake section in a direction parallel to the axis of rotation.

2. The rotorcraft according to claim 1, wherein the at least one grille extends facing a periphery of the intake section parallel to the axis of rotation.

3. The rotorcraft according to claim 2, wherein, the periphery comprising, in a direction of forward travel of the rotorcraft, a rear section nd a front section, a grille of the at least one grille at least partially faces the front section or the rear section parallel to the axis of rotation.

4. The rotorcraft according to claim 3, wherein the rotorcraft comprises two grilles of the at least one grille, the two grilles comprising a front grille facing the front section and a rear grille facing the rear section.

5. The rotorcraft according to claim 4, wherein the front grille and the rear grille are different.

6. The rotorcraft according to claim 5, wherein the front grille extends transversely parallel to the axis of rotation over a first distance, the rear grille extends transversely parallel to the axis of rotation over a second distance, the second distance being smaller than the first distance.

7. The rotorcraft according to claim 1, wherein the at least one grille is domed, with a concave face turned towards the air stream.

8. The rotorcraft according to claim 1, wherein the at least one grille is carried by a frame fastened to the fairing.

9. The rotorcraft according to claim 1, wherein the at least one grille is arranged frontally facing an air flow running along the rotorcraft and arriving from a front zone of the rotorcraft.

10. The rotorcraft according to claim 1, wherein, the casing comprising a rear sector followed by a front sector along an axis of forward travel of the rotorcraft, the rear sector and the front sector being arranged to either side of a plane that contains the axis of rotation of the rotor and is parallel to a yaw axis, the at least one grille is arranged at least partially upstream of the rear sector in a direction leading from a front zone to a rear end of the rotorcraft.

11. The rotorcraft according to claim 1, wherein the at least one grille extends in a curved line.

12. The rotorcraft according to claim 11, wherein the at least one grille extends over an arc of a circle.

13. The rotorcraft according to claim 1, wherein the intake section comprises, in a direction of forward travel of the rotorcraft, a first section extended by a second section from a hub of the rotor, the at least one grille comprising a grille facing the first section parallel to the axis of rotation.

14. The rotorcraft according to claim 1, wherein, the casing comprising a convergent section extended by a blade path surrounding the blades, the at least one grille is arranged, parallel to the axis of rotation, upstream of at least part of the convergent section and at least part of the blade path.

15. The rotorcraft according to claim 1, wherein the ice protection system partially covers the intake section in a direction parallel to the axis of rotation.

16. An ice protection method for a yaw motion control system with a ducted rotor of the rotorcraft, the system comprising a fairing and a rotor provided with blades, the blades being arranged in the fairing and able to rotate about an axis of rotation of the rotor, the fairing comprising a casing defining an air stream around the axis of rotation, the air stream extending in a direction of flow of the air within the fairing from an intake section towards an outlet section, wherein the method comprises the arrangement of at least one grille arranged upstream of the air stream in the air flow direction, the grille facing the intake section and the casing, no grille facing at least one unprotected section of the intake section in a direction parallel to the axis of rotation.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0061] The disclosure and its advantages appear in greater detail in the context of the following description of embodiments given by way of illustration and with reference to the accompanying figures, in which:

[0062] FIG. 1 is a schematic view of a rotorcraft according to the disclosure;

[0063] FIG. 2 is a three-dimensional view showing an ice protection system;

[0064] FIG. 3 is a schematic cross-section of an ice protection system according to FIG. 2;

[0065] FIG. 4 is a cross-section of an ice protection system having two different grilles;

[0066] FIG. 5 is a three-dimensional view showing an ice protection system;

[0067] FIG. 6 is a schematic cross-section of the ice protection system according to FIG. 5;

[0068] FIG. 7 is a three-dimensional view showing an ice protection system;

[0069] FIG. 8 is a schematic cross-section of an ice protection system according to FIG. 7;

[0070] FIG. 9 is a three-dimensional view showing an ice protection system; and

[0071] FIG. 10 is a schematic cross-section of an ice protection system according to FIG. 9.

DETAILED DESCRIPTION

[0072] Elements that are present in more than one of the figures are given the same references in each of them.

[0073] Three directions X, Y, and Z orthogonal to each other are shown in the figures.

[0074] Direction X is referred to as the longitudinal direction and another direction Y is referred to as the transverse direction. Finally, a third direction Z is referred to as the elevation direction and corresponds to the height dimensions of the structures described.

[0075] FIG. 1 shows a rotorcraft 1 according to the disclosure provided with a yaw motion control system 10, and with a rotary wing 2.

[0076] The rotorcraft 1 may comprise an airframe that extends longitudinally along an anteroposterior plane P from a rear end 5 to a front zone 6. In particular, the airframe may comprise a main section 3 provided with the front zone 6 and surmounted by the rotary wing 2. This main section 3 may be extended by a tail boom 4 carrying the yaw motion control system 10 forming the rear end 5.

[0077] Moreover, the rotorcraft 1 moves forwards in a direction of forward travel AV leading from the rear end 5 towards the front zone 6.

[0078] Irrespective of the shape of the rotorcraft 1, the yaw motion control system 10 comprises a fairing 11 carried, where appropriate, by the tail boom 4. The yaw motion control system 10 also comprises a rotor 12 in the fairing 11. In particular, the rotor 12 has a plurality of blades 13 carried by a hub 14. The blades 13 together rotate about an axis of rotation AXROT.

[0079] As is conventional, the rotorcraft 1 may comprise a power plant, which is not shown here, for moving the rotary wing 2 and/or the rotor 12.

[0080] More precisely, the fairing 11 comprises a cowling forming a casing 15 that delimits an air stream 90. The air stream 90 and the casing 15 that delimits it extend transversely along the axis of rotation AXROT. The casing 15 may be rotationally symmetrical with respect to the axis of rotation AXROT. In particular, air flows in the air stream 90, in a direction 95 of flow of the air within the fairing 11, from an intake section 20 towards an outlet section 30. The casing 15 may possibly comprise, transversely and successively, a convergent section 16, a blade path 17 that is, for example, cylindrical, then a divergent section 18. The term “convergent section” refers to a part of the casing 15 which narrows in the air flow direction 95, whereas the term “divergent section” refers, on the contrary, to a part of the casing 15 which widens in the air flow direction 95. The casing 15 may additionally comprise, longitudinally, a rear sector 151 followed by a front sector 152 along an axis of forward travel AV of the rotorcraft 1, the rear sector 151 and the front sector 152 being arranged to either side of a plane P1 that contains the axis of rotation AXROT and is parallel to a yaw axis AXLAC.

[0081] Therefore, the intake section 20 is defined by the convergent section 16 and the outlet section 30 is defined by the divergent section 18. The blades 13 are arranged in the air stream 90 and, for example, in the blade path 17, the hub 14 being carried by a support connected to the casing 15 in a conventional manner, by arms. Reference can be made, if necessary, to the literature that describes such a system 10.

[0082] The intake section 20 may comprise a periphery 21 surrounding a central zone 210. In the direction of forward travel AV of the rotorcraft 1, the periphery 21 comprises a rear section 22 and a front section 23 arranged around the central zone 210. For example, the rear section 22 and the front section 23 are symmetrical relative to the plane P1 of symmetry of the casing 15 and/or each extends over a semicircle.

[0083] In an innovative manner, the rotorcraft 1 includes an ice protection system 40 in order to optimize the operation of the yaw motion control system 10 in icing conditions.

[0084] This ice protection system 40 comprises one or more grilles 50. Reference number “50” is used to refer to any grille, reference numbers “51, 52” being used to refer to specific grilles. The term “each” is used hereinafter irrespective of the number of grilles, i.e., in the presence of one or more grilles 50. Each grille comprises a mesh forming openings. For example, each grille may include wires made from metal or the like, a perforated metal sheet, etc.

[0085] Each grille 50 is arranged upstream of the air stream 90 in the air flow direction 95. In other words, an individual looking at a grille 50 in a direction parallel to the axis of rotation AXROT would note that the grille 50 is located in front of a part of the intake section 20. Each grille 50 therefore faces at least the intake section 20 parallel to the axis of rotation AXROT.

[0086] Furthermore, at least one unprotected section 24 of the intake section 20 is not facing a grille 50, or indeed another member of the ice protection system 40, such as a frame carrying a grille, for example. Air flowing in the air flow direction 95 can thus reach the unprotected section 24 without passing through the grille 50. If the grille or grilles 50 are clogged with ice, air can still continue to flow in the air stream 90.

[0087] Thus, according to the method applied, at least one grille 50 is arranged upstream of the air stream 90 in the air flow direction 95, by arranging it in line with the intake section 20 and the casing 15 parallel to the axis of rotation AXROT.

[0088] Each grille 50 may optionally be arranged, parallel to the axis of rotation AXROT, upstream of at least a part of the convergent section 16, or of at least a part of the blade path 17, or of the divergent section 18. Optionally, the entire casing 15 may be protected from ice by one or more grilles 50. A grille 50 may in particular be arranged upstream of the rear sector 151 of the casing 15 with respect to a direction opposite the direction of forward travel AV, in order to protect it.

[0089] On a conventional ducted helicopter, in icing conditions, the air 85 arriving from the front zone 6 of the moving rotorcraft hits the casing 15. This air 85 may be loaded with supercooled water droplets, and may cause ice to form on this casing 15.

[0090] According to the disclosure, in icing conditions, each grille 50 is hit by supercooled water droplets that may be present in the air 85. The supercooled water droplets freeze on impact on each grille 50. The ice formed in this way quickly clogs the grille or grilles 50. As a result, each clogged grille 50 then prevents supercooled water droplets present in the air from reaching the zones of the casing 15 which it protects. In particular, each grille 50 can limit the accumulation of ice on the convergent section 16, the blade path and the divergent section 18, as the case may be, in particular at the rear sector 151. Each grille 50 thus makes it possible at least to limit the risk of ice forming on the casing 15 delimiting the air stream 90. The casing 15 can therefore always help effectively control yaw motion.

[0091] FIGS. 2 to 10 show various ice protection systems 40.

[0092] With reference to FIG. 2 and regardless of the embodiment of the ice protection system 40, each grille 50 may be fastened to a frame 80, this frame 80 itself being fastened to the fairing 11.

[0093] According to another optional feature and regardless of the embodiment of the ice protection system 40, each grille may be arranged frontally facing the air flow 85 running along the rotorcraft 1 and arriving from the front zone 6. This arrangement makes it possible to collect supercooled water droplets before they hit the casing 15.

[0094] According to another optional feature, regardless of the embodiment of the ice protection system 40 and as shown in FIG. 3, for example, each grille 50 may be domed, with a concave face 55 turned towards the air stream 90. Each grille 50 is thus domed towards the front zone 6 in order to optimize ice collection.

[0095] According to another optional feature, regardless of the embodiment of the ice protection system 40 and as shown in FIG. 3, for example, each grille 50 extends facing a periphery of said intake section 20 parallel to the axis of rotation AXROT. Such positioning helps protect the casing 15 of the fairing 11 surrounding the air stream 90.

[0096] In particular, each grille 50 may at least partially cover the front section 23 or the rear section 22 of the periphery 21 of the intake section 20.

[0097] According to FIGS. 2 to 4, the ice protection system 40 may comprise two grilles 51, 52 in order to possibly protect the entire casing 15. The unprotected section 24 then comprises the central zone 210.

[0098] The two grilles 51, 52 may comprise a front grille 52 facing the front section 23 and a rear grille 51 facing the rear section 22 of the periphery 21 parallel to the axis of rotation AXROT.

[0099] According to FIG. 3, the front 52 and rear 51 grilles are different but may extend transversely the same distance away from the intake section 20.

[0100] According to FIG. 4, the front grille 52 extends transversely parallel to the axis of rotation AXROT over a first distance D1 and the rear grille 51 extends transversely parallel to the axis of rotation AXROT over a second distance D2. However, the second distance D2 is smaller than the first distance D1 in order to promote ice collection.

[0101] According to FIGS. 5 and 6, the ice protection system 40 may comprise a single front grille 52 arranged facing the front section 23 of the periphery 21 and the front sector 152 of the casing 15. The unprotected section 24 then comprises the central zone 210 and the rear section 22. Optionally, the front grille 52 may cover part of the central zone 210. The front grille 52 allows supercooled water particles to be collected from the air 85 before the intake section 20.

[0102] According to FIGS. 7 and 8, the ice protection system 40 may comprise a single rear grille 51 arranged facing the rear section 22 of the periphery 21. The unprotected section 24 then comprises the central zone 210 and the front section 23.

[0103] Indeed, the supercooled water droplets in the air 85 may be deposited mainly on the rear sector 151 of the casing 15, due to of the movement of the rotorcraft 1. It is therefore possible to envisage positioning a grille 50 only at the rear section 22.

[0104] According to FIGS. 1 to 8, each grille 51, 52 extends in a curved line and, for example, over an arc of a circle that may be centered on the axis of rotation AXROT, and in particular over a semicircle. According to embodiments that are not shown here, each grille 50 may extend over an arc of a circle covering an angular sector of less than 180° in order to partially cover the rear section 22 or the front section 23 of the periphery 21.

[0105] According to FIGS. 9 and 10, the intake section 20 comprises, in the forward direction, a first section 26 that is extended by a second section 27 from a hub 14 of the rotor 12, a rear grille 51 then covering the first section 26.

[0106] Naturally, the present disclosure is subject to numerous variations as regards its implementation. Although several embodiments are described above, it should readily be understood that it is not conceivable to identify exhaustively all the possible embodiments. It is naturally possible to replace any of the means described with equivalent means without going beyond the ambit of the present disclosure.