Deicing device for propfan-type propeller blades

Abstract

The invention relates to a deicing device for propfan-type aircraft propeller blades, whereby the propulsion unit (1) comprises a turbine engine (8) rotating at least one rotor (3a) having a plurality of blades (4a) disposed around a ring (5a) that moves with the blades, the outer wall (14a) of said ring forming part of the outer skin of the propulsion unit and said outer skin (6) being subjected to the atmospheric conditions outside the propulsion unit. The aforementioned turbine engine (8) generates a flow of hot gases that are released through a hot annular channel (10) that is concentric with the above-mentioned moving ring (5a), a portion of the surface of said channel being defined by the inner wall (15a) of the moving ring (5a). The invention includes: means (11) for capturing the heat energy from the hot channel (10), which are disposed inside the moving ring (5a); means (12, 13) for transferring the heat energy to the blades (4a) of the rotor; and means (18, 19) for distributing the heat energy over at least one portion of the surface of said blades (4a).

Description

technical field [0001] The invention falls within the field of aeronautical equipment. More specifically, the present invention relates to deicing devices. In this context, the invention specifically concerns the problem of deicing propeller blades. Background technique [0002] During various phases of flight, especially when on the ground, take-off, climb or landing, aircraft are often subjected to icy atmospheric conditions (cold surfaces + ambient humidity), which lead to ice deposits on various parts of the aircraft. These ice deposits alter the aerodynamic performance of the aircraft, increase the mass of the aircraft, and reduce the maneuverability of the aircraft. [0003] Various anti-icing devices (preventing the formation of ice on the surfaces of the aircraft) and de-icing devices (separating ice blocks once they have formed) have been developed over the decades and are known to various experts. For the leading edges, for example, they use heating resistors th...

AI Technical Summary

Problems solved by technology

[0009] One of the main disadvantages of these rotating contact systems is associated with the velocity of the brush relative to the moving track, which undoubtedly depends on the diameter of the circular track and the rotational speed of the part

[0010] A consequence of this for all these rotating contact systems is rapid wear of the brushes, resulting in reduced performance and a requirement for frequent and costly maintenance

The lack of lubrication for these brushes (due to complexity) also results in a significant reduction of this life

[0011] In the case of the front propeller of a propeller fan, the diameter of the core of the turbine results in a relative velocity of the moving part with respect to the stationary part of the order of 400m / s, which makes the use of brush and the system of motion tracks is not available in practice

[0012] The situation is further exacerbated in the case of a propeller fan based on the counter-rotating properties of the two propellers, which in the place where it is necessary to install a device with brushes and conductive tracks, leads to a relative speed between them of 800 m / s

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