Turbofan engine de-icing compressor and de-icing process
An aircraft turbojet engine low-pressure compressor or booster, comprising an inlet structure de-iced by a pressurized hot fluid circulation coming from the high-pressure compressor. The de-icing structure comprises a deformable membrane through the thickness of which the pressurized fluid circulation passes. When there is a build-up of ice on the membrane, the pressurized fluid circulation is blocked, resulting in its pressure deforming the membrane in such a manner as to crack the build-up of ice.
1. An axial turbine engine compressor comprising:
a de-icing structure capable of being de-iced by a pressurized fluid circulation, wherein the de-icing structure comprises:
at least one deformable membrane having a thickness through which the pressurized fluid circulation can pass, wherein the de-icing structure is configured in such a manner that a build-up of ice on the at least one deformable membrane blocks or reduces the pressurized fluid circulation, and wherein in the event of a blockage or reduction in the circulation, the pressure of the pressurized fluid deforms the at least one deformable membrane in such a manner as to fracture the build-up of ice, and
at least one body with an external surface covered by the at least one deformable membrane, such that in the absence of ice the at least one deformable membrane is configured to be pressed against the external surface and in the presence of ice the at least one deformable membrane is configured to be moved away from the external surface via the pressurized fluid.
2. The compressor according to claim 1 , wherein the deformable membrane comprises an escape orifice for the pressurized fluid, the orifice being configured to be plugged by the build-up of ice.
3. The compressor according to claim 1 , wherein the de-icing structure comprises at least two annular rows of stator vanes, an upstream row and a downstream row, the at least one deformable membrane being disposed on one of the vanes of the downstream row.
4. The compressor according to claim 1 , wherein deformable membrane comprises a neoprene material permeable to the pressurized fluid.
5. The compressor according to claim 1 , wherein the deformable membrane comprises a metal sheet.
6. The compressor according to claim 1 , wherein the body comprises a zone of reduced thickness receiving the deformable membrane.
7. The compressor according to claim 1 , wherein the external surface comprises at least one channel extending with respect to the deformable membrane and intended to be passed through by the pressurized fluid.
8. The compressor according to claim 1 , wherein the body comprises a shoulder along which the deformable membrane is mounted in a leak-proof manner.
9. The compressor according to claim 1 , wherein the deformable membrane is capable of moving between a first position occupied in the absence of ice and a second position occupied in the presence of ice as a result of the pressurized fluid pressure being capable of at least one of moving the deformable membrane from the first position towards the second position, acting against a dynamic pressure of a fluid in the turbojet engine and overcoming the mechanical resistance of the build-up of ice.
10. The compressor of claim 1 , wherein the at least one deformable membrane further comprises:
at least one flow separation line, the at least one deformable membrane being capable of being passed through by the pressurized fluid at the separation line.
11. The compressor according to claim 10 , wherein the de-icing structure comprises a splitter with a circular separation edge formed by the separation line.
12. The compressor according to claim 10 , wherein the de-icing structure comprises a vane with a leading edge formed by the separation line.
13. The compressor according to claim 12 , wherein the vane comprises a lower surface and an upper surface extending from the leading edge, the deformable membrane forming, at least in part at least one of the upper surface and the lower surface.
14. A de-icing process of an axial low-pressure turbofan engine compressor, the process comprising the stages:
icing of a surface of the axial low-pressure turbofan engine compressor, the surface being in contact with a flow; and
detachment of ice from the surface by a pressurized gas,
wherein the surface is formed by a membrane that is permeable to the pressurized gas and deformable between a first configuration and a second configuration, wherein during the icing stage the permeability of the membrane drops with the result that the pressure of the pressurized fluid pushes the membrane into the second configuration, allowing the ice detachment stage to be carried out,
the surface forming, together with at least one body, a de-icing structure, wherein the at least one body is provided with an external surface covered by the deformable membrane, and wherein in the absence of ice the deformable membrane is configured to be pressed against the external surface and in the presence of ice the deformable membrane is configured to be moved away from the external surface via the pressurized fluid.
15. The process according to claim 14 , wherein the pressurized fluid is supplied to the compressor in a discontinuous manner.