Safran Aero Boosters Sa

David Bouillon

Ghislain Herbaut

Clément Collin

Guillaume Terlinden

M Ghislain Herbaut

The present application relates to a de-icing splitter lip for a low-pressure compressor of a turbofan aircraft engine. The splitter lip surrounds the primary flow and includes an annular splitter wall with a circular leading edge, an outer shroud connected to the splitter wall, and a heating device in an electric ribbon that de-ices the splitter lip. The splitter lip further includes an elastic element made of elastomer, holding the heating device on the inside of the splitter wall. The elastic element is compressed, pre-loaded, in the splitter lip. Thus, the elastic element exerts a force F clamping the heating device against the splitter wall and the outer shroud in order to improve thermal contact. The present application also provides a method for assembling a splitter lip.

De-icing splitter lip for axial turbomachine compressor

The invention proposes a de-icing splitter nose at the inlet of the low-pressure compressor of a double-flow turbine engine. The splitter nose comprises an annular separation surface with a circular leading edge, the surface being adapted to separate an upstream flow into a primary flow and a secondary flow. The nose further comprises an electric de-icing device with a heating element having a series of parallel, electric, heating strips. The strips are inserted between two strata of dielectric material and are able to prevent the formation of ice on the annular surface, as close as possible to the leading edge.

De-icing nose for low-pressure compressor of an axial turbine engine

The invention deals with a splitter nose delimiting the inlet of a low-pressure compressor of an axial turbine engine. The splitter nose comprises a separation surface with an upstream circular edge suitable for separating a flow entering into the turbine engine into a primary flow and a secondary flow, and a plasma de-icing device. The device comprises two annular layers of dielectric material () partially forming the separation surface, an electrode forming the upstream edge, an electrode forming an outer wall of the splitter nose, an electrode forming an outer shroud which supports blades, an electrode delimiting the primary flow. The device generates plasmas () opposing the presence of ice on the partitions of the splitter nose. The invention also deals with a turbine engine with a splitter nose that is provided with a de-icing system downstream of the fan.

Splitter nose with plasma de-icing for axial turbine engine compressor

The invention proposes a splitter lip for a low-pressure compressor of an axial turbomachine for an aeroplane. The splitter lip comprises an upstream annular wall made of metal with a circular leading edge, and a downstream annular partition made of an organic-matrix, short-fiber composite material. The splitter lip also supports an outer shroud for a stator upstream of the compressor. The upstream wall comprises an annular anchoring portion arranged in the thickness of the downstream partition so as to anchor the partition and the wall to one another. The anchoring portion has distributed hexagonal openings in order to increase anchoring. The invention also proposes a method for producing, by molding, a bi-material splitter lip or a mixed lip.

Composite splitter lip for axial turbomachine compressor

A de-icing and anti-icing splitter for an axial turbine engine low-pressure compressor has an external annular wall delimiting the secondary or bypass flow, and an internal annular wall; notably an external stator shroud; delimiting the primary or main stream. The upstream edge of the internal wall is fixed to the upstream annular hook of the external wall. The splitter has a series of notches which pass radially through the internal wall to allow de-icing fluid to circulate through the hook. The notches may form crescents. The splitter becomes simpler while at the same time maintaining optimal efficiency.

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Woluwe-Saint-Lambert, Belgium

David Bouillon