DEVICE FOR DEICING AN AERONAUTICAL TURBOMACHINE SEPARATOR Russian patent published in 2018 - IPC F02C7/47 F01D25/02 F02K3/04 F01D25/24 

FIELD: engines and pumps.

SUBSTANCE: device for deicing an aeronautical turbomachine separator comprising a separator (20) of streams and a housing (28). Splitter fairing (20) intended to be positioned downstream of a blower (14) of the turbine engine to form a separation between annular flow channels of a primary flow (16) and a bypass flow (18). Separating beak comprises an inner annular wall (22), delimiting outside the flow passage of the primary stream (16), and an outer annular wall (24) defining within the flow of secondary flow stream (18). At its downstream end, the inner wall (22) of the splitter fairing is extended by an annular flange (26) projecting radially toward the outer wall (24). Housing (28) attached to the spout of separation in the downstream extension thereof. Casing having an internal shell ring (30) delimiting on the outside the flow duct for the primary stream. Casing (28) comprising at least one air passage (36) incorporated into the internal shell ring to form one single same component therewith. Air passage opening downstream onto an air supply (38) and opening upstream onto the inside of the separator. Air channel (36) is limited by the inside of the internal shell ring and the outside of the internal shell ring. Outer wall of the internal shell ring (30) is extended at an upstream annular flange (32) which extends radially outwardly and is secured to the flange (26) of the stream separator (20), and the inner shroud (30) of the housing also extends through a downstream annular flange (34) extending radially outwards.

EFFECT: less weight and ease of manufacture.

10 cl, 3 dwg