AIRCRAFT TURBOMACHINE OUTLET GUIDE BLADE CONTAINING A CURVED LUBRICANT CHANNEL OF IMPROVED DESIGN Russian patent published in 2021 - IPC F01D9/06 F01D25/08 F01D25/18 F01D5/18 F02C7/14 

FIELD: aviation.

SUBSTANCE: invention relates to a guide blade (24) for a two-circuit turbomachine of an aircraft the aerodynamic part (34) of which consists of the first inner channel (50a) for cooling lubricant, in which heat transfer means are located, and the second inner channel (50b) for cooling lubricant, in which the heat transfer means are located. The aerodynamic part has a curved region (54) connecting the lubricant outlet end of the first inner channel (50a) with the lubricant inlet end of the second channel (50b). The curved region extends along the curved generatrix and is partially bounded by the lower wall and the upper wall of the blade. According to the invention, the curved region (54) includes one or more lubricant guides (84) located between the lower and upper walls of the blade, each of which extends substantially parallel to the curved generatrix of the curved region (54). By providing a lubricant guide, recirculation of the lubricant is preferably prevented. In addition, the guides enhance heat transfer by increasing the surface that the lubricant contacts and also increase the mechanical strength of the bent region.

EFFECT: invention performs its functions effectively.

10 cl, 11 dwg