SYSTEM TO ELIMINATE ICING OF TURBINE ENGINE NOSE FAIRING INLET FRONT EDGE Russian patent published in 2010 - IPC F02C7/47 

FIELD: engines and pumps.

SUBSTANCE: proposed system intended, particularly for aircraft turbine engine has a hollow front edge that bounds circular chamber closed by first inner baffle. It incorporates hot air forced feed pipe to be connected on front edge rear end to hot air line injector. Aforesaid pipe passes through air intake nose fairing chamber constricted, on its front, by first inner baffle and, on its rear, by second inner baffle. Inner protective casing is arranged in aforesaid nose fairing chamber to bound isolated space surrounding aforesaid hot air feed pipe. Two elements formed by said feed pipe and protective casing are rigidly attached to one of the baffles, on the one hand. On the other hand, said two elements are rigidly jointed together to slide along plain bearing arranged in the other baffle. Protective casing features a lengthwise rigidity. Aforesaid feed pipe comprises at least two telescoping parts to slide relative to each other that are tightly coupled together.

EFFECT: ruling out baffle deformation.

6 cl, 11 dwg