ANTI-ICING SYSTEM FOR GAS TURBINE ENGINE AIR INTAKE FRONT EDGE FAIRING Russian patent published in 2009 - IPC F02C7/47 

FIELD: aircraft engineering.

SUBSTANCE: invention relates aircraft engineering, particularly to anti-icing system for aircraft gas turbine engine air intake front edge fairing. The air intake hollow front edge constricts circular chamber closed by the 1^st inner baffle and comprises compressed hot air feed duct with its rear end, opposite to aforesaid front edge, connected to compressed hot air circuit, while its front edge, facing that of air intake, is connected to injector forcing compressed hot air into front edge circular chamber. Air feed duct passes the front air intake fairing constricted, from its front, by the 1^st inner baffle, and, from its rear, by the 2^nd inner baffle. Inner protective enclosure is accommodated in the fairing chamber to constrict isolated volume with air feed duct the latter and protective enclosure feature one-way rigidity. Both have their one side attached to one of aforesaid baffles. The protective enclose opposite side can slide relative to plain bearing mounted in the other baffle. Air feed duct is joined to protective enclosure with the help of elastic wall that covers aforesaid isolated volume to allow relative lengthwise displacements between aforesaid air feed duct and protective enclosure.

EFFECT: no deformation of baffles, no used of stiffness elements for aforesaid baffles.

11 cl, 8 dwg