| 摘要 |
An aerofoil assembly for a gas turbine engine comprises: (a) a turbine aerofoil 34 pivotally connected to an outer casing 28 of the turbine engine; (b) a bushing assembly 58 carried by the outer casing 28 and positioned over a trunnion 54 of the aerofoil 34 so as to transfer gas loads from the aerofoil 34 to the outer casing 28, the bushing assembly 58 comprises: (i) a bushing 60 having a first bore which receives the trunnion 54, the bushing 60 having a first electrical junction carried by an outer surface of the bushing 60, and a first conductor extending from the first electrical junction; (ii) a housing 62 which receives the bushing 60 for rotation therein, the housing 62 having a second electrical junction and a second conductor extending from the second electrical junction for electrical connection to an electrical power source; and (iii) a clock spring 90 electrically connected between the first electrical junction and the second electrical junction; and (c) a heating element 72 disposed on an outer surface of the aerofoil 34 and electrically connected to the second conductor via the bushing assembly 58. |
