| 摘要 |
A compressor rotor structure for a gas turbine engine is made by linear friction bonding stub rooted blades and separate platform pieces, to lands between slots in a compressor disc periphery. These results an integral structure in which the periphery of the disc has had metal removed so as to form the slots and the disc is thus lightened, and the stub roots and platform pieces cooperate to form the airflow inner annulus wall. |
