| 摘要 |
<p>A hinge device (12) for a rotary member (11) of an aircraft engine (1) having a conduit (3) housing the rotary member (11) and for conducting a stream of gas, and a cavity (9) outside the conduit (3) and for receiving a mass of air having, in use, a higher pressure than the conduit (3); the device (12) having a seat (18) formed in a platform (6) interposed between the cavity (9) and the conduit (3), and a pin (16) integral with the rotary member (11) and engaging the seat (18) to rotate about an axis (15); the pin (16) is cooled by a stream of air, which flows inside a passage (42) having an inlet (43) which comes out inside the cavity (9), an outlet (44) which comes out inside the conduit (3), and at least one number of channels (46, 48, 50, 56, 60) formed outside the pin (16) and spaced angularly apart; and part of the passage (46, 48, 50) is formed on a collar portion (33) fitted to the pin (16) to calibrate the flow of air inside the passage (42). <IMAGE></p> |
