| 摘要 |
<p>A gas turbine engine assembly is connected to a pylon (14) for mounting the gas turbine engine (10) to an aircraft. The assembly has a frame (26) supporting at least one accessory (35, 50) independently of the gas turbine engine (10). The frame (26) is attached to the pylon (14) at forward and rearward engine mounting locations (16, 18). The frame (26) comprises at least one hollow tube (30, 32, 38) and the at least one hollow tube (30, 32, 38) is fluid tight. The at least one hollow tube (30, 32, 38) is evacuated or contains pressurised fluid and a pressure sensor (76) is provided to detect a change in the pressure in the at least one hollow tube (30, 32, 38) to determine if there is a leak in the at least one hollow tube (30, 32, 38) and hence if the frame (26) is damaged. This ensures that the frame (26) may be repaired or replaced before there is a loss of operation of one or more of the accessories (35, 50) which may result in a failure of the gas turbine engine.</p> |
