| 摘要 |
A gas turbine engine (10, fig 1) has a nacelle (21, fig 1), a plurality of pipes 32 and a drains assembly 50. The drains assembly 50 has a drains mast (54) that extends through the nacelle (21, fig 1) and provides an outlet 66 for the pipes 32, the drains assembly 50 also having a connection block 56 which defines internal passages 58 arranged to connect the pipes 32 and the drains mast 54. The connection block 56 comprises lateral connections to the pipes 32 enabling the nacelle (21, fig 1) to have a lower profile thereby reducing aerodynamic drag. |
