| 摘要 |
A ducted fan gas turbine engine has a fan duct across which extends an aerodynamically configured fairing. The fairing has a leading edge region which is defined by a pair of doors. The doors pivot between a first position in which they define the fairing leading edge region and a second position in which they define an inlet for the flow of air into the fairing. The air flow into the fairing serves to provide cooling of components within the fairing.
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