CPC B64D 33/08 (2013.01) [B64C 27/12 (2013.01); F01P 1/06 (2013.01); F01P 11/10 (2013.01); F16H 57/0416 (2013.01)] | 10 Claims |
1. A rotorcraft, comprising:
a fuselage;
one or more engines coupled to the fuselage;
a transition duct assembly coupled to the fuselage, wherein the transition duct assembly comprises:
a shared connector comprising an articulatable partition that forms a plurality of channels within the shared connector;
a plurality of primary cooling pathways for cooling one or more systems or components, wherein each of the primary cooling pathways is in fluid communication with a respective channel within the shared connector:
a respective transition duct in fluid communication with a single respective channel within the shared connector; and
a respective transition connector in fluid communication with the respective transition duct, wherein articulation of the articulatable partition from a first to a second position allows for air flow over most or all of a cooling apparatus.
|