CPC F02K 1/52 (2013.01) [B64D 27/18 (2013.01); B64D 29/06 (2013.01); F02K 1/805 (2013.01); F02K 3/06 (2013.01); B64D 27/26 (2013.01); F05D 2220/323 (2013.01); F05D 2240/128 (2013.01)] | 15 Claims |
1. An assembly for an aircraft propulsion system, comprising:
a nozzle extending axially along and circumferentially about an axial centerline, the nozzle including a nozzle panel and a nozzle fairing fixedly connected to the nozzle panel at an axial end of the nozzle;
the nozzle configured with a first internal flow passage radially between the nozzle panel and the nozzle fairing, the first internal flow passage extending axially within the nozzle to a first outlet between the nozzle panel and the nozzle fairing at the axial end of the nozzle; and
the nozzle further configured with a second internal flow passage radially between the nozzle panel and the nozzle fairing, and the second internal flow passage extending axially within the nozzle to a second outlet between the nozzle panel and the nozzle fairing at the axial end of the nozzle, wherein the second internal flow passage is circumferentially adjacent the first internal flow passage.
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