NOZZLE FOR AN AIRCRAFT TURBOPROP ENGINE WITH AN UNDUCTED FAN

摘要

The present disclosure provides a nozzle for an aircraft turboprop engine with an unducted fan, including: an inner wall, an outer wall radially spaced apart from the inner wall and concentric with the inner wall, a junction area of the inner and outer walls including an opening contained in a plane transverse to a longitudinal axis of the nozzle. In particular, the junction area of the inner and outer walls includes two connecting plates and a member to secure the two connecting plates together, or in another form, the junction area includes a pad secured to the inner wall, and a pad secured to the outer wall, facing the pad of the inner wall of the nozzle.

主权项

1. A nozzle for an aircraft turboprop engine with an unducted fan, comprising:
an inner wall, an outer wall being radially spaced apart from the inner wall and concentric with the inner wall, a junction area of the inner and outer walls comprising at least one opening contained in a plane substantially transverse to a longitudinal axis of said nozzle, wherein the junction area of the inner and outer walls further comprises means selected from the group consisting of: means for connecting the inner and outer walls, said connecting means comprising at least two connecting plates and means for securing said at least two connecting plates together, and at least one pad secured to the inner wall and at least one pad secured to the outer wall of the nozzle and positioned facing said at least one pad of the inner wall of the nozzle.