US 12,078,082 B2
Non-axisymmetric secondary duct portion
Aurélien Mazzella, Moissy-Cramayel (FR); and Laurent Soulat, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/438,058
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Mar. 11, 2020, PCT No. PCT/FR2020/050505
§ 371(c)(1), (2) Date Sep. 10, 2021,
PCT Pub. No. WO2020/183109, PCT Pub. Date Sep. 17, 2020.
Claims priority of application No. 1902476 (FR), filed on Mar. 12, 2019.
Prior Publication US 2022/0251961 A1, Aug. 11, 2022
Int. Cl. F01D 9/04 (2006.01); F02K 3/02 (2006.01)
CPC F01D 9/041 (2013.01) [F02K 3/02 (2013.01); F05D 2260/606 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A portion of a bypass of a turbomachine extending about a longitudinal axis, comprising:
an outer wall and an inner wall, defining a secondary flowpath portion,
a grid of outlet guide vanes, each outlet guide vane extending within the secondary flowpath portion between the outer wall and the inner wall,
wherein, at the grid of outlet guide vanes and in a plane orthogonal to the longitudinal axis, a distance from the outer wall to the longitudinal axis along a first axis orthogonal to the longitudinal axis is greater than a distance from the outer wall to the longitudinal axis along a second axis orthogonal to the longitudinal axis and to the first axis,
wherein the outer wall defines in the plane orthogonal to the longitudinal axis a concave-like shape when viewed from an interior of the secondary flowpath, and
wherein the inner wall defines in said plane orthogonal to the longitudinal axis a shape identical to that of the outer wall, so that a height of the flowpath is generally constant.