Patent ID: 9714627
Date: 2017-07-25
CPC Classifications: B64D,F02C,F02K,F05D,Y02T

Claim:
1. A propulsion system of an aircraft comprising: a pylon adapted to be mounted to an aircraft; an inner fixed structure adapted to surround an engine core, the inner fixed structure mounted via at least a first hinge to the pylon; and an outer sleeve, the outer sleeve mounted via at least a second hinge to the pylon; wherein a side surface of the pylon is generally aerodynamically smooth, the side surface being located between the first hinge and the second hinge; and wherein the side surface of the pylon, the inner fixed structure and the outer sleeve help define a bypass air duct for bypass air from a fan, the side surface being exposed to a bypass air flowpath, wherein the side surface of the pylon spans an axial direction parallel to an engine axis and spans a radial direction perpendicular to the axial direction, the first hinge being spaced from the second hinge in the radial direction, and the side surface comprising a concave geometry along the radial direction at an axial location of the first hinge and the second hinge.