Patent ID: 8757540
Filing Date: 2014-06-24
Classification: B64D

Abstract:
1. A nacelle inlet for a turbofan engine having an engine centerline, comprising an annular inlet lip mounted to an inlet section of the nacelle, the annular inlet lip being made from a single continuous piece of material separate from that of the inlet section, the annular inlet lip being concentric relative to the engine centerline, the annular inlet lip having a constant cross-section all along a circumference thereof, the annular inlet lip having an external surface and an internal surface joined by a rounded leading edge, the external surface being spaced radially outwardly from the internal surface relative to the engine centerline, the external surface being axially shorter than the internal surface, and a forwardly canted conical bulkhead extending between said external surface and said internal surface and defining with the annular inlet lip an anti-icing cavity, wherein said inlet section of the nacelle has an external surface and an internal surface, the external surface of the inlet section of the nacelle being connected to the external surface of the inlet lip along a first joint, the internal surface of the inlet section of the nacelle being connected to the internal surface of the inlet lip along a second joint, the first joint being located axially forwardly of the second joint, wherein said forwardly canted conical bulkhead has a radially outer end provided with a forwardly projecting flange spanning the first joint and a radially inner end provided with a rearwardly projecting flange spanning the second joint, and wherein the forwardly canted conical bulkhead has a conical wall extending between the radially outer and inner ends thereof, and wherein the entirety of said conical wall is disposed axially rearwardly from said first joint.