Patent ID: 8142144
Filing Date: 2012-03-27
Classification: F02C,F05B,F05D,F16B,Y02T

Abstract:
1. An aircraft turbine engine having a longitudinal axis, the aircraft turbine engine comprising: an air intake provided with a tubular internal wall; and a fan, supplied with air by said air intake and enclosed by a tubular fan casing, with a rear end of said air intake internal wall and a front end of said fan casing being joined together by at least one fastener wherein: at least one of said air intake internal wall and said fan casing is comprised of a resin/fiber composite; said rear end of said air intake internal wall and said front end of said fan casing are uniform, having no projections that join said internal wall and said casing together; said at least one fastener has an axis that makes an angle of at least 60° with respect to said turbine engine longitudinal axis; and the at least one fastener is connected to at least one of the rear end of said air intake internal wall and the front end of said fan casing by a plastically deformable member so as to allow the rear end of said air intake and the front end of said fan casing to pivot relative to one another.