Patent ID: 6497550
Filing Date: 2002-12-24
Classification: F01D,Y02T

Abstract:
A gas turbine engine rotor blade containment assembly comprising a generally cylindrical, or frustoconical, containment casing, the containment casing having an upstream portion, a blade containment portion and a transition portion, the upstream portion having a flange connecting the containment casing to an axially adjacent casing, the blade containment portion being downstream of the upstream portion, the diameter of the upstream portion of the casing being greater than the diameter of blade containment portion and the thickness of the blade containment portion being greater than the thickness of the upstream portion, the transition portion connecting the blade containment portion and the upstream portion to transmit loads from the blade containment portion to the flange of the upstream portion, the transition portion having a smoothly curved increase in diameter between the blade containment portion and the upstream portion, the transition portion having a smoothly curved increase in diameter between the blade containment portion and the upstream portion, the transition portion comprising a smoothly curved outer surface and the thickness of the transition portion is substantially constant and a smoothly curved inner surface such that the thickness of the transition portion is substantially the same thickness as the upstream portion of the containment casing whereby the transition region is allowed to flex to reduce impact loads transmitted to the flange of the upstream portion.