Gas turbine engine blade containment assembly

Details Gas turbine engine blade containment assembly Gas turbine engine blade containment assembly

2007-03-20

2007-03-20

Nguyen, Ninh H. (Department: 3745)

Rotary kinetic fluid motors or pumps

Including destructible, fusible, or deformable non-reusable...

C415S220000

Reexamination Certificate

active

11046246

ABSTRACT:
A gas turbine engine rotor blade containment assembly (38) comprises a generally cylindrical, or frustoconical, metal casing (40). The metal casing (40) has at least one arched portion (62, 64, 66) and each arched portion (62, 64, 66) extends circumferentially around the metal casing (40). Each arched portion (62, 64, 66) comprises a radially inwardly extending arch (68) in which the trough (74) of the arch (68) is radially inwardly of a straight line (76) interconnecting the axial ends (70, 72) of the arch (68). The trough (74) of the arch (68) is radially inwardly of the at least one of the axial ends (70, 72) of the at least one arch (68). The arched portions (62, 64, 66) introduce compressive stresses into the metal casing (40) during a fan blade34impact and enable the metal casing (40) to withstand the impact. The fan blade containment assembly (38) is lighter for large diameter turbofan gas turbine engine (10).

REFERENCES:
patent: 4648795 (1987-03-01), Lardellier
patent: 6179551 (2001-01-01), Sathianathan et al.
patent: 6290455 (2001-09-01), Hemmelgarn et al.
patent: 0 965 731 (2000-12-01), None
patent: 1 245 791 (2002-10-01), None
patent: 1 104 837 (2003-01-01), None

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