| 摘要 |
A fan section (16) of a gas turbine engine includes a fan assembly (28), a fan containment case (30), and a plurality of structural exit guide vanes (34). The fan assembly (28) includes a fan rotor hub (36) centered on and rotatable about the engine centerline (24), and a plurality of fan blades (38) that are attached to and extend radially out from the fan rotor hub (36). The fan containment case (30) is disposed radially outside of and circumferentially around the fan assembly (25). The fan containment case (30) includes a shell (31) and an integral flange ring (50) that extends around the circumference of the shell (31), a circumferentially extending blade outer air seal (32) disposed between the fan blades (38) and the shell (31). The structural exit guide vanes (34) are mechanically attached to the fan containment case (30) at a position aligned with the integral flange ring (50).
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