Abstract:
A composite fan case has a generally cylindrical composite shell, at least one band of sacrificial composite material circumscribing an outer surface of the composite shell, and a metallic rail mounted on the band of sacrificial material. Also disclosed is a method of construction the aforementioned case.
Abstract:
A blade containment system includes a plurality of circumferentially-arranged rotatable blades. Each blade has a blade compliance. An annular containment structure is arranged around the rotatable blades. The containment structure includes a liner that has a liner compliance. The blade compliance and the liner compliance are configured such that a strain induced on a respective one of the blades upon impact with the liner is less than a threshold critical strain beyond which the rotatable blades fracture.
Abstract:
A casing for installation in more than one circumferential position, includes a shell into which fluid may drain, a pre-installation bottom dead center of the shell, a first post-installation bottom dead center of the shell wherein the first post-installation bottom dead center of the shell is circumferentially rotated a first number of degrees in a first direction from the pre-installation bottom dead center of the shell. The non-limiting embodiment further discloses a first ramp disposed between the first post-installation bottom dead center of the shell and the pre-installation bottom dead center of the shell for directing fluid from the first post-installation bottom dead center of the shell to the pre-installation bottom dead center of the shell.
Abstract:
A fan platform section (300) may include a flow path portion (310) with a plurality of composite plies. A first composite ply (830) in the plurality of composite plies may include directional fibers (835). The directional fibers may be configured to prevent twisting of the flow path section in response to a centripetal load. The fan platform section may include a second composite ply (820) in the plurality of composite plies. The second composite ply may include directional fibers (825). The directional fibers in the first composite ply may be orthogonal with respect to the directional fibers in the second composite ply.
Abstract:
A fan section of a gas turbine engine includes a fan containment case assembly includes an outer case of an aluminum alloy. The outer case extends circumferentially around an axial centerline. A thermally conforming liner assembly is located inwardly of the outer case. The thermally conforming liner assembly includes a circumferential liner of an aluminum alloy. A ballistic liner is located between the outer case and the thermally conforming liner assembly.
Abstract:
A fan (42) is provided. The fan (42) may comprise a fan blade (101) and a blade platform (102) coupled to the fan blade (101). The blade platform (102) may be a thermoplastic. A fan blade platform (102) is also provided. The fan blade platform (102) may comprise a first platform half (104) comprising a slot (114) at a first end of the first platform half (104) and a first receiving member (120) at a second end of the first platform half (104) opposite the first end of the first platform half (104). A second platform half (106) may comprise a hook (112). The second platform half (106) may also include a second receiving member (118) at a second end of the second platform half (106) opposite the first end of the second platform half (106) with the hook (112) configured to interface with the slot (114). A pin (116) may be configured to pass through the first receiving member (120) and the second receiving member (118).
Abstract:
A fan blade (100) for use in a gas turbine engine, includes a metallic fan blade body (102), including a fan blade body leading edge (108) and body outer surface (102), extending radially outward from a root (106), and a static dissipative coating material (112) disposed on the body outer surface (102).