Gas turbine engine with fan track liner having triply periodic minimal surface reinforcement
AssigneeRolls-Royce North American Technologies Inc.
InventorTimothy Unton
Life of this patent
Estimating the term…
Abstract
A fan case assembly adapted for use with a gas turbine engine includes a fan case and a fan track liner. The fan case that extends circumferentially about an axis. The fan track liner extends circumferentially at least partway about the axis and is coupled with the fan case. The fan track liner includes an abradable section and a core section located radially outward of the abradable section. The core section defines a triply periodic minimal surface geometry.
Claims19
A fan case assembly adapted for use with a gas turbine engine, the fan case assembly comprising
- a fan track liner that extends circumferentially at least partway about a central axis of the gas turbine engine and axially between a forward end and an aft end spaced apart axially from the forward end, the fan track liner includes an abradable section comprising an abradable material that extends between the forward end and the aft end to define a gas path of the gas turbine engine, a septum section that comprises a composite material and is bonded to the abradable section radially outward of the abradable section, and a core section bonded to the septum section and configured to dissipate energy of a fan blade during a blade off event, and
- an annular case configured to support the fan track liner at a radial position relative to the central axis, the annular case including an outer wall that extends circumferentially around the central axis of the gas turbine engine and a hook that extends radially inward and axially aft from the outer wall,
- wherein the core section of the fan track liner comprises a triply periodic minimal surface geometry having a variable density that increases in at least one of a radially outward direction and an axially aft direction so that the initial impact of the fan blade with the fan track liner during the blade off event allows the fan blade to move into the fan track liner with relatively low resistance while the fan track liner provides relative high resistance as the fan blade moves radially outward to provide additional energy absorption to capture the fan blade in the fan track liner after the initial impact.
A fan case assembly adapted for use with a gas turbine engine, the fan case assembly comprising
- a fan case that extends circumferentially about an axis, and
- a fan track liner that extends circumferentially at least partway about the axis and coupled with the fan case, the fan track liner including an abradable section and a core section located radially outward of the abradable section, wherein the core section defines a triply periodic minimal surface geometry,
- wherein the triply periodic minimal surface geometry has a variable density that increases in at least one of a radially outward direction and an axially aft direction.
A method comprising
- forming a core section to define a triply periodic minimal surface geometry having a variable density that increases in at least one of a radially outward direction and an axially aft direction, the core section extending circumferentially at least partway about an axis and axially between a forward end and an aft end spaced apart axially from the forward end,
- adding an abradable section on the core section radially inward of the core section to form a fan track liner, the abradable section comprising an abradable material, and
- coupling the fan track liner to an annular case that extends circumferentially at least partway about the axis.
Dependencies are inferred from the claim text.