Abstract: Systems and methods for attaching a protective liner to a an aircraft engine component having a different coefficient of thermal expansion in comparison to the protective liner include a mounting member configured to be mounted to the aircraft engine component and an attachment member configured to be attached to the protective liner. The mounting member and the attachment member are coupled to each other such that a portion of the mounting member is received within a portion of the attachment member and such that the mounting member is permitted to move with both radial and rotational freedom relative to the attachment member.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed for a structure of an engine component, including a first plurality of unit cells offset from a neutral plane in a first direction, a second plurality of unit cells offset from the neutral plane in a second direction, a plurality of nodes joining ones of the first plurality of unit cells and ones of the second plurality of unit cells, wherein the first plurality of unit cells and the second plurality of unit cells are arranged in pairs such that ones of the first plurality of unit cells are laterally adjacent to and interconnected with ones of the second plurality of unit cells, and wherein the structure is a stiffened structure.

Abstract: A sealing apparatus for a gas turbine engine includes: a first component; a second component positioned in proximity to the first component such that cavity is defined between the first and second components; a resilient seal disposed in the cavity so as to block gas flow between the first and second components, the resilient seal having a first contact surface contacting the first component and a second contact surface contacting the second component; and wherein the resilient seal is configured so as to produce a rolling movement in response to relative movement of the first and second components.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed for a structure of an engine component, including a first plurality of unit cells offset from a neutral plane in a first direction, a second plurality of unit cells offset from the neutral plane in a second direction, a plurality of nodes joining ones of the first plurality of unit cells and ones of the second plurality of unit cells, wherein the first plurality of unit cells and the second plurality of unit cells are arranged in pairs such that ones of the first plurality of unit cells are laterally adjacent to and interconnected with ones of the second plurality of unit cells, and wherein the structure is a stiffened structure.

Abstract: Light weight fan casing configurations for energy absorption are disclosed herein. An apparatus includes a first set of metal bands positioned within a containment casing of a turbofan engine, and a second set of metal bands traversing the first set of metal bands, the first set of metal bands and the second set of metal bands to surround at least a portion of the turbofan engine.

Abstract: A sealing apparatus for a gas turbine engine includes: a first component; a second component positioned in proximity to the first component such that cavity is defined between the first and second components; a resilient seal disposed in the cavity so as to block gas flow between the first and second components, the resilient seal having a first contact surface contacting the first component and a second contact surface contacting the second component; and wherein the resilient seal is configured so as to produce a rolling movement in response to relative movement of the first and second components.

Abstract: A fan case with crack-arresting backsheet structure and removable containment cartridge is disclosed. An example engine fan case includes a segmented backsheet structure, the segmented backsheet structure including at least a first backsheet segment of a first length and a second backsheet segment of a second length, the first backsheet segment coupled to the second backsheet segment and at least one of the first backsheet segment or the second backsheet segment coupled to the fan case, a honeycomb structure, and a containment structure for blade fragment retention, the containment structure coupled to the segmented backsheet structure.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed for a structure of an engine component, including a first plurality of unit cells offset from a neutral plane in a first direction, a second plurality of unit cells offset from the neutral plane in a second direction, a plurality of nodes joining ones of the first plurality of unit cells and ones of the second plurality of unit cells, wherein the first plurality of unit cells and the second plurality of unit cells are arranged in pairs such that ones of the first plurality of unit cells are laterally adjacent to and interconnected with ones of the second plurality of unit cells, and wherein the structure is a stiffened structure.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed for a structure of an engine component, including a first plurality of unit cells offset from a neutral plane in a first direction, a second plurality of unit cells offset from the neutral plane in a second direction, a plurality of nodes joining ones of the first plurality of unit cells and ones of the second plurality of unit cells, wherein the first plurality of unit cells and the second plurality of unit cells are arranged in pairs such that ones of the first plurality of unit cells are laterally adjacent to and interconnected with ones of the second plurality of unit cells, and wherein the structure is a stiffened structure.

Abstract: A fan case with crack-arresting backsheet structure and removable containment cartridge is disclosed. An example engine fan case includes a segmented backsheet structure, the segmented backsheet structure including at least a first backsheet segment of a first length and a second backsheet segment of a second length, the first backsheet segment coupled to the second backsheet segment and at least one of the first backsheet segment or the second backsheet segment coupled to the fan case, a honeycomb structure, and a containment structure for blade fragment retention, the containment structure coupled to the segmented backsheet structure.

Abstract: A sealing apparatus for a gas turbine engine includes: a first component; a second component positioned in proximity to the first component such that cavity is defined between the first and second components; a resilient seal disposed in the cavity so as to block gas flow between the first and second components, the resilient seal having a first contact surface contacting the first component and a second contact surface contacting the second component; and wherein the resilient seal is configured so as to produce a rolling movement in response to relative movement of the first and second components.

Abstract: A method for assembling a compressor for use with a turbine is provided. The method includes coupling at least a first stator ring to a second stator ring via at least one fastener sized to extend through at least one stator ring opening. The method further includes coupling a shield assembly to at least one of the first stator ring and the second stator ring to facilitate reducing convection and aerodynamic bleed losses of the at least one stator ring. The shield assembly includes a downstream surface, a retaining portion, and a contoured upstream surface extending from the downstream surface to the retaining portion.

Abstract: A method for assembling a compressor for use with a turbine is provided. The method includes coupling at least a first stator ring to a second stator ring via at least one fastener sized to extend through at least one stator ring opening. The method further includes coupling a shield assembly to at least one of the first stator ring and the second stator ring to facilitate reducing convection and aerodynamic bleed losses of the at least one stator ring. The shield assembly includes a downstream surface, a retaining portion, and a contoured upstream surface extending from the downstream surface to the retaining portion.

Abstract: A rotor assembly or “blisk” for a gas turbine engine includes a metallic hub having an annular flowpath surface, and at least one blade extending outwardly from the flowpath surface. The blade includes a metallic body having a first density. The metallic body defines a shank portion and an airfoil portion having opposed pressure and suction sides, and is integral with the hub. An insert having a second density less than the first density is carried by the body, and the insert and the body collectively define an airfoil shape. A method is also provided for manufacturing a rotor assembly.

Abstract: A rotor assembly or “blisk” for a gas turbine engine includes a metallic hub having an annular flowpath surface, and at least one blade extending outwardly from the flowpath surface. The blade includes a metallic body having a first density. The metallic body defines a shank portion and an airfoil portion having opposed pressure and suction sides, and is integral with the hub. An insert having a second density less than the first density is carried by the body, and the insert and the body collectively define an airfoil shape. A method is also provided for manufacturing a rotor assembly.

Abstract: A connector support block has a recess defined in part by an arcuate surface for limiting deflection of a main lead connector coupled between the main lead terminal and the innermost turn of end coils on a generator. The recess is spanned by a pin displaceable in elliptical openings in flanges defining the recess and about which pin the main lead connector makes a 180.degree. bend. By limiting the deflection of the main lead connector, stresses introduced into the main lead connector at the 180.degree. bend, a 90.degree. bend and the joint between the main lead connector and innermost turn are reduced under cyclic loading whereby increased fatigue life of the main lead connector is provided.