Abstract: Aspects of the disclosure regard a fan case assembly for a gas turbine engine, the fan case assembly comprising a fan case having an inner surface, a fan case liner having an outer surface, and a reclosable fastening system attaching the fan case liner to the fan case, the reclosable fastening system comprising two components, a first component being attached to the fan case inner surface and a second component being attached to the fan case liner outer surface.

Abstract: Aspects of the disclosure regard a fan case assembly for a gas turbine engine, the fan case assembly comprising a fan case having an inner surface, a fan case liner having an outer surface, and a reclosable fastening system attaching the fan case liner to the fan case, the reclosable fastening system comprising two components, a first component being attached to the fan case inner surface and a second component being attached to the fan case liner outer surface.

Abstract: According to one aspect, an airfoil assembly for a gas turbine engine comprises a first end wall, a second end wall, an airfoil and a sheath. The first end wall has surfaces defining a first recess, and the second end wall has surfaces defining a second recess. The airfoil includes a first portion disposed in the first recess, a second portion disposed in the second recess, and a leading edge disposed between the first and second portions. The sheath is in contact with the first and second portions of the airfoil covering the leading edge between the surfaces defining the first and second recesses.

Abstract: According to one aspect, an airfoil assembly for a gas turbine engine comprises a first end wall, a second end wall, an airfoil and a sheath. The first end wall has surfaces defining a first recess, and the second end wall has surfaces defining a second recess. The airfoil includes a first portion disposed in the first recess, a second portion disposed in the second recess, and a leading edge disposed between the first and second portions. The sheath is in contact with the first and second portions of the airfoil covering the leading edge between the surfaces defining the first and second recesses.

Abstract: A method of replacing a fan case liner panel in an engine fan case is provided. In one illustrative form, the method may include applying heat to an engine fan case to debond an adhesive layer, removing the first fan case liner panel, and bonding a second fan case liner panel.

Abstract: A rotor for a gas turbine engine includes a central wheel and a plurality of blades that extend outwardly from the central wheel. The blades are non-uniform to reduce flutter and forced response effects induced during operation of a gas turbine engine including the rotor.

Abstract: A gas turbine engine includes a fan positioned in a containment case. The fan includes a fan hub with a number of fan blades extending from the fan hub. A blade motion control system is coupled to the gas turbine engine to detect and control fan blade motion caused by harmonic modes. One or more magnetic materials are coupled to one or more of the fan blades of the gas turbine engine. One or more blade motion sensors are coupled to the containment case and are configured to detect the motion of the magnetic materials coupled to the fan blades. A control unit can adjust one or more operational parameters of the gas turbine engine to disrupt the fan blade motion caused by the detected harmonic modes.

Abstract: A method of replacing a fan case liner panel in an engine fan case is provided. In one illustrative form, the method may include applying heat to an engine fan case to debond an adhesive layer, removing the first fan case liner panel, and bonding a second fan case liner panel.

Abstract: A rotor for a gas turbine engine includes a central wheel and a plurality of blades that extend outwardly from the central wheel. The blades are non-uniform to reduce flutter and forced response effects induced during operation of a gas turbine engine including the rotor.

Abstract: A touch panel is integrated into a flat panel display device having a visual display surface with a front polarizer layer, particularly a liquid crystal display device. The touch panel comprises a flexible transparent membrane containing the front polarizer layer and having a first transparent conductive layer on a lower surface of the flexible transparent membrane and a rigid base comprising the flat panel display device and having a second transparent conductive layer on an upper surface of the rigid base. At least one spacer separates the flexible transparent membrane from the rigid base, keeping the first and second transparent conductive layers in spaced-apart facing relationship. A bus bar and tail communicate a signal from the touch panel to the flat panel display device.

Abstract: The present invention is a method and apparatus for capping and grounding an electrical connector to prevent leakage of electromagnetic interference into or out of a chassis for a piece of electronic equipment. In a preferred embodiment of the present invention, a chassis panel has a conductive area that may serve as chassis ground. The electrical connector is secured to the chassis panel, and it is disposed over a penetration in the chassis panel. The electrical connector has a conductive shell that is electrically tied to chassis ground. An EMI plate caps the electrical connector, and it is also electrically tied to chassis ground. The EMI plate permits the transmission of desired signals into and out of the chassis via the electrical connector and associated conductors while substantially preventing leakage of electromagnetic interference through the electrical connector.