Abstract: A hybrid fan blade for a gas turbine engine is provided that includes an airfoil and a composite panel. The airfoil has a first side and a second side orientated opposite the first side. The first and second sides extend between a tip, a base, a leading edge and a trailing edge. The airfoil includes a plurality of cavities disposed in the first side of the airfoil, which cavities extend inwardly toward the second side. The cavities collectively form an opening. At least one rib is disposed between the cavities. A shelf is disposed around the opening. The composite panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The first composite panel is a load bearing structure operable to transfer loads to the airfoil and receive loads from the airfoil.

Abstract: A hybrid fan blade for a gas turbine engine is provided that includes an airfoil and a composite panel. The airfoil has a first side and a second side orientated opposite the first side. The first and second sides extend between a tip, a base, a leading edge and a trailing edge. The airfoil includes a plurality of cavities disposed in the first side of the airfoil, which cavities extend inwardly toward the second side. The cavities collectively form an opening. At least one rib is disposed between the cavities. A shelf is disposed around the opening. The composite panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The first composite panel is a load bearing structure operable to transfer loads to the airfoil and receive loads from the airfoil.

Abstract: A method of machining a blade retention slot with an abrasive water jet machining. A straight blade retention slot along an X-axis then a at least one side of the straight blade retention slot is abrasive water jet machined to generate a curved side of the blade retention slot defined within an X-Y plane.

Abstract: A method of machining a curved blade retention slot with electron discharge machining.

Abstract: A turbofan engine includes a variable geometry fan exit guide vane (FEGV) system having a multiple of circumferentially spaced radially extending fan exit guide vanes. Rotation of the fan exit guide vanes between a nominal position and a rotated position selectively changes a fan bypass flow path to permit efficient operation at various flight conditions.

Abstract: A gas turbine engine includes a compressor section, a combustion section communicating with and disposed downstream of the compressor section relative to a direction of airflow, and a gas turbine section communicating with and disposed downstream of the combustion section relative to a direction of airflow. One of the sections has a wall defining an opening to access an airflow through the sections. A bleed diffuser assembly is disposed over the opening, and includes a housing including inlet and outlet ends. A diffuser having inlet and outlet ends is movably disposed within the housing. An actuator is coupled to the diffuser for moving the diffuser generally toward the inlet end of the housing and into an operative position when the actuator is energized. A biasing member is provided for urging the diffuser generally toward the outlet end of the housing and into a retracted position when the actuator is de-energized.

Abstract: A fuel delivery system includes a fuel stabilization unit that receives vibratory energy for mixing fuel within fuel passages to improve the removal of dissolved oxygen from an oxygen containing fuel. A vibration generator transmits vibratory energy into the fuel stabilization unit to induce mixing of fuel. Vibratory energy is directed into the fuel to create enhanced mixing by inducing large-scale secondary flow motions that circulates fuel from a center flow area toward an oxygen permeable surface to improve overall fuel deoxygenation as more of the fuel is placed in adjacent contact with the oxygen permeable membranes.

Abstract: A method and apparatus wherein, during time periods when a turbine is off-line and in a restart-ready condition, residual steam is circulated in the turbine between the cover and base of the turbine such that the cover and base are maintained at generally equal temperatures.

Abstract: A steam turbine monitoring and control system for a steam turbine having a base, a cover and interfacing plant piping system with plural feed water heaters and fluid tanks, includes a plurality of water detectors located in the interfacing plant piping system, for detecting the presence of water or cool fluid, a plurality of heater blankets covering the steam turbine, temperature detector means, coupled to the base and cover of the steam turbine, for detecting temperature differentials between the base and the cover, a water detector controller coupled to the plurality of water detectors and the temperature detector means; and monitor/alarm means, coupled to the water blanket power source, the plurality of heater blankets, the temperature detector means, and the plurality of water detectors, for indicating a condition of potential water induction when water or cool fluid is detected at any one of the plurality of water detectors, and for switching on the heater blankets to maintain absolute and relative tempe

Abstract: Compressor discharge pressure (CDP) in a gas turbine engine is sensed. A fall in CDP is interpreted as indicating compressor stall.