Abstract: A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the inlet duct area. In a further embodiment of the present invention, the spinner includes a spinner contoured surface for reducing the inlet duct area. In other embodiments, the nacelle and/or the spinner include an inflatable bladder, a SMA actuator, a fluidic actuator, or a combination thereof, selectively activated to increase acoustic attenuation during certain conditions of an aircraft.

Abstract: A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the inlet duct area. In a further embodiment of the present invention, the spinner includes a spinner contoured surface for reducing the inlet duct area. In other embodiments, the nacelle and/or the spinner include an inflatable bladder, a SMA actuator, a fluidic actuator, or a combination thereof, selectively activated to increase acoustic attenuation during certain conditions of an aircraft.

Abstract: A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the inlet duct area. In a further embodiment of the present invention, the spinner includes a spinner contoured surface for reducing the inlet duct area. In other embodiments, the nacelle and/or the spinner include an inflatable bladder, a SMA actuator, a fluidic actuator, or a combination thereof, selectively activated to increase acoustic attenuation during certain conditions of an aircraft.

Abstract: The present invention is a low density hybrid airfoil comprising a temperature resistant exterior layer and a tough, high impact resistant interior layer. Specifically, the airfoil comprises a monolithic ceramic exterior layer and a fiber reinforced ceramic matrix composite interior layer. Both the monolithic ceramic and fiber reinforced ceramic matrix composite are low density materials. Additionally, the monolithic ceramic is a high temperature resistant material, and the fiber reinforced ceramic matrix composite is a relatively high impact resistant structure. Encapsulating the airfoil with a temperature resistant exterior layer protects the airfoil in a high temperature environment, and supporting the airfoil with a high impact resistant, fiber reinforced ceramic matrix composite improves the overall impact resistance of the airfoil thereby resulting in a tough, high temperature resistant, low density airfoil.

Abstract: A valve assembly that is useful for controlling fuel delivery utilizes turbine power available from the steady state fuel flow within the valve assembly. A turbine element, which is moved by the steady state fuel flow, provides a motive force to a valve element that controls fuel delivery through selected outlet members of the valve arrangement. A rotating cage valve member preferably is coupled with the turbine element so that the valve member rotates responsive to movement of the turbine element. A controller determines the rate of rotation of the valve member and selectively controls a braking actuator to control the movement of the turbine element and the valve member.

Abstract: A valve assembly that is useful for controlling fuel delivery utilizes turbine power available from the steady state fuel flow within the valve assembly. A turbine element, which is moved by the steady state fuel flow, provides a motive force to a valve element that controls fuel delivery through selected outlet members of the valve arrangement. A rotating cage valve member preferably is coupled with the turbine element so that the valve member rotates responsive to movement of the turbine element. A controller determines the rate of rotation of the valve member and selectively controls a braking actuator to control the movement of the turbine element and the valve member.

Abstract: The present invention is a low density hybrid airfoil comprising a temperature resistant exterior layer and a tough, high impact resistant interior layer. Specifically, the airfoil comprises a monolithic ceramic exterior layer and a fiber reinforced ceramic matrix composite interior layer. Both the monolithic ceramic and fiber reinforced ceramic matrix composite are low density materials. Additionally, the monolithic ceramic is a high temperature resistant material, and the fiber reinforced ceramic matrix composite is a relatively high impact resistant structure. Encapsulating the airfoil with a temperature resistant exterior layer protects the airfoil in a high temperature environment, and supporting the airfoil with a high impact resistant, fiber reinforced ceramic matrix composite improves the overall impact resistance of the airfoil thereby resulting in a tough, high temperature resistant, low density airfoil.

Abstract: The present invention is a low density hybrid airfoil comprising a temperature resistant exterior layer and a tough, high impact resistant interior layer. Specifically, the airfoil comprises a monolithic ceramic exterior layer and a fiber reinforced ceramic matrix composite interior layer. Both the monolithic ceramic and fiber reinforced ceramic matrix composite are low density materials. Additionally, the monolithic ceramic is a high temperature resistant material, and the fiber reinforced ceramic matrix composite is a relatively high impact resistant structure. Encapsulating the airfoil with a temperature resistant exterior layer protects the airfoil in a high temperature environment, and supporting the airfoil with a high impact resistant, fiber reinforced ceramic matrix composite improves the overall impact resistance of the airfoil thereby resulting in a tough, high temperature resistant, low density airfoil.

Abstract: In a turbo compressor, such as a centrifugal compressor, having swirl inducing structure, such as inlet guide vanes, one or more free rotors are located intermediate the swirl inducing structure and the inlet of the compressor. The free rotors are driven by the flow and the kinetic energy stored therein serves to mitigate transient changes in the flow as perceived at the inlet of the compressor such that a more stable operation results.

Abstract: Respiration therapy is accomplished by generating pulses of inhalation gas for delivery to a patient. The inhalation gas pulses may be generated by entraining humidified low pressure gas with pulses of high pressure entrainment gas. The pulses of entrainment gas may be of variable frequency, duration and duty cycle and are produced by modulating the flow of a highly pressured gas with a solenoid operated valve.

Abstract: Respiration therapy is accomplished by generating pulses of inhalation gas for delivery to a patient. The inhalation gas pulses may be generated by entraining humidified low pressure gas with pulses of high pressure entrainment gas. The pulses of entrainment gas may be of variable frequency, duration and duty cycle and are produced by modulating the flow of a highly pressured gas with a solenoid operated valve.