Abstract: A turbine engine including a fan, a nacelle circumscribing at least the fan, a compressor section downstream of the fan, and a conduit defined, at least in part, by the nacelle. The conduit includes a first opening at the compressor section, a second opening downstream of the fan and upstream of the compressor section, and a third opening upstream of the fan. Pressure sensors coupled to the nacelle are communicatively coupled to at least one actuator. The at least one actuator can adjust airflow between the first opening and the second opening, or between the first opening and the third opening. The pressure sensors can provide outputs for generating commands that control the at least one actuator.

Abstract: A turbine engine including a fan, a nacelle circumscribing at least the fan, a compressor section downstream of the fan, and a conduit defined, at least in part, by the nacelle. The conduit includes a first opening at the compressor section, a second opening downstream of the fan and upstream of the compressor section, and a third opening upstream of the fan. Pressure sensors coupled to the nacelle are communicatively coupled to at least one actuator. The at least one actuator can adjust airflow between the first opening and the second opening, or between the first opening and the third opening. The pressure sensors can provide outputs for generating commands that control the at least one actuator.

Abstract: Composite components and methods for forming composite components are provided. For example, a composite component of a gas turbine engine comprises a composite material, a plurality of piezoelectric fibers, and an anti-icing mechanism. The anti-icing mechanism is in operative communication with the piezoelectric fibers such that the anti-icing mechanism is activated by one or more electrical signals from the piezoelectric fibers. In exemplary embodiments, the composite component is a composite airfoil and the anti-icing mechanism is one or more heating elements. Methods for forming composite components may comprise forming piezoelectric plies comprising piezoelectric fibers embedded in a matrix material; forming reinforcing plies comprising reinforcing fibers embedded in the matrix material; laying up the piezoelectric and reinforcing plies to form a ply layup; and processing the ply layup to form the composite component.

Abstract: Composite components and methods for forming composite components are provided. For example, a composite component of a gas turbine engine comprises a composite material, a plurality of piezoelectric fibers, and an anti-icing mechanism. The anti-icing mechanism is in operative communication with the piezoelectric fibers such that the anti-icing mechanism is activated by one or more electrical signals from the piezoelectric fibers. In exemplary embodiments, the composite component is a composite airfoil and the anti-icing mechanism is one or more heating elements. Methods for forming composite components may comprise forming piezoelectric plies comprising piezoelectric fibers embedded in a matrix material; forming reinforcing plies comprising reinforcing fibers embedded in the matrix material; laying up the piezoelectric and reinforcing plies to form a ply layup; and processing the ply layup to form the composite component.

Abstract: A system for measuring a gap between a moving and stationary component of a turbine engine. The system comprises a turbine engine having a core with compressor, combustor, and turbine sections in axial flow arrangement, with at least one rotating blade mounted to a shaft in the compressor and turbine sections and a stationary casing surrounding the at least one blade. At least one surface acoustic wave sensor mounted on one of the at least one blades or casing and generating an electromagnetic signal. An antenna in communication with the surface acoustic wave sensor for receiving the electromagnetic signal; and a computer system configured to receive the electromagnetic signal from the antenna and to convert the electromagnetic signal to a clearance value.

Abstract: A system for measuring a gap between a moving and stationary component of a turbine engine. The system comprises a turbine engine having a core with compressor, combustor, and turbine sections in axial flow arrangement, with at least one rotating blade mounted to a shaft in the compressor and turbine sections and a stationary casing surrounding the at least one blade. At least one surface acoustic wave sensor mounted on one of the at least one blades or casing and generating an electromagnetic signal. An antenna in communication with the surface acoustic wave sensor for receiving the electromagnetic signal; and a computer system configured to receive the electromagnetic signal from the antenna and to convert the electromagnetic signal to a clearance value.