Abstract: A method is provided for an engine. During this method, a saturation current of a gas flow is measured. The gas flow includes combustion products generated by the engine. The saturation current is monitored to determine presence of debris entrained within the gas flow.

Abstract: A method of producing an operational data for an aircraft turbine engine is provided that including: sensing an inlet airflow to an aircraft turbine engine for CMAS particulate matter, the sensing performed during one or more ground portions of a flight operational cycle of the turbine engine, the sensing producing sensor signals indicative of the presence or absence of the CMAS particulate matter; determining a presence or absence of an exposure by the turbine engine to a CMAS environment based on the sensor signals; and producing an operational data indicative of the presence or absence of said exposure by the turbine engine to said CMAS environment.

Abstract: An optical particulate detection system for an aircraft is provided. The optical particulate detection system includes an optical particulate detector and a controller. The optical particulate detector includes at least two optical sources and at least one optical sensor distributed in series with respect to a flow path of a component surface of the aircraft. The controller is configured to interface with the optical particulate detector, monitor the at least one optical sensor, and characterize one or more particles of foreign object debris based on a pulse width and two or more scattering ratios determined with respect to light emitted from the at least two optical sources.

Abstract: A method is provided for an engine. During this method, a saturation current of a gas flow is measured. The gas flow includes combustion products generated by the engine. The saturation current is monitored to determine presence of debris entrained within the gas flow.

Abstract: A method is provided for an engine. During this method, a saturation current of a gas flow is measured. The gas flow includes combustion products generated by the engine. The saturation current is monitored to determine presence of debris entrained within the gas flow.

Abstract: A method is provided for an engine. During this method, a saturation current of a gas flow is measured. The gas flow includes combustion products generated by the engine. The saturation current is monitored to determine presence of debris entrained within the gas flow.

Abstract: A foreign object debris (FOD) detection system for a gas turbine engine comprises a light detection and ranging (LiDAR) sensor assembly. The LiDAR sensor assembly is configured to scan a pre-determined volume within an inlet of the gas turbine engine. The inlet may be defined by a nacelle of the gas turbine engine. The LiDAR sensor assembly may comprise a single transceiver, a transmitter and a receiver, a plurality of transmitters and a receiver, or a plurality of receivers and a transmitter.

Abstract: An inlet debris monitoring includes processing circuitry configured to: obtain a data set of electrostatic charge data from an electrostatic sensor; utilize a dimensional reduction technique to obtain a first set of basis vectors that represent the data set in a reduced dimensional space that is reduced with respect to initial dimensions of the data set; utilize the first set of basis vectors or a second set of reference basis vectors which are based on historical electrostatic charge data for one or more reference gas turbine engines, to project the data set onto the reduced dimensional space and obtain a reduced dimensional representation of the data set; utilize machine learning to determine whether the reduced dimensional representation of the data set indicates foreign object debris in the particular gas turbine engine; and based on the determination indicating detection of foreign object debris, provide a foreign object debris notification.

Abstract: An optical particulate detection system for an aircraft is provided. The optical particulate detection system includes an optical particulate detector and a controller. The optical particulate detector includes at least two optical sources and at least one optical sensor distributed in series with respect to a flow path of a component surface of the aircraft. The controller is configured to interface with the optical particulate detector, monitor the at least one optical sensor, and characterize one or more particles of foreign object debris based on a pulse width and two or more scattering ratios determined with respect to light emitted from the at least two optical sources.

Abstract: A foreign object debris (FOD) detection system for a gas turbine engine comprises a light detection and ranging (LiDAR) sensor assembly. The LiDAR sensor assembly is configured to scan a pre-determined volume within an inlet of the gas turbine engine. The inlet may be defined by a nacelle of the gas turbine engine. The LiDAR sensor assembly may comprise a single transceiver, a transmitter and a receiver, a plurality of transmitters and a receiver, or a plurality of receivers and a transmitter.