Abstract: A propulsion system for an aircraft includes a hydrogen fuel system, a water recovery system and a water pressure and quantity monitoring system. The water recovery system uses a condenser to extract water from an exhaust gas flow. The water pressure and quantity monitoring system measures water pressures and quantities at various locations in the water recovery system to assess the health and efficiency of the water recovery/supply system and the propulsion system.

Abstract: An in-situ system for a gas turbine engine blade inspection including a sensor system configured to capture images of a forward surface of at least one gas turbine engine blade; a processor coupled to the sensor system, the processor configured to determine damage to the at least one gas turbine engine blade based on video analytics; and a tangible, non-transitory memory configured to communicate with the processor, the tangible, non-transitory memory having instructions stored therein that, in response to execution by the processor, cause the processor to perform operations comprising receiving, by the processor, data for the forward surface of at least one gas turbine engine blade from the sensor system; determining, by the processor, a rotational speed of a fan; and determining, by the processor, a fan synchronization.

Abstract: An in-situ system for a gas turbine engine blade inspection including a sensor system configured to capture images of a forward surface of at least one gas turbine engine blade; a processor coupled to the sensor system, the processor configured to determine damage to the at least one gas turbine engine blade based on image analytics; and a tangible, non-transitory memory configured to communicate with the processor, the tangible, non-transitory memory having instructions stored therein that, in response to execution by the processor, cause the processor to perform operations comprising receiving, by the processor, data for the forward surface of at least one gas turbine engine blade from the sensor system; and determining, by the processor, surface damage responsive to the light source.

Abstract: An assembly for an aircraft propulsion system includes a propulsor section, an imaging device, a plurality of light sources, and a controller. The propulsor section includes a propulsor. The propulsor includes a plurality of propulsor blades. The imaging device is disposed in the propulsor section. The imaging device includes a camera. The plurality of light sources are disposed in the propulsor section. The controller includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to: control the plurality of light sources to direct light to the plurality of propulsor blades, control the camera to capture image data of each propulsor blade of the plurality of propulsor blades, and identify a presence or an absence of damage for each propulsor blade of the plurality of propulsor blades using the image data.

Abstract: An assembly for an aircraft propulsion system includes a propulsor section for the aircraft propulsion system, a plurality of imaging devices, and a controller. The propulsor section includes a propulsor. The propulsor includes a plurality of propulsor blades. The plurality of imaging devices are mounted in the propulsor section. Each imaging device includes a camera. The controller includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to: control the camera of each imaging device of the plurality of imaging devices to capture image data of each propulsor blade of the plurality of propulsor blades and identify a presence or an absence of damage for each propulsor blade of the plurality of propulsor blades using the image data from the camera of two or more imaging devices of the plurality of imaging devices.

Abstract: An engine model calibration system includes a gas turbine engine, a sensor, a nominal engine estimation module for FD&I, and a self-tuning engine estimation module for engine parameter estimation. The nominal engine estimation module includes an open-loop nominal engine model configured to output estimated nominal engine parameters indicative of the one or more engine operating parameters, and selectively updates the open-loop nominal engine model based on one or more identified engine operating conditions. The engine model calibration system can perform calibration of a nominal engine model and a self-tuning engine model as they are used for FD&I and engine parameter estimation. The self-calibrating dynamic model also can separate the long-term tuning parameters and the short-term tuning parameters from one another so that the self-tuning capability for the self-tuning engine model is not compromised or diminished as the engine deteriorates.

Abstract: A propulsion system for an aircraft includes a hydrogen fuel system, a water recovery system and a water pressure and quantity monitoring system. The water recovery system uses a condenser to extract water from an exhaust gas flow. The water pressure and quantity monitoring system measures water pressures and quantities at various locations in the water recovery system to assess the health and efficiency of the water recovery/supply system and the propulsion system.

Abstract: A propulsion system for an aircraft is disclosed and includes a water recovery system and a water monitoring system. The water recover system includes a condenser that is arranged along the core flow path and is configured to extract water from an exhaust gas flow. The water monitoring system includes a sensor and a controller programed to determine a condition of water and generate a prompt based on information communicated from the at least one sensor.

Abstract: A propulsion system for an aircraft includes a hydrogen fuel system, a water recovery system and a water pressure and quantity monitoring system. The water recovery system uses a condenser to extract water from an exhaust gas flow. The water pressure and quantity monitoring system measures water pressures and quantities at various locations in the water recovery system to assess the health and efficiency of the water recovery/supply system and the propulsion system.

Abstract: A propulsion system for an aircraft is disclosed and includes a water recovery system and a water monitoring system. The water recover system includes a condenser that is arranged along the core flow path and is configured to extract water from an exhaust gas flow. The water monitoring system includes a sensor and a controller programed to determine a condition of water and generate a prompt based on information communicated from the at least one sensor.

Abstract: A propulsion system for an aircraft includes a hydrogen fuel system, a water recovery system and a water pressure and quantity monitoring system. The water recovery system uses a condenser to extract water from an exhaust gas flow. The water pressure and quantity monitoring system measures water pressures and quantities at various locations in the water recovery system to assess the health and efficiency of the water recovery/supply system and the propulsion system.

Abstract: A method to effectively utilize an oil debris monitor to provide advanced warning to mechanical system failures in a high noise system by adapting detection and annunciation algorithms to the background noise in a system that includes collecting I and Q channel data from a sensor; processing the I and Q channel data to both calculate a noise based (RMS adjusted) detection threshold and to identify a ferrous and nonferrous signal; processing the ferrous and nonferrous signals to determine signal peaks above the RMS adjusted detection threshold; adjusting a detection threshold if more signal peaks observed than allowable particles in a given time window; transmitting the detection threshold previously determined to particle detection, rate limit adjustment, detectability algorithms, and estimated mass loss accumulation.

Abstract: An engine parameter estimation tuning system includes an engine parameter estimator unit and a gas path analysis (GPA) unit. The engine parameter estimator unit includes an onboard model (OBM) configured to output estimated parameters based on operation of a gas turbine engine. The gas path analysis (GPA) unit includes a performance health monitor unit configured to adjust a long-term deterioration parameter independently from adjustment of a short-term tuning parameter to tune one or more targeted estimation parameters included in the estimated engine parameter. In this manner, the engine parameter estimation tuning system can realize the different time scales associated with uncertainties in an engine and accommodate them separately so that the estimated engine parameters become much more accurate.

Abstract: A method for fault identification for a gas turbine engine includes receiving sensor data from at least one health monitoring sensor of a health monitoring system for a gas turbine engine; utilizing a pre-filter to filter the sensor data and obtain filtered data based on a plurality of signatures of fault conditions of the health monitoring system and the gas turbine engine; utilizing at least one transfer function to extract features from the filtered sensor data based on the plurality of signatures; utilizing a machine learning technique to analyze the extracted features, and determine whether any of the extracted features are indicative of a fault condition in the health monitoring system or the gas turbine engine; and based on the analysis indicating the presence of a fault condition, providing a fault detection notification. A health monitoring system for a gas turbine engine is also disclosed.

Abstract: A method to effectively utilize an oil debris monitor to provide advanced warning to mechanical system failures in a high noise system by adapting detection and annunciation algorithms to the background noise in a system that includes collecting I and Q channel data from a sensor; processing the I and Q channel data to both calculate a noise based (RMS adjusted) detection threshold and to identify a ferrous and nonferrous signal; processing the ferrous and nonferrous signals to determine signal peaks above the RMS adjusted detection threshold; adjusting a detection threshold if more signal peaks observed than allowable particles in a given time window; transmitting the detection threshold previously determined to particle detection, rate limit adjustment, detectability algorithms, and estimated mass loss accumulation.

Abstract: A method to effectively utilize an oil debris monitor to provide advanced warning to mechanical system failures in a high noise system by adapting detection and annunciation algorithms to the background noise in a system that includes collecting I and Q channel data from a sensor; processing the I and Q channel data to both calculate a noise based (RMS adjusted) detection threshold and to identify a ferrous and nonferrous signal; processing the ferrous and nonferrous signals to determine signal peaks above the RMS adjusted detection threshold; adjusting a detection threshold if more signal peaks observed than allowable particles in a given time window; transmitting the detection threshold previously determined to particle detection, rate limit adjustment, detectability algorithms, and estimated mass loss accumulation.

Abstract: A method for fault diagnosis of a bearing includes detecting, using an oil debris monitor (ODM) sensor, ODM data corresponding to an amount of debris flowing downstream from the bearing. The method also includes detecting, using a vibration sensor, vibration data corresponding to vibration of the bearing during use. The method also includes determining, by a controller, a vibration stage flag corresponding to a severity of damage of the bearing based on the vibration data. The method also includes determining, by the controller, a severity level of the damage of the bearing based on a combination of the vibration stage flag and the ODM data. The method also includes outputting, by an output device, the severity level.

Abstract: A method to effectively utilize an oil debris monitor to provide advanced warning to mechanical system failures in a high noise system by adapting detection and annunciation algorithms to the background noise in a system that includes collecting I and Q channel data from a sensor; processing the I and Q channel data to both calculate a noise based (RMS adjusted) detection threshold and to identify a ferrous and nonferrous signal; processing the ferrous and nonferrous signals to determine signal peaks above the RMS adjusted detection threshold; adjusting a detection threshold if more signal peaks observed than allowable particles in a given time window; transmitting the detection threshold previously determined to particle detection, rate limit adjustment, detectability algorithms, and estimated mass loss accumulation.

Abstract: A method for fault diagnosis of a bearing includes detecting, using an oil debris monitor (ODM) sensor, ODM data corresponding to an amount of debris flowing downstream from the bearing. The method also includes detecting, using a vibration sensor, vibration data corresponding to vibration of the bearing during use. The method also includes determining, by a controller, a vibration stage flag corresponding to a severity of damage of the bearing based on the vibration data. The method also includes determining, by the controller, a severity level of the damage of the bearing based on a combination of the vibration stage flag and the ODM data. The method also includes outputting, by an output device, the severity level.