A method for foreign object debris detection in a gas turbine engine may comprise receiving, by a controller, a plurality of master configuration parameters, receiving, by the controller, a plurality of individual configuration parameters in response to the plurality of master configuration parameters, receiving, by the controller, a first time-series data from a database, pre-processing, by the controller, the first time-series data to generate a second time-series data, implementing, by the controller, an anomaly detector model, the anomaly detector model configured to generate a third time-series data, and implementing, by the controller, a foreign object debris (FOD) damage model, the FOD damage model receiving the third time-series data. The pre-processing the first time-series data, the implementing the anomaly detector model, and the implementing the FOD damage model may be defined by the plurality of individual configuration parameters.

A method for foreign object debris detection in a gas turbine engine may comprise receiving, by a controller, a plurality of master configuration parameters, receiving, by the controller, a plurality of individual configuration parameters in response to the plurality of master configuration parameters, receiving, by the controller, a first time-series data from a database, pre-processing, by the controller, the first time-series data to generate a second time-series data, implementing, by the controller, an anomaly detector model, the anomaly detector model configured to generate a third time-series data, and implementing, by the controller, a foreign object debris (FOD) damage model, the FOD damage model receiving the third time-series data. The pre-processing the first time-series data, the implementing the anomaly detector model, and the implementing the FOD damage model may be defined by the plurality of individual configuration parameters.

A gas turbine engine, a method, and a system for detecting oil debris are provided. The gas turbine engine includes an oil debris monitor sensor configured to detects oil debris in an oil flow, and generate a sensor signal based on the detected oil debris, a controller configured to control the oil flow through the oil debris monitor sensor using a plurality of valves, and a signal processor configured to receive the sensor signal from the oil debris monitor and to receive a valve system configuration from the controller, the signal processor further configured to generates a health indicator based on the sensor signal and valve configuration.

A case for a gas turbine engine includes a core body. The core body defines a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A heating element is connected to the core body and is in thermal communication with the structure-supporting member.

A case for a gas turbine engine includes a core body. The core body defines a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A heating element is connected to the core body and is in thermal communication with the structure-supporting member.

A method for analyzing a droplet fraction of an oil mist sample of a gas turbine is provided. A collecting device collects the oil mist sample, wherein the collecting device is arranged within a breather pipe which is coupled to the gas turbine such that oil mist is flowing through the breather pipe. The droplet fraction is separated from a gaseous fraction of the oil mist sample by a filter device, wherein the filter device is soaked with the droplet fraction, the droplet fraction is extracted from the filter device by using a tetrachloroethylene solvent. A composition of the droplet fraction is analyzed by a spectrometer.

A method for analyzing a droplet fraction of an oil mist sample of a gas turbine is provided. A collecting device collects the oil mist sample, wherein the collecting device is arranged within a breather pipe which is coupled to the gas turbine such that oil mist is flowing through the breather pipe. The droplet fraction is separated from a gaseous fraction of the oil mist sample by a filter device, wherein the filter device is soaked with the droplet fraction, the droplet fraction is extracted from the filter device by using a tetrachloroethylene solvent. A composition of the droplet fraction is analyzed by a spectrometer.

A wash optimization system and related methods are provided that increase the efficiency and the effectiveness of engine washes. A system comprising at least one processor receives sensor data representing one or more measured parameters of a turbine engine and determines at least one performance parameter based on the sensor data. The at least one performance parameter represents one or more particulate values associated with the turbine engine. The system generates a health state for the turbine engine based on the at least one performance parameter and generates a wash identifier based on the health state of the turbine engine.

A wash optimization system and related methods are provided that increase the efficiency and the effectiveness of engine washes. A system comprising at least one processor receives sensor data representing one or more measured parameters of a turbine engine and determines at least one performance parameter based on the sensor data. The at least one performance parameter represents one or more particulate values associated with the turbine engine. The system generates a health state for the turbine engine based on the at least one performance parameter and generates a wash identifier based on the health state of the turbine engine.

A system for inspecting surfaces of rotor blades for a surface characteristic. The system may include an assembly having a movable arm and, mounted on the movable arm, a scanner. A row of rotor blades may be positioned near the assembly for inspection. The row of rotor blades may include a plurality of the rotor blades circumferentially spaced about a center axis. The row of rotor blades and the assembly may be moved relative to the other so as to index the row of rotor blades relative to the assembly.