Systems and methods for monitoring a pressure transducer are described. The method comprises sampling an output signal of a pressure transducer to obtain a plurality of pressure measurements as recorded by the pressure transducer, comparing the pressure measurements to a first pressure exposure limit associated with the pressure transducer, and recording data related to exposure of the pressure transducer to the first pressure exposure limit.

Methods and systems for detecting a shaft event of a gas turbine engine are described. The method comprises monitoring at least one engine parameter and comparing the at least one engine parameter to a schedule for the at least one parameter defining a first threshold and a second threshold greater than the first threshold; applying a limit to the at least one engine parameter when the at least one engine parameter is inside a parameter limiting region between the first threshold and the second threshold, the first threshold separating the parameter limiting region from a normal operating region, the second threshold separating the parameter limiting region from a hazardous operating region; and detecting the shaft event when the at least one engine parameter crosses the second threshold and issuing a signal in response to the detecting.

Methods and systems for detecting a shaft event of a gas turbine engine are described. The method comprises monitoring at least one engine parameter and comparing the at least one engine parameter to a schedule for the at least one parameter defining a first threshold and a second threshold greater than the first threshold; applying a limit to the at least one engine parameter when the at least one engine parameter is inside a parameter limiting region between the first threshold and the second threshold, the first threshold separating the parameter limiting region from a normal operating region, the second threshold separating the parameter limiting region from a hazardous operating region; and detecting the shaft event when the at least one engine parameter crosses the second threshold and issuing a signal in response to the detecting.

A gas turbine engine can have a magnetic chip detector system with a first conductor member and a second conductor member both exposed to a lubricant flow path of the gas turbine engine, at least a first one of the conductor members including an electromagnet including a coil wrapped around a ferromagnetic core. As part of an engine shutdown procedure, an intrinsic magnetic field strength within the ferromagnetic core can be increased by circulating electrical current in the coil, and the electrical current circulation can then be interrupted for the magnetic field to remain active during engine shutdown.

A gas turbine engine can have a magnetic chip detector system with a first conductor member and a second conductor member both exposed to a lubricant flow path of the gas turbine engine, at least a first one of the conductor members including an electromagnet including a coil wrapped around a ferromagnetic core. As part of an engine shutdown procedure, an intrinsic magnetic field strength within the ferromagnetic core can be increased by circulating electrical current in the coil, and the electrical current circulation can then be interrupted for the magnetic field to remain active during engine shutdown.

A depolluted test bench (I) for a turbomachine includes a channeled air duct with an air inlet and an air outlet to allow a flow of air between the air inlet and the air outlet. The channeled air duct includes a test chamber) for testing a turbomachine, the test chamber being located between the air inlet and the air outlet. A depolluting system is positioned in the air duct to depollute an air flow generated at least in part by a test of said turbomachine in the test bench. Control means control the depolluting system to allow the depolluting system to be switched on or off when a test of the turbomachine is started or stopped.

A depolluted test bench (I) for a turbomachine includes a channeled air duct with an air inlet and an air outlet to allow a flow of air between the air inlet and the air outlet. The channeled air duct includes a test chamber) for testing a turbomachine, the test chamber being located between the air inlet and the air outlet. A depolluting system is positioned in the air duct to depollute an air flow generated at least in part by a test of said turbomachine in the test bench. Control means control the depolluting system to allow the depolluting system to be switched on or off when a test of the turbomachine is started or stopped.

Predictive models for diagnosing the unbalance state in an aircraft engine such as a jet engine based on engine vibrations and other known and/or determinable parameters are disclosed. Also disclosed are methods for developing the predictive model and using the model to identify aircraft engine unbalance.

Predictive models for diagnosing the unbalance state in an aircraft engine such as a jet engine based on engine vibrations and other known and/or determinable parameters are disclosed. Also disclosed are methods for developing the predictive model and using the model to identify aircraft engine unbalance.

The present application provides a hazardous gas detection system to determine hazardous gas concentrations and/or temperatures within a flow of exhaust air in an exhaust duct of a gas turbine compartment. The hazardous gas detection system may include one or more sensors positioned within or in communication with the exhaust duct and a static mixer positioned upstream of the one or more sensors to promote mixing of the flow of exhaust air.