A gas turbine engine is provided with a controller configured to detect a spool shaft failure and to initiate an engine shut-down in response to the shaft failure. The controller evaluates the compressor speed probe, the speed probe continuity, P30 pressure and compressor surge to determine whether a shaft failure has occurred.

There is described herein methods and systems for detecting a shaft event, such as a shaft shear, a shaft decoupling, and/or a shaft failure in a gas turbine engine. The method comprises determining a detection threshold as a set of threshold values for a spool speed of a first spool of the engine and a load transfer through a shaft of a second spool of the engine different from the first spool, the set of threshold values varying throughout a flight envelope, the detection threshold defining, for each spool speed value, at least one load transfer value beyond which a shaft event is detected. Operation values of the spool speed and the load transfer are obtained during operation of the engine, and the operation values are compared to the detection threshold. The shaft event is detected when the operation values are below the detection threshold.

There is described herein methods and systems for detecting a shaft event, such as a shaft shear, a shaft decoupling, and/or a shaft failure in a gas turbine engine. The method comprises determining a detection threshold as a set of threshold values for a spool speed of a first spool of the engine and a load transfer through a shaft of a second spool of the engine different from the first spool, the set of threshold values varying throughout a flight envelope, the detection threshold defining, for each spool speed value, at least one load transfer value beyond which a shaft event is detected. Operation values of the spool speed and the load transfer are obtained during operation of the engine, and the operation values are compared to the detection threshold. The shaft event is detected when the operation values are below the detection threshold.

Systems and methods for detecting a shaft shear event in a turbine engine. An accelerometer coupled to the engine detects an axial acceleration indicative of a shaft shear event in the engine. A control system is configured to, in response to the detected axial acceleration, transmit a signal to initiate a shut down of a fuel system of the engine.

Systems and methods for detecting a shaft shear event in a turbine engine. An accelerometer coupled to the engine detects an axial acceleration indicative of a shaft shear event in the engine. A control system is configured to, in response to the detected axial acceleration, transmit a signal to initiate a shut down of a fuel system of the engine.

A core section and nacelle assembly of a gas turbine engine includes a compressor located at an engine central longitudinal axis, a core case enclosing the compressor, and a nacelle located radially outboard of the core case and defining a core compartment between the nacelle and the core case. One or more vent openings are located in the nacelle to circulate a cooling airflow through the core compartment, and one or more fans are positioned at the one or more vent openings to urge the cooling airflow through the one or more vent openings to cool the core compartment.

A core section and nacelle assembly of a gas turbine engine includes a compressor located at an engine central longitudinal axis, a core case enclosing the compressor, and a nacelle located radially outboard of the core case and defining a core compartment between the nacelle and the core case. One or more vent openings are located in the nacelle to circulate a cooling airflow through the core compartment, and one or more fans are positioned at the one or more vent openings to urge the cooling airflow through the one or more vent openings to cool the core compartment.

A bowed rotor prevention system includes a gas turbine engine, an electric motor, and a core turning controller in signal communication with the electric motor. The gas turbine engine includes a rotor that is rotatably coupled to a drive shaft. The electric motor rotatably is coupled to a motor shaft, which is mechanically coupled to the drive shaft so as to rotate therewith. The core turning controller is configured to invoke an anti-rotor bowing mode, and to control the electric motor to periodically rotate the rotor into a plurality of rotor positions during a given time period in response to invoking the anti-rotor bowing mode.

A bowed rotor prevention system includes a gas turbine engine, an electric motor, and a core turning controller in signal communication with the electric motor. The gas turbine engine includes a rotor that is rotatably coupled to a drive shaft. The electric motor rotatably is coupled to a motor shaft, which is mechanically coupled to the drive shaft so as to rotate therewith. The core turning controller is configured to invoke an anti-rotor bowing mode, and to control the electric motor to periodically rotate the rotor into a plurality of rotor positions during a given time period in response to invoking the anti-rotor bowing mode.

An inspection system for rotating fan rotor blades in a gas turbine engine is provided. The system includes a plurality of cameras and lids, and a cleaning system. The cameras are each controllable to capture an image of a leading edge of a fan rotor blade and produce signals representative thereof. Each camera is mounted to a static structure disposed forward of the fan rotor blade stage. The lids are attached to the static structure and is selectively movable between closed and open positions. In the closed position at least one camera is enclosed. In the open position the camera is at least partially exposed and has a field of view of the rotating fan rotor blades. The cleaning system is controllable to selectively produce a body of fluid relative to the at least one camera when the respective lid is in the open position.