A method and system for managing power to an engine controller operatively coupled to an engine of an aircraft are described. The method comprises powering the engine controller from an aircraft battery, starting a timer in response to a predetermined trigger to maintain the engine controller powered by the aircraft battery for a predetermined time, and removing power from the aircraft battery to the engine controller when the timer expires.

A method and system for managing power to an engine controller operatively coupled to an engine of an aircraft are described. The method comprises powering the engine controller from an aircraft battery, starting a timer in response to a predetermined trigger to maintain the engine controller powered by the aircraft battery for a predetermined time, and removing power from the aircraft battery to the engine controller when the timer expires.

A turbine overspeed trip test data system is a portable system by which an operator can electronically gather and log data during a turbine overspeed test. A plurality of sensors can be affixed to various components of the turbine for gathering test data to be received by a processing unit to assess the operation of the turbine overspeed trip protection components. The test data may be compiled into a turbine test log. A method for processing the gathered sensor data is also provided.

A turbine overspeed trip test data system is a portable system by which an operator can electronically gather and log data during a turbine overspeed test. A plurality of sensors can be affixed to various components of the turbine for gathering test data to be received by a processing unit to assess the operation of the turbine overspeed trip protection components. The test data may be compiled into a turbine test log. A method for processing the gathered sensor data is also provided.

A turbine overspeed trip test data system is a portable system by which an operator can electronically gather and log data during a turbine overspeed test. A plurality of sensors can be affixed to various components of the turbine for gathering test data to be received by a processing unit to assess the operation of the turbine overspeed trip protection components. The test data may be compiled into a turbine test log. A method for processing the gathered sensor data is also provided.

The present application provides a method of evaluating valve spindle vibration in a turbine by a data acquisition system. The method may include the steps of receiving a number of operating parameters from a number of sensors, wherein the operating parameters may include valve spindle vibration, comparing the valve spindle vibration to a predetermined value, and altering one or more of the operating parameters if the valve spindle vibration exceeds the predetermined value.

The present application provides a method of evaluating valve spindle vibration in a turbine by a data acquisition system. The method may include the steps of receiving a number of operating parameters from a number of sensors, wherein the operating parameters may include valve spindle vibration, comparing the valve spindle vibration to a predetermined value, and altering one or more of the operating parameters if the valve spindle vibration exceeds the predetermined value.

A bowed rotor prevention system for a gas turbine engine includes a core turning motor operable to drive rotation of an engine core of the gas turbine engine. The bowed rotor prevention system also includes an auxiliary electric motor control operable to control the core turning motor to drive rotation of the engine core using electric power while a full authority digital engine control that controls operation of the gas turbine engine is either depowered or in a power state that is less than a power level used by the full authority digital engine control in flight operation.

A bowed rotor prevention system for a gas turbine engine includes a core turning motor operable to drive rotation of an engine core of the gas turbine engine. The bowed rotor prevention system also includes an auxiliary electric motor control operable to control the core turning motor to drive rotation of the engine core using electric power while a full authority digital engine control that controls operation of the gas turbine engine is either depowered or in a power state that is less than a power level used by the full authority digital engine control in flight operation.

The emergency shutoff device is provided with a casing (21) in which inflow ports (22) through which control oil flows into a space (A1) provided therein and a plurality of outflow ports (23) through which the control oil flows outside of the space (A1) are formed; and a switching unit (24) configured to slide along an inner circumferential surface of the casing (21) in which the space (A1) is formed, to change its position relative to the plurality of outflow ports (23), and thus to switch a circulation state of the control oil in the space (A1). The switching unit (24) switches the circulation state between the first circulation state in which the control oil is circulated from a first inflow port (221) to a first outflow port (231) and the third circulation state in which an open and closed state of a test outflow port (236) is switched while the control oil is being circulated from the first inflow port (221) to the first outflow port (231).