An aircraft turbomachine includes a lubricating circuit notably including a reservoir of lubricating fluid, a pump drawing lubricating fluid from the reservoir to inject it toward several components of the turbomachine, and an intake pipe connecting the reservoir to an intake orifice of the pump, the turbomachine further including a pneumatic starting circuit including a starting tube through which there circulates a flow of compressed air intended to supply a pneumatic starter of the turbomachine, wherein it includes a pneumatic line extending from the starting tube as far as the reservoir so as to supply the reservoir with compressed air so as to cause the lubricating fluid to circulate through the intake pipe towards the pump.

An air turbine start system includes an air supply duct, an air turbine starter, a starter air valve, a stepper motor, and a controller. The air turbine starter is coupled to the air supply duct to selectively receive a flow of pressurized air therefrom. The starter air valve is mounted on the air supply duct and is movable between a closed position and a plurality of open positions. The stepper motor is coupled to the starter air valve and is configured, in response to valve position commands, to move the starter air valve between the closed position and one or more of the plurality of open positions. The controller is coupled to the stepper motor and is configured to supply the valve position commands to the stepper motor and determine a position of the starter air valve based on the valve position commands supplied to the stepper motor.

An air turbine start system includes an air supply duct, an air turbine starter, a starter air valve, a stepper motor, and a controller. The air turbine starter is coupled to the air supply duct to selectively receive a flow of pressurized air therefrom. The starter air valve is mounted on the air supply duct and is movable between a closed position and a plurality of open positions. The stepper motor is coupled to the starter air valve and is configured, in response to valve position commands, to move the starter air valve between the closed position and one or more of the plurality of open positions. The controller is coupled to the stepper motor and is configured to supply the valve position commands to the stepper motor and determine a position of the starter air valve based on the valve position commands supplied to the stepper motor.

An engine system for an aircraft includes a first gas turbine engine, a first core turning system, a second gas turbine engine, and a second core turning system. The engine system also includes a controller operable to shutdown the first gas turbine engine responsive to determining that the aircraft has landed and operate in the second gas turbine engine in a taxi mode while using the first core turning system to cool the first gas turbine engine. The controller is further operable to shutdown the second gas turbine engine and disable the first core turning system based on a power-down condition, restart the first gas turbine engine and use the second core turning system to cool the second gas turbine engine based on a restart condition, and complete cooling of the second gas turbine prior to restarting the second gas turbine engine.

An engine system for an aircraft includes a first gas turbine engine, a first core turning system, a second gas turbine engine, and a second core turning system. The engine system also includes a controller operable to shutdown the first gas turbine engine responsive to determining that the aircraft has landed and operate in the second gas turbine engine in a taxi mode while using the first core turning system to cool the first gas turbine engine. The controller is further operable to shutdown the second gas turbine engine and disable the first core turning system based on a power-down condition, restart the first gas turbine engine and use the second core turning system to cool the second gas turbine engine based on a restart condition, and complete cooling of the second gas turbine prior to restarting the second gas turbine engine.

A starter assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fluid-actuated starter coupled to a spool, and a controller operable to cause a reduction in torque output of the starter in response to determining that a first threshold is met. The first threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.

A starter assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fluid-actuated starter coupled to a spool, and a controller operable to cause a reduction in torque output of the starter in response to determining that a first threshold is met. The first threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.

A gas turbine engine includes a bypass duct, a compressor, and a pyrotechnic gas conduit. The bypass duct conducts bypass air between an outer bypass wall and an inner bypass wall. The compressor includes an impeller to compress engine air. The pyrotechnic gas conduit is configured to conduct a gas onto the impeller to start the gas turbine engine.

A gas turbine engine includes a bypass duct, a compressor, and a pyrotechnic gas conduit. The bypass duct conducts bypass air between an outer bypass wall and an inner bypass wall. The compressor includes an impeller to compress engine air. The pyrotechnic gas conduit is configured to conduct a gas onto the impeller to start the gas turbine engine.

A gas turbine engine includes at least one shaft that interconnects a compressor section and a turbine section. A starter turbine provides torque to the at least one shaft during an engine start event. The starter turbine includes an air inlet and an outlet. A buffer air system is in fluid communication with the starter turbine and is configured to receive air associated with the outlet to supplement sealing of a bearing compartment sealing system.