A gas turbine engine includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a high spool, and a low spool including a low pressure turbine that drives the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.

The subject matter of the present disclosure is directed to a turbine engine having an adaptive prognostic health management control system that passively monitors stall margin reductions and applies corrective trims to a power management schedule of the engine to recover operability over time whilst maintaining a sufficient level of stall margin over the life cycle of the engine. The control system can adjust the power management schedule as needed to sustain a target stall margin, which allows for a more optimized and gradual performance to operability trade-off.

An electric water pump having a motor with an axially moveable rotor unit. A rotary pump member is fixed for axial movement with the rotor unit to vary its position within a pump chamber so as to vary the flow rate through the pump chamber.

The present disclosure relates to a gas turbine engine including a turbine wheel mounted for rotation about a central axis and a turbine shroud ring mounted radially outward from the turbine wheel. The turbine wheel includes a plurality of blades that are spaced apart radially from the turbine shroud ring to establish a blade tip clearance gap. The gas turbine engine further includes a blade tip clearance control system that passively controls the size of the clearance gap based on engine operation.

A method for selectively modulating bleed air used for cooling a downstream turbine section in a gas turbine engine. The method including: measuring an engine and/or aircraft performance parameter by an engine sensor device; comparing the engine and/or aircraft performance parameter to a performance threshold; determining a bleed trigger condition, if the engine and/or aircraft performance parameter crosses the performance threshold; determining a non-cooling condition, if the engine and/or aircraft performance parameter is below the performance threshold; actuating a flow control valve to an open position, in response to the bleed trigger condition, so that bleed air is extracted from the compressor section and flowed to the downstream turbine section; and terminating, in response to the non-cooling condition, the flow of the bleed air to the downstream turbine section of the engine by actuating the flow control valve to a closed position.

A wear monitoring system for measuring incursion depth into an abradable coating includes a layer of abradable coating including a depth, and a measurement circuit including a plurality of conductive leads disposed within the abradable coating. The conductive leads are spaced radially apart within a common radial plane corresponding to the depth of the abradable coating. A radio frequency identification tag (RFID) is disposed within the abradable coating and connected to the measurement circuit. A plurality of resistor elements corresponds with the plurality of conductive leads. Each of the plurality of resistor elements in electrical communication with one of the plurality of conductive leads is disposed within the common radial plane of the corresponding one of the plurality of conductive leads. An electrical characteristic of the measurement circuit varies responsive to cutting of one or more of the plurality of conductive leads by a passing airfoil.

A method includes receiving a command to operate a power load of a power system at a command output power while operating the power load at a reference output power; operating a gas turbine engine of the power system in a maximum regulator mode to increase a power generation of the gas turbine engine when the command output power is greater than the reference output power or in a minimum regulator mode to decrease the power generation of the gas turbine engine when the command output power is less than the reference output power; and coordinating an electric machine power draw from the gas turbine engine with a change in power generation of the gas turbine engine to maintain a rotational speed parameter of the gas turbine engine substantially constant while operating the gas turbine engine in the maximum regulator mode or in the minimum regulator mode.

A liquid fuel leak detection system for a gas turbine enclosure including a liquid fuel module is disclosed. The system includes a tube probe array positioned adjacent a floor of the gas turbine enclosure under the liquid fuel module, the tube probe array including at least one tube having at least one opening; and a first hazardous gas sensor panel in communication with the tube probe array, the hazardous gas sensor panel detecting a first accumulation level of turbine liquid fuel vapors in the gas turbine enclosure from the liquid fuel module based on input from the tube probe array, and creating an alarm in response to the detected first accumulation level exceeding a first predetermined amount. A pipe array under a fuel delivery system for detecting fuel leaks thereunder may also be provided.

A system for monitoring fuel additives on board a vehicle includes a fuel line carrying fuel from a fuel source to an engine; a fuel additive sensor configured to measure concentration of additives in fuel at a point along the fuel line; a fuel additive dispenser connected in parallel to the fuel line; at least one flow control device for controlling an amount of flow from the fuel line into the fuel additive dispenser; and a controller configured to receive input from the fuel additive sensor and to control the flow control device to adjust the amount of the flow from the fuel line into the fuel additive dispenser.

A turbomachine of bypass type comprising a nacelle defining a fan duct with an interduct. The turbomachine comprises at least one compartment created in the thickness of the interduct or of the nacelle. The compartment is separated from the fan duct by a cold wall and comprises at least one heat-sensitive element. The compartment further is equipped with a ventilation assembly comprising at least one ventilation opening made in the cold wall in order, in use, to cause air from the fan duct to enter the compartment. Each ventilation opening comprises a passive-opening system arranged in the compartment, the system comprising a flap able to move between an open position in which the flap uncovers the opening and a closing-off position in which the flap closes off the opening, and a passive-actuation device of the flap for moving the flap between the two positions.