Abstract: A system for controlling lubricant flow to a component in a gas turbine engine includes a control valve, an electromechanical actuator, and an engine controller. The control valve includes a lubricant inlet that is in fluid communication with a pressurized lubricant source, a lubricant outlet is in fluid communication with the gas turbine engine component, and a valve element that is movable to a plurality of valve positions. The electromechanical valve actuator is coupled to the valve element and is responsive to actuator commands to position the valve element. The engine controller is coupled to receive a pressure sensor signal indicative of a compressor pressure in the gas turbine engine and, in response, determines a commanded valve element position and supplies the actuator commands to the electromechanical valve actuator that cause the electromechanical valve actuator to move the valve element to the commanded valve element position.

Abstract: A compressor of a gas turbine engine includes an impeller having a plurality of impeller blades. The compressor includes a diffuser downstream from the impeller that has a plurality of diffuser blades. Each diffuser blade extends from a hub to a shroud in a spanwise direction, and a leading edge of each diffuser blade is spaced apart from an impeller trailing edge of each of the plurality of impeller blades by a vaneless gap. Each diffuser blade includes a cutback region that extends from proximate the leading edge toward a trailing edge. The cutback region reduces a thickness of each of the diffuser blades such that a throat area defined between adjacent diffuser blades increases in the spanwise direction from the hub to the shroud and the vaneless gap increases in the spanwise direction from the hub to the shroud.

Abstract: A compressor of a gas turbine engine includes an impeller having a plurality of impeller blades. The compressor includes a diffuser downstream from the impeller that has a plurality of diffuser blades. Each diffuser blade extends from a hub to a shroud in a spanwise direction, and a leading edge of each diffuser blade is spaced apart from an impeller trailing edge of each of the plurality of impeller blades by a vaneless gap. Each diffuser blade includes a cutback region that extends from proximate the leading edge toward a trailing edge. The cutback region reduces a thickness of each of the diffuser blades such that a throat area defined between adjacent diffuser blades increases in the spanwise direction from the hub to the shroud and the vaneless gap increases in the spanwise direction from the hub to the shroud.