A bleed system including control circuitry and a variable jet pump. The control circuitry is configured to receive a signal indicative of a fluid parameter in the bleed system and cause the jet pump to alter a mixing ratio of a higher pressure gas and a lower pressure gas based on the signal. The jet pump is configured to combine the lower pressure gas and the higher pressure gas in the mixing ratio to generate a mixed gas. The jet pump is configured to supply the mixed gas to one or more gas loads in the bleed system. In examples, the control circuitry is configured to establish a system setpoint for the fluid parameter based on an operating status of the one or more gas loads.

A bleed system including control circuitry and a variable jet pump. The control circuitry is configured to receive a signal indicative of a fluid parameter in the bleed system and cause the jet pump to alter a mixing ratio of a higher pressure gas and a lower pressure gas based on the signal. The jet pump is configured to combine the lower pressure gas and the higher pressure gas in the mixing ratio to generate a mixed gas. The jet pump is configured to supply the mixed gas to one or more gas loads in the bleed system. In examples, the control circuitry is configured to establish a system setpoint for the fluid parameter based on an operating status of the one or more gas loads.

A gas turbine engine includes a main compressor section with a downstream most location. A turbine section has a high pressure turbine. A tap line is connected to tap air from a location upstream of the downstream most location in the main compressor section. The tapped air is connected to a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and is connected to deliver air into the high pressure turbine. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions.

A gas turbine engine includes a main compressor section with a downstream most location. A turbine section has a high pressure turbine. A tap line is connected to tap air from a location upstream of the downstream most location in the main compressor section. The tapped air is connected to a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and is connected to deliver air into the high pressure turbine. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions.

A method and device for detecting conditions conducive to the onset of pumping that can affect a low-pressure compressor of an aircraft turbine engine. The turbine engine including a high-pressure compressor. The method including measuring a speed variation of the aircraft and measuring a speed variation of the high-pressure compressor. The method including a preliminary step of measuring an altitude of the aircraft. The conditions conducive to the onset of pumping being detected when the following conditions are jointly obtained: (a) the speed variation measured over a predetermined time interval corresponds to an acceleration greater than a first positive threshold, (b) the measured speed variation corresponds to a deceleration less than a second negative threshold, and (c) the altitude is greater than a third predetermined threshold.

A method and device for detecting conditions conducive to the onset of pumping that can affect a low-pressure compressor of an aircraft turbine engine. The turbine engine including a high-pressure compressor. The method including measuring a speed variation of the aircraft and measuring a speed variation of the high-pressure compressor. The method including a preliminary step of measuring an altitude of the aircraft. The conditions conducive to the onset of pumping being detected when the following conditions are jointly obtained: (a) the speed variation measured over a predetermined time interval corresponds to an acceleration greater than a first positive threshold, (b) the measured speed variation corresponds to a deceleration less than a second negative threshold, and (c) the altitude is greater than a third predetermined threshold.

Methods for controlling actuating components of turbine engines using an adaptive damping lag filter are provided. The adaptive filter includes features that filter out insignificant changes in actuator demand, respond to fast transient conditions to follow demanded position of the actuating component more closely, and adapts the gain of the output position to avoid stall conditions.

Methods for controlling actuating components of turbine engines using an adaptive damping lag filter are provided. The adaptive filter includes features that filter out insignificant changes in actuator demand, respond to fast transient conditions to follow demanded position of the actuating component more closely, and adapts the gain of the output position to avoid stall conditions.

A system for modulating airflow into a bore defined by a rotor of a gas turbine engine defining an axial direction, a circumferential direction, and a radial direction is provided. The system includes a movable member positioned forward of a first stage of rotor blades of the rotor. The movable member is movable between at least a first position and a second position to modulate airflow into the bore via a plurality of opening in fluid communication with the bore.

The method can include sensing operating conditions of the gas turbine engine; generating a base value signal of a control parameter of the bleed valve based on the sensed operating conditions and on control data; determining whether a contaminant management condition is met; generating a control value signal of the control parameter including the base value signal and, when the contaminant management conditions is met, the control value signal further including a contaminant management signal of the control parameter value of the valve superposed to the base value signal, the contaminant management signal including at least three successive back and forth fluctuations of the control parameter value relative the base value signal over a period of 10 seconds or less; and controlling an actuator of the bleed valve based on the control value signal.