Abstract: An actuation assembly includes a control valve, a first actuator and a second actuator fluidly connected to the control valve via plumbing. The first actuator has a first extend port and the second actuator having a second extend port. A flow control device fluidly connected to the first actuator and the second actuator is operable to balance a flow rate of a fluid at the first actuator with the flow rate of the fluid at the second actuator. The flow control device is arranged within the plumbing, at a position between the control valve and the first extend port and the second extend port.

Abstract: An actuation assembly includes a control valve, a first actuator and a second actuator fluidly connected to the control valve via plumbing. The first actuator has a first extend port and the second actuator having a second extend port. A flow control device fluidly connected to the first actuator and the second actuator is operable to balance a flow rate of a fluid at the first actuator with the flow rate of the fluid at the second actuator. The flow control device is arranged within the plumbing, at a position between the control valve and the first extend port and the second extend port.

Abstract: A system includes a main pump having a main pump shaft configured to connect to a gear box for driving the main pump with rotational power from the gear box in a run mode, and for driving the gear box with rotational power from the main pump in a start mode. The system includes a first fuel line with an inlet configured to connect to connected in fluid communication with a fuel source. The first fuel line includes a first branch in fluid communication with the main pump, and a second branch. A start pump is connected in fluid communication with the second branch of the first fuel line. A second fuel line connects the start pump in fluid communication with a pump management valve (PMV). A third fuel line connects the main pump in fluid communication with the pump management valve.

Abstract: A system includes a burn flow line and a flow divider valve in fluid communication with the burn flow line to split flow from the burn flow line to a primary line and to a secondary line for supplying fuel to a set of primary engine nozzles and to a set of secondary engine nozzles, respectively. A sensor operatively connected to the flow divider valve to produce a feedback signal indicative of flow split between the primary line and the secondary line. A controller is operatively connected to receive the feedback signal from the senor, compare the feedback signal to a stored flow split value for a mismatch, and output an alert message upon detecting the mismatch.

Abstract: A system includes a main pump having a main pump shaft configured to connect to a gear box for driving the main pump with rotational power from the gear box in a run mode, and for driving the gear box with rotational power from the main pump in a start mode. The system includes a first fuel line with an inlet configured to connect to connected in fluid communication with a fuel source. The first fuel line includes a first branch in fluid communication with the main pump, and a second branch. A start pump is connected in fluid communication with the second branch of the first fuel line. A second fuel line connects the start pump in fluid communication with a pump management valve (PMV). A third fuel line connects the main pump in fluid communication with the pump management valve.

Abstract: In accordance with at least one aspect of this disclosure, a system includes a fuel line, an electrically driven fuel pump configured to supply fuel to a first fuel line branch and a second fuel line branch, and a selector valve disposed in the fuel line at a juncture of a first fuel line branch and a second fuel line branch configured to communicate the electrically driven fuel pump with the first fuel line branch or the second fuel line branch based on a position of the selector valve. In a first position, the selector valve is configured to fluidly connect the electrically driven fuel pump with the first fuel line branch to supply fuel to a combustor of the engine and drive a high pressure shaft at a first speed. In a second position, the selector valve is configured to fluidly connect the electrically driven fuel pump with the second fuel line branch to drive a hydraulic rotation unit configured to drive the high pressure spool of the engine at a second speed different from the first speed.

Abstract: In accordance with at least one aspect of this disclosure, a system includes a fuel line, an electrically driven fuel pump configured to supply fuel to a first fuel line branch and a second fuel line branch, and a selector valve disposed in the fuel line at a juncture of a first fuel line branch and a second fuel line branch configured to communicate the electrically driven fuel pump with the first fuel line branch or the second fuel line branch based on a position of the selector valve. In a first position, the selector valve is configured to fluidly connect the electrically driven fuel pump with the first fuel line branch to supply fuel to a combustor of the engine and drive a high pressure shaft at a first speed. In a second position, the selector valve is configured to fluidly connect the electrically driven fuel pump with the second fuel line branch to drive a hydraulic rotation unit configured to drive the high pressure spool of the engine at a second speed different from the first speed.

Abstract: A two stage fuel delivery system for an aircraft includes a first stage pump including an inlet connected to a source of fuel and an outlet connected to a combustor assembly, and a second stage pump including an inlet portion connected to the source of fuel and an outlet portion connected to the combustor assembly. A bypass valve is connected between the source of fuel, the inlet, and the inlet portion. The bypass valve selectively disconnects the second stage pump from the source of fuel. A metering valve is connected to the inlet and the inlet portion. The metering valve includes a metering valve inlet and a metering valve outlet. A pressure regulating valve is connected to the metering valve. A stage monitoring system is configured to detect a change in operation of the second stage and control the bypass valve.

Abstract: A two stage fuel delivery system for an aircraft includes a first stage pump including an inlet connected to a source of fuel and an outlet connected to a combustor assembly, and a second stage pump including an inlet portion connected to the source of fuel and an outlet portion connected to the combustor assembly. A bypass valve is connected between the source of fuel, the inlet, and the inlet portion. The bypass valve selectively disconnects the second stage pump from the source of fuel. A metering valve is connected to the inlet and the inlet portion. The metering valve includes a metering valve inlet and a metering valve outlet. A pressure regulating valve is connected to the metering valve. A stage monitoring system is configured to detect a change in operation of the second stage and control the bypass valve.