Abstract: Provided is an electro-hydraulic control system (10) for controlling the movement of a third structure (18) of an engine using a power actuator (26) mountable to the third structure (18), a telescoping fluid porting tube (24) for porting a fluid to the power actuator (26) and a control valve (22) for controlling the flow of movement to effect the movement of the third structure (18). In this way, the third structure (18), such as a nozzle slat of an engine, may be moved via a compact and lightweight electro-hydraulic system.

Abstract: Provided is a valve assembly having a thermal valve member and a priority valve member that are shiftable to first and second positions in response to a temperature and pressure of a fluid flowing through the valve assembly. Consequently, the valve can provide for flow through a heating orifice under low temperature, high pressure conditions so that pressure drops in fluid lines coupled to the valve assembly may be prevented or reduced, allowing fluid lines with small diameters to be used in an aircraft or other fluid flow system, thereby reducing the weight of the aircraft or fluid flow system.

Abstract: Provided is an electro-hydraulic control system (10) for controlling the movement of a third structure (18) of an engine using a power actuator (26) mountable to the third structure (18), a telescoping fluid porting tube (24) for porting a fluid to the power actuator (26) and a control valve (22) for controlling the flow of movement to effect the movement of the third structure (18). In this way, the third structure (18), such as a nozzle slat of an engine, may be moved via a compact and lightweight electro-hydraulic system.

Abstract: Provided is a valve assembly having a thermal valve member and a priority valve member that are shiftable to first and second positions in response to a temperature and pressure of a fluid flowing through the valve assembly. Consequently, the valve can provide for flow through a heating orifice under low temperature, high pressure conditions so that pressure drops in fluid lines coupled to the valve assembly may be prevented or reduced, allowing fluid lines with small diameters to be used in an aircraft or other fluid flow system, thereby reducing the weight of the aircraft or fluid flow system.