Fuel control valve for an aircraft gas turbine engine fuel system

摘要

A fuel control valve arrangement is provided, which when connected to a number of fuel flow paths (GHJKNM) in the fuel system of a turbofan aeroengine, is capable of interconnecting them in several different fuel flow configurations as necessary to vary transport of heat around the fuel system. The valve arrangement has fuel ports (705-714) as necessary to connect it to the fuel flow paths and transfer fuel between a diverter valve component (701) and a fuel spill control valve component (702), each of which has independently translatable valve elements (A/B, 716) which are positionable to selectively prevent communication between the fuel ports (705-714). The spill control valve element (716) is controllable to move progressively over a range of positions to throttle fuel flow to one of the ports 713 and the connected fuel flow path (M) which spills fuel back to a fuel supply tank.