Patent ID: 8850827

Claim:
A gas turbine engine comprising: a compressor having an inlet and an outlet and operable to supply compressed air; a combustor coupled to receive a first portion of the compressed air from the compressor and operable to supply combusted air; a turbine coupled to receive the combusted air from the combustor and a second portion of the compressed air from the compressor; and a control valve coupled between the compressor and the combustor, the control valve comprising: a valve body forming an inlet, an outlet, and a fluid flow passage therebetween; a valve element disposed at least partially within the valve body and movable between at least: a closed position, in which fluid is restricted from flowing through the fluid flow passage; and an open position, in which the fluid is allowed to flow through the fluid flow passage; an inner radial seal disposed against the valve body at a first distance from a centerline of the control valve, the first distance comprising a shortest distance between the inner radial seal and the centerline; and an outer radial seal disposed against the valve body at a second distance from the centerline, the second distance comprising a shortest distance between the outer radial seal and the centerline, the second distance being greater than the first distance, wherein the difference between the second distance and the first distance is less than the first distance; wherein the inner radial seal and the outer radial seal are axially aligned with one another along the centerline of the control valve.