| CPC F01D 17/145 (2013.01) [F05D 2220/323 (2013.01); F05D 2250/182 (2013.01); F05D 2260/31 (2013.01); F05D 2260/36 (2013.01); F05D 2260/606 (2013.01)] | 16 Claims |
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1. A valve for an air system in an aircraft engine, comprising:
a piston housing defining a cylindrical chamber having a valve axis;
a piston body received within the chamber, the piston body extending annularly about a piston axis collinear with the valve axis, the piston body extending axially from a first axial piston surface to a second axial piston surface axially spaced apart from the first axial piston surface, the piston body defining a piston bore extending axially from the first axial piston surface to the second axial piston surface along the piston axis, the piston body defining a recess extending axially inwardly from the second axial piston surface and extending radially to an outer recess diameter outward of the piston bore, a junction between the first axial piston surface and the piston bore located radially inward of the outer recess diameter;
a sleeve extending longitudinally from a first sleeve end to a second sleeve end along a sleeve axis collinear with the valve axis, the first sleeve end sized to be received within the recess; and
a shuttle having a stem extending longitudinally along a stem axis collinear with the valve axis, the shuttle having a flange projecting radially outwardly from the stem relative to the valve axis, the flange defining an axial flange surface at a first axial location of the stem, the stem defining an axial landmark at a second axial location of the stem, the piston body and the sleeve axially stacked onto the flange such that the first axial piston surface lays against the axial flange surface, the first sleeve end is received within the recess and the second sleeve end is located between the second axial piston surface and the axial landmark at the second axial location of the stem.
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