A GAS TURBINE ENGINE COMPONENT

摘要

The invention involves a gas turbine engine component comprising an annular outer casing (101) and a hub (102) located radially inwards in relation to the outer casing (101), a gas flow passage (105) being located between the outer casing (101) and the hub (102), a plurality of circumferentially distributed struts (103) extending between the outer casing (101) and the hub (102), at least one of the struts (103) presenting an inner cooling passage (106) for a cooling air flow. The component comprises cooling air control means (114) adapted to adjust the cooling air flow in the inner cooling passage (106).