Air cooling systems for gas turbine engines

Claim 1

In a gas turbine engine having a rotating component and a static wall positioned adjacent said rotating component to define a passageway, said engine having a main air flow, means for tapping pressurized air from said main air flow, means for preswirling said tapped air in the same direction as the direction of rotation of said rotating component, and means for directing the preswirled air onto said rotating component through said passageway, the improvement comprising: a plurality of passages through said static wall, said static wall comprising a perforated or foraminated sheet and having a boundary layer of the preswirled tapped air adjacent thereto; and supplemental air supply means for supplying pressurized air at a higher pressure than the pressure of the preswirled tapped air to a side of the wall remote from the preswirled tapped air, thereby to induce supplemental air to flow through the passages into the preswirled tapped air such that said induced supplemental air flow causes said boundary layer to move relative to said static wall in the same direction as the direction of swirl, whereby the air flow through said passages reduces windage heating of the preswirled tapped air by reducing viscous drag on the static wall.