Vane for a gas turbine engine having means for impingement cooli

Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...

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416 96A, 415115, F01D 518

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active

041053648

ABSTRACT:
A vane for directing hot gases of a gas turbine engine and comprising at least one platform and a hollow aerofoil portion having an air entry tube extending spanwise therein, the tube being provided with a plurality of apertures, the size and the spacing therebetween being chosen to cause cooling fluid to impinge on the interior surface of the aerofoil portion in the form of a plurality of jets. A plurality of columnar projections extend between the interior surface of the aerofoil portion and the exterior of the air entry tube, each projection being positioned directly upstream of one of the apertures in the air entry tube with respect to the general flow of impinged fluid in the space between the interior surface of the aerofoil portion and the exterior of the air entry tube.

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patent: 3620643 (1971-11-01), Jones
patent: 3700348 (1972-10-01), Corsmeir et al.
patent: 3781129 (1973-12-01), Aspinwall
patent: 3806276 (1974-04-01), Aspinwall
patent: 3846041 (1974-11-01), Albani
patent: 3864199 (1975-02-01), McGinnis

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