Tip cooled blade

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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Details

415115, 416 97R, 416 97A, 416 95, F01D 518

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active

052617890

ABSTRACT:
A gas turbine engine blade includes an airfoil having first and second sides and a dovetail extending from the airfoil root. The airfoil includes a tip having a tip floor with first and second tip walls extending from the floor and spaced apart to define therebetween a tip pienum. The first tip wall is recessed at least in part from the airfoil first side to define an outwardly facing tip shelf, with the tip shelf and the first tip wall defining therebetween a trough. A plurality of cooling holes extend through the tip floor at the tip shelf for channeling cooling air from a flow channel inside the airfoil into the trough for cooling the blade tip.

REFERENCES:
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W. Aung et al., "Heat Transfer in Tubulent Separated Flow Downstream of a Rearward-Facing Step," Isreal Journal of Technology, vol. 10, No. 1-2, 1972, pp. 35-41.

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