Accession Number : ADD011525

Title :   Cooled Turbine Blade Tip Closure.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON DC

Personal Author(s) : Horvath,R L ; Harris,R W

Report Date : 11 Dec 1984

Pagination or Media Count : 6

Abstract : In this patents, an improved high pressure turbine rotor blade and tip cap structure therefore is provided, which comprises, a plurality of metallic layers bonded to the tip end of the blade, each layer having a peripheral shape conforming to the camber of the blade, the layers defining a plurality of radially outwardly opening, serpentine-shaped passageways for passage of coolant fluid through the periphery of the tip end of the blade.

Descriptors :   *Patents, *Rotor blades(Turbomachinery), *Closures, Air flow, Cooling, Gas turbines, Metals, Layers, Bonding, High temperature, FAbrication, Holes(Openings), Camber

Subject Categories : Hydraulic and Pneumatic Equipment

Distribution Statement : APPROVED FOR PUBLIC RELEASE