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