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US 4,302,153 AGranted
Rotor blade for a gas turbine engine
AssigneeROLLS-ROYCE plc
InventorHenry Tubbs
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AssigneeROLLS-ROYCE plc
InventorHenry Tubbs
Estimating the term…
A rotor blade for a gas turbine engine comprises an aerofoil, shank portion and a root by which the remainder of the blade may be supported from a rotor disc. Cooling for the aerofoil is provided by passages in the leading portion of the aerofoil which are fed with cooling air from an entry aperture and a sealed liquid cooling circuit which contains a cooling liquid. This circuit comprises a liquid feed passage adjacent the trailing edge of the aerofoil and connected adjacent the tip of the aerofoil with a vapor return passage, both passages communicating with a sealed cavity within the shank of the blade. In operation the cooling fluid (e.g. metallic sodium) flows under the influence of centrifugal and other forces along the feed passage, is vaporized and returns to the cavity via the return passage. The cavity acts as a condenser for the fluid.
A rotor blade for a gas turbine engine comprising an aerofoil, a shank portion and a root adapted to engage with a rotor disc so as to support the aerofoil via the shank, and cooling means for the aerofoil comprising passages in the leading portion of the aerofoil, a cooling air entry aperture connected to the passages for the flow of cooling air therethrough, and a sealed cooling fluid circuit in the trailing portion of the aerofoil containing a quantity of cooling fluid and comprising a liquid feed passage closely adjacent to the trailing edge, and a vapour return passage forward of said liquid feed passage, wall portions extending between the flanks of the blade which at least partly divide said feed from said return passage, and a sealed cavity within the shank of the blade communicating with the feed and return passages and adapted to operate as a condenser of the vapour.
Dependencies are inferred from the claim text.