| 摘要 |
723,394. Gas-turbine rotors. GENERAL MOTORS CORPORATION. Oct. 10, 1952 [Oct. 10, 1951], No. 25423/52. Class 110 (3). [Also in Group XXII] A hollow gas-turbine rotor blade of aerofoil cross-section comprises at least one strip welded or brazed along longitudinal surfaces to the opposite internal walls of the blade so as to form longitudinally extending channels therein. The blade comprises a sheet-metal portion 11 brazed at the trailing edge, the walls of the blade preferably tapering towards the tip The blade root is composed of two serrated castings 21, 22 which are brazed to the portion 11. The walls 12, 13 of the blade are bridged by metal strips 17 which preferably extend slightly within the rim of the rotor disc to the tip of the blade. Air is fed to the blade through a passage in the rotor disc. In a modification, the strips 17 are provided with flanges and in a further modification they are replaced by a corrugated strip. The portion 11 may be formed from a tube with tapered walls or constitute a casting. |
