GB802667A - Improvements in or relating to a turbine wheel assembly for use with a gas turbine engine and method of manufacturing same - Google Patents

Abstract

802,667. Bladed turbine rotors. CHRYSLER CORPORATION. Feb. 18, 1955 [March 15, 1954], No. 4905/55. Class 110 (3). A turbine wheel for use in a gas turbine engine comprises a circular disc 10 and a cast rim 18 secured to the periphery of the disc, the rim having a plurality of circumferentially-spaced blades 22 formed integrally therewith, and at least one of the members comprising said rim and disc has a portion of reduced axial width adjacent its juncture with the other of the members. The rim may be formed of a high heat-resistant metal and the disc may be formed of a relatively ductile material. The rim and disc may be secured together by brazing. The disc in Fig. 2 is formed with a portion 10a of reduced axial width inwardly of the flanged periphery 17 to which is secured the rim 18. In Fig. 4 the outer periphery of the disc flange and the inner periphery of the rim are axially extended so that they each have a portion of reduced axial width adjacent the juncture. In a further embodiment the lateral faces of the disc periphery and of the rim are formed with annular grooves to provide portions of reduced axial width adjacent the juncture. The rim portion 68 in Figs. 6 and 7 comprises flange portions 66, 70 and a web 64 which provides the portion of reduced axial width. Circumferentially - spaced radially - extending ribs 72 are formed between the flanges radially inwardly of each blade 62. Specification 802,666 is referred to.