GB1081649A - Turbine wheel - Google Patents

Abstract

1,081,649. Turbines. GENERAL MOTORS CORPORATION. March 31, 1966 [April 30, 1965], No. 14334/66. Heading F1T. The high and low pressure turbine rotor wheels 54, 94 in a gas turbine lift engine are drivingly connected to their respective shafts 72, 88 by annular frusto-conical and double frusto-conical members 70, 90 forming the sole support for the respective rotor wheels. Wheel 54 is spaced at its inner periphery from its compressor driving shaft 72 and radial movement of the wheel is limited by an integral annular extension 66 bottoming on a spacer member 76 attached to the shaft 72. The inner periphery of wheel 94 is also spaced from its power shaft 88 which is rotatably mounted within shaft 72 by a bearing 87. Support 70 may be formed integral with wheel 54. The angles of the conical portions of supports 70, 90 are such that the axial deflections of the supports at their greatest diameters due to centrifugal forces balance the axial deflections of their respective wheels 54, 94 due to gas loading of the blades 58, 98 at design speed. The turbine includes guide vanes 30, 34, the vanes 34 being attached at their radially outer ends to a shroud ring 32 which is secured to the outer casing 14 by hangers 36 which extend through the casing 14 to provide engine mounts 38. An inner shroud ring 40 is supported by the vanes 34 and carries a double-walled diaphragm 48 attached to a support sleeve 46 for shaft bearings 71, 87. An annular bracing member 50 extends between diaphragm 48 and a forward extension 42 of shroud ring 40.