| 摘要 |
1,160,806. Gas turbine rotors. GENERAL ELECTRIC CO. Nov.7, 1967 [March 22, 1967], No.50496/67. Heading F1T. An axial flow turbine for a gas turbine engine comprises first and second stage bladed discs 52, 54, respectively, the disc 52 being connected to a shaft 24 and the discs being inter-connected by a frusto-conical torque carrying member 58 extending outwardly from the disc 52. A heat shield 62 is bolted to the periphery of the disc 52 and slidably engages at its downstream end 66 a rim 68 on member 58 adjacent the periphery of disc 54. The shield 62 is strengthened by an integral disc 84 and carries on a circumferential rib 90 a labyrinth seal ring 88. Cooling air is supplied to the annular chamber 70 defined between disc 52, members 58 and shield 62 through holes 72 in the shaft 24 and disc 52 and registering grooves 74 in member 58. This air passes from chamber 70 through holes 76 in shield 62 to passages 78 in the blades 50. Cooling air also flows to the disc surfaces through holes 46 in shaft 24. The construction reduces thermal stresses. |
