stuetzkonstruktion for the fastening of turbines - rotor blades to a laeufer

摘要

1,179,098. Turbine blade fixing; jet propulsion plant. GENERAL ELECTRIC CO. Sept. 5, 1967 [Dec.7, 1966], No.40544/67. Headings F1J and F1T. A supporting structure for securing hollow gas turbine blades 14 at the tip of fan rotor blades 12 comprises a box section base member carrying two or more blades 14 and formed by circumferentially extending plates 22, 26, 28 welded together, and side rails 34, 36 bolted at 54 to extensions 50 of the fan blades 12 and having holes 38 loosely engaging projections 32 on the base member. The projections 32 are formed by the ends of tubular pins 30 passing through and welded to the plates 26, 28. The side rails 34, 36 are segmental, each segment supporting several groups of blades 14 and being connected to the ends of adjacent segments by slotted straps 58 and studs 60 for torque transmission. Stiffening cross members 56 extend between the facing surfaces of side rails 34, 36 and are held in position by bolts 64 which also retain a sealing member 62. A band segment 44 is clamped at the inner periphery of rails 34, 36 by a tab 48 and lips 46. Sealing members 68 are provided at the extremities of the band 44. The plates 22, 26, 28 of the base member of each blade group and the corresponding shroud plate 24 are all uncurved such that, as shown in Fig. 4, the blades 14 extend nomal to the shroud and base and parallel to a radial line. The blades 14 are driven by the exhaust gases of jet propulsion engines (16), Fig. 1 (not shown), the blades 12 forming a propulsion fan.