| 摘要 |
1,085,349. Turbine blade fixing; gas turbine ducted fan engines. GENERAL ELECTRIC CO. Dec.20, 1965 [Dec. 29, 1964], No. 53791/65. Headings F1J and F1T. [Also in Division F2] In a rotor assembly for turbine and like bladed machines, e.g. a gas turbine engine with an aft fan, Fig. 1 (not shown), the rotor blades are located in the correct axial position in axial fir-tree slots in the rotor disc rim 33 by members 60, thereby ensuring the correct axial relationship between sealing members 47, 50 and 48, 51. These sealing members prevent leakage between the combustion products passage containing turbine blade portions 44, and an outer air passage containing fan blade portions 46. Each member 60 comprises a strip 61 seated on the periphery of the rim 33 between adjacent slots, and radially inwardly projecting tongues 62, 63 engaging the side walls of the rim. The upstream tongue 63 extends across at least one of the adjacent slots to provide abutments for the upstream ends 41a of the blade roots 41 entering these slots. Each upstream end 41a is held in contact with the tongue 63 by a locking strip 70 and the net axial thrust exerted on the associated blade 40 during operation of the engine. The spaces between adjacent blade roots underneath platforms 43 are sealed by closefitting baffles 66, 67, the sealing being improved by the effects of centrifugal force during engine operation. Additionally, the baffles 66, 67 damp vibrations. |
