| 摘要 |
818,846. Turbine and compressor blade assemblies. NAPIER & SON Ltd., D. Jan. 22, 1957 [Feb. 3, 1956], No. 3510/56. Class 110 (3). In a turbine or axial-flow compressor blade ring assembly in which the blades each comprise an aerofoil portion 10, a stem portion 13 having transverse front and rear walls and at least one web extending between these walls, and a root portion 14, the individual blades are laced together by wire lacing 15 which passes through the webs of the stem portions. The lacing wire is formed in two parts 15A, 15B, as shown in Fig. 2, to give greater flexibility, and the wire may either be in the form of a single ring passing through all the blades of the blade ring or in the form of short wire segments arranged end-to-end in the form of a ring, each wire segment passing through a group of blades. Enlarged or deformed portions are provided in the wire to prevent the wire disengaging from the holes in the stem portions. The wire lacing may pass through ferrules fitted in the blade stem portions so as to prevent wear caused by rubbing of the wire on the stem portions. In Fig. 7 short wires such as 28C, 28D pass obliquely through holes in the stem portion 26A, 26B . . . each stem portion being connected to the stem portions of the blades on either side of it. The object of the invention is to reduce blade vibration and to avoid the use of lacing wire disposed in the working fluid stream.
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