| 摘要 |
1,135,349. Turbines. UNITED AIRCRAFT CORP. Nov. 13, 1967 [Nov. 23, 1966], No. 51611/67. Heading F1T. To facilitate removal of the guide vanes in a turbine or the like, e.g. the turbine nozzle guide vanes in a gas turbine engine, the individual vanes 24 are connected to an arcuate segment 30 of a split retaining ring by pins 32, the ring being removably mounted within the machine outer casing 22. In the assembled state, shown in Fig. 3, the pins 32 also engage an annular support member 50 carrying a seal 42 and bolted at 52 to an inner casing 54 itself bolted at 56 to the outer casing 22 and an annular member 58. The radially outer platforms 34 on the vanes 24 are thus held in position. An inner platform 62 on each vane is joined by a spline connection 64 to an annular member 66, in turn connected through a spline 68 to an inner support 70 bolted at 72 to a casing 76. An additional support member 78 has a lug 90 engaging a finger 82 on the platform 62 to limit radially outward movement of the vane 24 should the support structure at the outer end of the vane fail. A similar finger 80 adjacent the leading edge of platform 62 engages between lugs on member 66. The latter carries an annular shield 92 to prevent a bolt 72 from entering the gas stream should the bolt fail. To remove the guide vane assembly, bolts 60, 56 and then 52 are removed so that casings 22, 54 and member 50 can be slid to the left into the position shown in Fig. 5. The vane assembly is then moved to the left to disengage splines 68 so that the assembly can be moved radially outwards to the position shown dotted. A stator shroud ring 96 surrounding the rotor blades 26 can now be removed if required. The construction also permits removal of the guide vanes 24 individually rather than as a complete segment. The vanes are hollow to receive cooling air from a manifold 36 supplied with the air through passages 40 in the pins 32. |
