| 摘要 |
737,473. Turbines ; axial-flow compressors. NAPIER & SON, Ltd., D. Sept. 28, 1953 [Oct. 3, 1952], No. 24895/52. Classes 110 (1) and 110 (3). A turbine or axial flow compressor having a guide blade ring assembly comprising inner and outer annular members with angularly adjustable guide blades pivoted therein about radial axes, has non-adjustable guide blades dispersed at intervals between the adjustable guide blades and connected to both the annular members. The hot gases from' an annular combustion chamber or several individual combustion chambers 11 pass through a ring of adjustable guide blades 12 to the turbine rotor. The combustion chambers having a sliding fit in an annular member 16. The blades 12 are adjusted by an annular adjusting member 31 as described in Specification 737,472. To maintain the annular members 16 and 30 in which the blades are pivoted in a given position relative to one another so as to prevent binding of the pivots, fixed blades 26 are provided. The fixed blades are attached to the flange 19 of the annular member 16 by studs 27 at least one of which is threaded to receive a nut 28 and to the outer annular member 30 by links 34 pivoted to spigots 33 on the blades and the member 30. The links 34 are disposed in a plane normal to the axis of the turbine or compressor, so that the blades 26 can expand and contract radially but' are not free to move axially relative to the casing 30. A shroud ring 30, which may be made up of separate arcuate portions, surrounds the fixed and adjustable blades and is mounted on and located by the spigots 32. The rear edge of this shroud ring abuts against a shoulder of the casing 30 to form a gas seal. To avoid all of the axial thrust on the blades 12 being taken through the outer ends of the blades, compressed air from the compressor is led through the shaft 15 and ports 22, 23 to the rear of the annular member 16. The blade platforms 35, Fig. 4, are provided with stops 36, 37 which in the end positions of the blades abut against corresponding stops 38, 39 on adjacent blade platforms. |
