| 摘要 |
602,706. Gas turbines. GILBERT, A. V. Nov. 9, 1945, No. 30041. [Class 110 (iii)] A gas turbine rotor for use in the propulsion of automobiles is provided with adjustable blades the angle of which relative to the axis of the rotor is adjusted in accordance with the load on the shaft driven by the rotor. A compound gas turbine, Fig. 2, has two independently rotating stages A, B, the first stage A has fixed blades D and is used to drive the compressor of the plant and the second stage B has adjustable blades G and is used to drive the output shaft N. The blades G are rotatably mounted in a bowllike housing B<1> by shafts H attached to bevel pinions K which are engaged by two crown bevel wheels L and M. The wheel M is attached to, and the wheel L is rotatably mounted on, the shaft N. Attached to the wheel M is a disc O also secured to the shaft N and provided with four arcuate recesses P in which are mounted compression springs Q, and attached to wheel L is a disc T with four projections U which fit into the recesses P on one side of the springs Q. Relative rotation of the discs T and O compresses the springs Q. Any relative movement between the discs T and O due to changes in the torque required by the shaft N will cause the crown bevel wheels L and M to rotate the pinions K and adjust the angle of the blades G and thus alter the output of the turbine to suit. Projections on the distance pieces S between the springs Q limit the amount by which the springs Q may be compressed.
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