| 摘要 |
<p>1,213,443. Automatic speed control. UNITED AIRCRAFT CORP. Jan.13, 1969 [March 8, 1968], No.1862/69. Heading G3R. [Also in Divisions F1 and F2] In a dual-fuel gas turbine, during transfer from one source to the other the valves controlling flow from the sources to respective combustion chamber manifolds are respectively closed and opened over the same period and ideally at the same speed to ensure smooth transfer. As shown, valves 14, 24 are respectively open and closed, and flow from source 10 through valve 14 is modulated according to signals from control 96 which senses engine speed and temperature parameters and supplies signals through summer 50 to motor 30. Totransfer to source 20, relay 62 is energized to reposition its moving contacts 64, 74, 92. Motor 30 will normally be stationary at this time so that the signal from potentiometer 34 will differentiate to zero at 54 so that summer 66 will only receive a signal from potentiometer 70 which is amplified at 68 and via 78 determines the rate of closure of valve 14 by motor 30. The feedback through 34, 54 ensures controlled movement of motor 30. The signal from 34 is also differentiated at 48 and applies a constant voltage input to summer 50 the output of which is applied via 88 to motor 32 which provides a feedback to summer 50 via potentiometer 36 and differentiator 46 such that the speed of opening of valve 24 matches the speed of closure of valve 14 except for such variations as may be dictated by signals to summer 50 from control 96. Either source may be gas or liquid. Valve 24 may be of the butterfly type.</p> |
