GB815484A - Fuel controls for gas turbine power plants - Google Patents

Abstract

815,484. Gas turbine plant. UNITED AIRCRAFT CORPORATION. Dec. 19, 1955 [Dec. 21, 1954], No. 36334/55. Class 110 (3). [Also in Group XXIX] In a gas turbine power plant 10 a lever 30 sets three cams 32, 34, 36 for co-ordinating both the propeller and fuel controls. The cam 32 sets, through the mechanism shown, the speeder spring 52 of a governor 54 which is rotated at a speed proportional to the turbine speed and operates a pilot valve 56. The cam 34 is connected through the linkage 90, 88 to a piston 94 located within a cylinder 86. The cam 36 adjusts the speeder spring of a governor which regulates the pitch of the propeller 18. The pilot valve 56 comprises a stem 58 controlled by the governor 52, 54 so that high pressure or drain pressure fluid is conducted to the chamber 66 of a cylinder 68 containing a piston 70. High pressure fluid is continuously supplied to the chamber 72 of the cylinder 68. The pistonrod 76 is connected through the linkage 80 to the follow-up sleeve 82 of the pilot valve 56. The piston-rod 76 is connected by the link 88 to the piston 94 of the reset pilot valve 86 which through a line 96 controls a reset servo-mechanism 100 which comprises a piston loaded by a spring 1021 which adds or subtracts spring force to the droop governor. The lower end of the piston-rod 76 engages a pivoted lever 118 located above the stem 116 of the fuel throttle valve 78. Interposed between the lever 118 and the stem 116 is a roller 114 carried by a rod 112 moved by a bellows 110 exposed to compressor inlet pressure and temperature. The arrangement is such that the steady-state fuel flow is always that determined by the setting of the cam 34. Specification 804,783, [Group XXXV], is referred to.