GB820913A - Control apparatus for internal combustion engine - Google Patents

Abstract

820,913. Gas turbine plant. BENDIX AVIATION CORPORATION. July 22, 1957 [Sept. 14, 1956], No. 23163/57. Class 110 (3). [Also in Group XXIX] In a gas turbine fuel regulating system the fuel metering valve 84 is controlled through arms 78, 80 in accordance with engine speed and throttle setting by a cam and a planetary transmission, of which latter one member (annulus 60) is operatively connected with the cam, a second member (planet 58) to the throttle control lever 46, and a third member (sun-wheel 62) to an engine speed responsive device 66. In the arrangement shown, the outer surface of the annulus 60 itself is formed with three cam surfaces 72, 74, 76 controlling valve 84 under engine accelerating, steady state, and engine decelerating, conditions respectively. The radial position of planet 58 is adjusted by rotation of a cam 52 consequent upon movement of throttle lever 46, and sun-wheel 62 is carried by a shaft 64 rotated by the speed responsive member 66 through a rack 68 and pinion 70. In addition, adjustment of planet 58 may be effected by translational movement of cam 52 by means of a member 42 responsive to pressure or temperature in the compressor inlet. An acceleration cam 69 also mounted on shaft 64 acts conjointly on valve 84 through control lever 80. As shown in Fig. 4, the fuel metering valve consists of a spring-loaded ported sleeve 112, the axial position of which is varied, to regulate supply of fuel from pump 30, by pressure liquid supplied through pipe 116 to the space 110 above the sleeve and controlled by a leak-off valve 82 at the end of lever 80. The rotary position of sleeve 112 may be varied by a control valve 117 in accordance with compressor discharge pressure, or any other desired engine-operating parameter. The rack 68 of the engine speed responsive member 68 is actuated by a piston subjected to pressure liquid supply to a cylinder provided with a leak-off valve operated by a centrifugal weight in accordance with engine speed, Fig. 3 (not shown). Control arms 78, 80 may be moved axially along supporting rod 86 to modify the action of their associated cams, and similar results may be obtained by pressure and/or temperature responsive devices which impart axial movements to the cams, Fig. 7 (not shown). In addition the side of annulus 60 may be formed with a cam surface for effecting appropriate axial displacement of member 60.