Patent GB-1164406-A (GB)
Title: Gas Turbine Jet Propulsion Engine
Inventor: JOHNSON CHRISTOPHER LINLEY
IPC: F02C9/44
Filed: 1968-06-24
Abstract: 1,164,406. Gas turbine jet engines - by-pass duct combustion equipment. ROLLS-ROYCE Ltd. June 24, 1968, No.30104/68. Heading F1J. The invention relates to a gas turbine jet engine of the by-pass type having combustion equipment for burning fuel in the by-pass duct and control means for controlling supply of fuel to such equipment. The invention is described with reference to an engine of the kind comprising LP compressor 3, HP compressor 4, combustion equipment 5, HP turbine 6 and LP turbine 9, the HP turbine driving the HP compressor through shaft 7 and the LP turbine driving the LP compressor through shaft 10. The exhaust gas from the turbine 9 passes through two ducts 20, 21 which terminate in variable area propulsion nozzles 22, 23 which may be moved to provide either forward thrust or vertical lift. A portion of air delivered by the LP compressor 3 passes thro through two ducts 12, 13 which terminate in variable area propulsion nozzles 14,15 which may be moved to provide either forward thrust or vertical lift. Combustion equipments 16, 17 are provided in the by-pass ducts 12, 13 whereby the thrust of the gases discharged through the nozzles 14, 15 may be increased, for example at aircraft take-off. In accordance with the invention, the fuel system for controlling supply of fuel to the combustion equipments 16, 17 comprises means for measuring the dynamic pressure in the by-pass ducts 12, 13 upstream of the by-pass combustion equipments, and control means which are responsive to the measuring means to control the supply of fuel to the by-pass combustion equipments. In Fig. 1 fuel is supplied to the equipments 16, 17 by means of a vapour core type fuel pump 34, the fuel discharging into an annular manifold 27 and through lines 25, 26 to the equipments 16, 17. Fuel passes into the pump from inlet 35 under control of an axially movable sleeve valve 36 which co-operates with a valve seat 37, the valve being movable by means of a piston 40 slidable in cylinder 42, the piston being connected to the valve by linkage 41. The face 43 of the piston is subjected to pressure of fuel at the outlet of pump 34 which pressure is communicated through line 45, and the face 44 of the piston is subjected to the pressure in line 46 which communicates with line 45 through restriction 47. The line 46 also communicates at 51 with a chamber 50 in a housing 61, the communication being controlled by an axially movable valve member 52. The valve member 52 is rotated continuously in operation by gearing 56 to prevent "stiction" and is movable axially by the arm 53 of a bell-crank lever 53, 54, the lever being connected to the housing 61 by link 60 and being movable about fixed fulcrum 62. The housing 61 is divided into three chambers 65, 66, 67 by two diaphragms 63, 64, the diaphragms being operatively connected to the bell-crank lever. The chamber 67 is connected by line 74 to a point 73' of the plenum chamber 11 upstream of the combustion equipments 16, 17 so as to measure the total pressure at that point. The chamber 66 is connected by line 73 to the point 73' so as to measure the static pressure at that point so that the force on the diaphragm 64 is a measure of the dynamic head at the point 73'. The chamber 65 is connected to chamber 66 through restriction 68 and through restriction 69 to outlet 70 to atmosphere, it being arranged that the pressure on the diaphragm 63 is functionally related to the dynamic pressure at the fuel injection nozzles 16, 17. Movement of the bell-crank lever 53, 54 will cause variation of fuel pressure in the line 46 and so movement of the piston 40 and of the sleeve valve 36 so that the fuel output of the pump 34 will be varied so as to restore the position of the bell-crank lever. In a second embodiment Fig. 2 a nozzle 124 is connected to the plenum space 111, flow through the nozzle being at sonic velocity. A thermocouple 177 is disposed in the nozzle 124 and the signal therefrom is transmitted to a device 181 which acts through linkage to control the position of the fulcrum point 162 of the bell-crank lever 153, 154, the device 181 being also responsive to the rate of change of temperature sensed by the thermocouple 177. A signal dependent on the speed of the shaft 110 as sensed by the device 183 is also communicated to the device 181.