GB791062A - Improvements in or relating to gas turbine engine power plants - Google Patents

Abstract

791,062. Gas-turbine plant. ROLLS-ROYCE, Ltd. May 7, 1956 [May 5, 1955], No. 13118/55. Class 110 (3). [Also in Group XXIX] A gas-turbine power plant comprising two or more engines supplied by a common fuel system has, in each engine, at least one temperaturesensitive element disposed in the gas stream downstream of the combustion equipment and common means connected to the temperaturesensitive elements to reduce the fuel flow through the common system when one of the temperature sensitive elements senses a predetermined maximum temperature. Gas turbine jet-propulsion engines 1, 2, 3, 4 are supplied with fuel for a common fuel system consisting of a fuel tank or tanks 9, a booster pump or pumps 10, a high pressure fuel pump or pumps 11 and a fuel line 12. The common fuel supply 12 is controlled by a throttle valve 12a and by varying the stroke of the pump 11. The angle of the swashplate 15 is controlled by a spring- loaded piston 16 the position of which is determined by the flow through the vent pipe 19 in turn controlled by the valve 20. The valve 20 is carried by a pivoted lever 21 which is acted on by an evacuated capsule 25 responsive to the atmospheric pressure, a push-rod 29 loaded by the fuel pressure in the pipe 12 and a spring 30. This arrangement maintains a given fuel pressure for each altitude. The lever 21 is also loaded by a push-rod 34 connected to a Bourdon tube or capsule stack 33 responsive to the pressure in piping 32, which is connected in turn to temperature sensitive elements 31 of the mercury vapour type. When one of the elements 31 senses a predetermined maximum temperature the valve 20 is opened and the fuel supply to all of the engines reduced. The preset maximum temperature may be varied by means of the lever 38. The Bourdon tube or capsule stack 33 may be arranged to increase the fuel supply when the highest temperature falls below the predetermined value. The application of the invention to the fuel system described in Specification 753,474 is also described.- The elements 31 may be located at the outlet of the combustion equipment 6 or when the engine has a multi-stage turbine, in or adjacent to the leading edge of the nozzle guide vanes of a downstream stage or at the outlet of the turbine. The common control means may be a throttle valve in the main fuel line.