GB717100A - Improvements in or relating to turbine starters for gas turbine units - Google Patents

Abstract

717,100. Gas turbine plant; turbine nozzles. BENDIX AVIATION CORPORATION. Oct. 3, 1952 [Oct. 3, 1951], No. 24865/52. Class 110(3) [Also in Group XII] In a starter system for a gas turbine comprising a starter turbine 5 having a combustion chamber 6 supplied with a mixture of fuel and compressed air, the source of fuel is adapted to be pressureized by the source of air 9 upon operation of a device controlling the admission of compressed air to the combustion chamber. The compressed air is fed to the combustion chamber through a pressure regulating valve 10, a solenoid-operated valve 11 and a nozzle 13. The fuel is fed through a check valve 25, a tank 17 and a poppet valve 15 which prevents the fuel from flowing into the combustion chamber until the tank is pressureized. The tank has an elastic diaphragm responsive to the pressure of compressed air fed thereto through, an orifice 22 and is provided with a screen 21 forming a minimum air space. The solenoid of the valve 11 and a sparking plug 26 are connected to a battery 29 through a time switch 31; a spark coil 28 being disposed in the circuit as shown. After a predetermined time the switch 31 de-energizes the valve 11 thus shutting off the air supply and permitting the valve 15 to close. A centrifugally-operated switch 34 may be inserted in series with the switch 31 to de-energize the solenoid. The combustion chamber comprises a two-part housing, the parts 35, 40 of which have interengaging flanges interconnected by a clamping ring 41. The fuel nozzle 7 and the air inlet nozzle 13 are mounted in the housing 35, the fuel nozzle having an air deflector 45 and a frusto-conical portion 43, 44 opposed to the nozzle 13. The nozzle block 46 is formed integral with the housing 40 or secured thereto and has ports 47 which register with nozzles 48 in a plate 49. The plate 49 is secured to said block by screws and has a baffle 51.