GB616622A - Improvements in or relating to gas-turbines and controlling means therefor - Google Patents

Abstract

616,622. Gas-turbine plant. GRIFFITH, A. A. Sept. 11, 1946, No. 27342. [Class 110 (iii)] A gas-turbine plant for aircraft is controlled by the manual regulation of the quantity of compressed air which byepasses the combustion chamber and the fuel supply is determined automatically by a thermostatic device responsive to the absolute temperature of the gases leaving the combustion chamber, or by such a device responsive to the rise in the temperature of the gases passing through the combustion chamber. Single rings of compressor and turbine bladings 10, 14, are carried by oppositely rotating freely mounted rotor discs. Air is delivered to an annular combustion chamber 12 through a conduit 11 and air may be byepassed through channels 27, controlled by valves 28, to mix with the gases from the combustion chamber in the annular passage 13. The supply of fuel from a source 22 is regulated by a thermostatically-controlled valve 25 with a thermometric device 26 in the combustion chamber. The fuel is distributed in the combustion chamber by a centrifugal atomizer 17 which is rotated by vanes 18 in the air stream. Fuel passes through radial pipes 24 and air passes along an annular conduit 19 into the chamber 21. In a plant having a circular assembly of a number of combustion chambers, each chamber is associated with a byepass conduit for the air. In combustion chambers having secondary air-inlets, the air may be byepassed to these inlets. An over-riding speed-governor control may be provided.