GB656337A - Improvements in compressor gas turbine assemblies - Google Patents

Abstract

656,337. Gas turbine plant; jet propulsion plant. BOSCO, C. A. L. Jan. 3, 1949, No. 106. Convention date, Jan. 5, 1948. [Class 110(iii)] In a gas turbine, a circular series of closed combustion chambers 17 is defined by pockets in a casing 10 and surfaces of a rotary distributer 6. The distributer has a single air port 15 and a single combustion product port 16, spaced circumferentially, which operate in sequence to admit air to and discharge hot gases from the combustion chambers. Each chamber has a fuel nozzle 18 and a spark plug 19. The rotor wheels 5 have inner ,axial-flow air-compressor blades 8 and outer turbine blades 11. The ,rotor drives a shaft 4 through reduction gearing 2. The distributer may be, as shown, fast on the shaft 1, or, independently mounted and driven through a speed-reduction gear. The casing may have a cooling jacket. Two units may be arranged end-to-end in one casing with one driving shaft. Fig. 5 shows a turbine with centrifugal impellers 38, 38a, two sets of combustion chambers 47, 47a, two rotary distributers 36, 36a, and oppositely-running inward-flow radial turbine wheels 35, 35a. The turbines exhaust into stationary central pipes 52, 52a within the hollow shafts 31, 31a which are mounted in the casing. The air and gas ports 45, 46 are in the cylindrical flanges of the distributers. In Fig. 8 the plant is arranged for driving an air-screw 30 and energizing a propulsion jet 29. The combustion chambers are defined by two flanges 16d, 54, formed with gas discharge ports. These ports are controlled by disc valves 52, 53 which rotate with the distributer and are adjusted relatively thereto in opposite directions by a gear operated from an external lever. A cooling air-jacket 55a is open downstream and air is drawn through it by ejector action of the propulsion jet. Fig. 14 shows a distributer 6g with a single disc valve 52g which controls the flow of hot gases from the combustion chambers to the turbine and the propulsion jet duct 29g. The rotors may have three tiers of blades; two tiers forming two stages of a compressor and one forming the turbine. In a plant for'jet propulsion alone, there are two sets of combustion chambers, one set each for the compressor turbine and the propulsion jet.