GB513816A - Improvements in or relating to gas turbine plants - Google Patents

Abstract

513,816. Elastic-fluid turbines. SOC. RATEAU, and ANXIONNAZ, R. Aug. 3, 1938, No. 22998. Convention date, Aug. 4, 1937. [Class 110 (iii)] In a combustion-gas turbine system wherein one turbine stage 2, Fig. 1, with distributing nozzles or blades 1 is immediately followed by another turbine wheel 4 on. a separate shaft, the excess expansion of the first stage is utilized in the second wheel together with a further expansion due to intermediate distributers 3 or the second wheel itself which is then a reaction wheel. The second wheel preferably rotates oppositely to the first wheel to avoid deviation in the fluid flow. 'A balancing conduit may be provided between an intermediate turbine point and a stage of compression with equivalent pressure as in Specification 490,198. Wheel 2, Fig. 6, drives two series compressers 5, 6 while wheel 4 drives an external load 7. A cooler 8 and heater 9 are in series with the compressers 5, 6 while the conduit 10 may have a gas heater and also a heat regenerator 11. The velocity and direction of the conduit gases is made equal to that of the main stream by a volute 12, Fig. 8, communicating with an annular outlet 13 between wheel 2 and nozzles 3. Guide vanes may be also used in the volute 12, the outlet 13 or beyond the outlet and these vanes may be adjustable, preferably simultaneously. To adjust the pressure in the conduit 10, valves may be provided to select' the compression stage from which the gas is obtained. Two turbine sets driving separate external loads may be supplied in parallel from compressor 6 driven by one set, compresser 5 being driven by the' other set and conduit 10 supplying both sets, also in parallel. Compresser 6 may in this case have an electric starter and an inlet valve direct to atmosphere, compresser 5 and its related set being started when the first set has reached a sufficient speed. In a modification, the electric starter is geared to both compressers but at different speeds, the high-pressure set 6 turning at a higher speed than set 5. clutches being provided to cut out the starters at sufficient speed. For high temperatures, Fig. 17, the combustion chamber 52 and turbine sets are enclosed within double walls 49, 50. the intermediate space 51 receiving cold air under a pressure similar to that in chamber 52. Screens may be provided between the two walls to reduce heat radiation. The cooling air in space 51 may be provided by compresser 6 before reaching the combustion chamber 52.