GB513151A - Improvements in or relating to power plants comprising a gas turbine employing products of combustion and a compressor for compressing the combustion air - Google Patents

Abstract

513,151. Gas turbines. SULZER FRERES SOC. ANON. March 31,1939, Nos. 10125 and 10126. Convention dates, April 7, 1938, and Feb. 25, 1939. [Class 110 (iii)] A multi-stage air compressor 1 supplies a multi-stage turbine 2 in which a portion of the working fluid is passed into re-heating chambers 3a, 3b ,and 3c, and returned to the main supply of gas before the two streams enter the next stage. Exhaust gas from the turbine passes through a heat-exchanger 10 and to atmosphere through a pipe 25, while air from the compressor passes through the exchanger, pipe 11, combustion chamber 12 to the first stage blades 14. A slight excess of air may be provided in the intermediate heaters. Intercoolers 6a, 6b, are fitted to the compressor. After expansion in stage 14, a portion of the gas is deflected into a conduit 15, heated in a chamber 3a and is led through nozzles 27, Fig. 3, to the centre parts 29 of the spaces between guide vanes 28. The gas not reheated and passing through space 16 follows arrows 30 forming a cooler layer in the region 'of blades 28. In an alternative arrangement, Figs. 5, 6, 7, the deflected gases flow through a conduit 47 into annular chambers 48, 49, into a heating chamber 50 leading to nozzles 54. These lead to pairs of guide passages 55, and the gas not re-heated passes through passages 56. The two streams are arranged to flow at about the same speed through the guide blades. Openings 57 allow a portion of the cooler gases to pass into channels 55. Guide blades 58 impart a whirl of gases entering the chamber 50. The temperature of the gases after passing through chambers 12, 3a, 3b, 3c, is stated to be between 500‹C. and 600‹C.