GB614160A - Improvements relating to combustion turbine power plant - Google Patents

Abstract

614,160. Centrifugal and radial-flow compressors; jet-propulsion plant. POWER JETS (RESEARCH & DEVELOPMENT), Ltd., and JOHNSON, W. E. P. March 5, 1945, No. 5520. [Classes 110 (i) and 110 (iii)] In a gas turbine plant comprising a turbinedriven compressor and a combustion chamber, the compressor consists of one or more single entry centrifugal stages, the or each stage being backed by multi-stage radial-flow blading. Rotors 7, 20, Fig. 1, which are mounted on a shaft 6 and driven by a gas turbine 1, each comprise a centrifugal impeller having radial flow blading 16, 24 on its rear face. The three-stage compressor, comprising centrifugal blading 8, 21 and intermediate inward-flow blading 14, 16 delivers compressed air to combustion chambers 4. Outward-flow blading 23, 24 works in parallel with the centrifugal blading 21, receiving air through ducts 29, its purpose being to balance end thrust and prevent air leakage along the rear face of the rotor 20. An annular inner wall 13, which is supported by diffuser vanes 11, may be hollow and may be ventilated through struts 12a or the vanes 11, which may be hollow for this purpose, to provide intercooling of the compressed air. In a modification, Fig. 2, the passage between the first and second stages is considerably lengthened to provide more gradual diffusion, and comprises walls 48, 49 separated by a baffle 50, the latter being supported by hollow struts 54 which also act as ventilators for the enclosed space 55. Cooling fins 48a are provided. In both embodiments the guide vanes 14, 44 and their shrouding may be hollow to permit the passage of a cooling fluid. According to the Provisional Specification, the blade angles or stagger of the radial flow stator blading or the diffuser blades of the centrifugal stages may be made mechanically adjustable. Specifications 242,855, [Class 110 (i)], and 443,620 are referred to.