GB805003A - Improvements in and relating to inlet duct arrangements for gas turbines and compressors - Google Patents

Abstract

805,003. Turbines; centrifugal and axialflow compressors. ALLEN SONS & CO. Ltd., W. H., PERROT, F. C., and OXFORD, J. T. B. June 16, 1955 [June 25, 1954], No. 18716/54. Classes 110 (1) and 110 (3). An inlet duct for a gas turbine or compressor of the axial flow type or compressors of the centrifugal type wherein the gas enters the turbine or compressor casing laterally at one or more sides, i.e. transversely to the shaft axis and is led to a circumferential passage from which the flow is turned through approximately 90 degrees to enter the compressor or turbine blading through an annular approach passage, has the annular approach passage formed asymetrically either axially or radially or both relative to the rotor axis such that the lines of constant static pressure in the passage are inclined to a radial plane in such a manner as to produce acceleration of air or gas towards the region adjacent a lateral inlet and thereby reduce or counteract the whirl velocity in the inlet. In the axial flow gas turbine, Fig. 1, the combustion chamber 1 is connected with a circumferential passage or chamber 2 which communicates with the turbine blading 4 by an annular approach duct 5. This duct is longer at a point adjacent the inlet from the combustion chamber than at a diametrically opposite point. The radial dimensions of the duct are approximately uniform. Due to the inclination of the entry plane 8, the lines of constant static pressure are inclined in directions roughly parallel to the plane of entry. In a modification, as applied to a compressor, Figs. 6 and 7 (not shown), the entry plane 8 is at right angles to the rotor axis and the radial width of the duct is varied with the narrowest position adjacent the lateral inlet.