GB931105A - Improvements in combustion apparatus - Google Patents

Abstract

931,105. Liquid fuel burners. POWER JETS (RESEARCH & DEVELOPMENT) Ltd June 16, 1960 [June 23, 1959], No. 21449/59. Class 75 (1). [Also in Group XXVI] Combustion apparatus for a gas turbine plant comprises a rotatable fuel distributing disc 11 having a coaxial recess 13 in its side face, the junction 13a between the outer wall of the recess and the side face of the disc being curved, means for introducing liquid fuel into the recess 13 and a swirler 15 in the recess. The fuel flows over the curved junction 13a and over the side face of the disc with a swirling motion either with or against the rotation of the disc. The disc is supported on a sleeve 12 which is mounted on a shaft 4 connecting the rotors of an axial flow turbine 3 and an axial flow compresser 1, the disc forming the upstream end wall of an annular flame tube 2. The disc is slightly coned and carries paddles 19. Air from the compressor enters the flame tube through an annular inlet 2a having a stabilizer 30 and atomizes the sheet of fuel leaving the disc. The fuel is delivered by a pipe 20 to an annular gallery 21 and passes through an aperture 26 to an annular channel 25 and then through aper - tures 27 to an annular gallery 14 formed by the disc and the sleeve 12. A series of ports in the sleeve convey the fuel to the recess 13 in the disc. Spaced vanes 18 are disposed between the ports. The swirler 15 is annular and is clamped between the sleeve and the gallery and has a series of inclined slots through which the fuel passes. The outer wall 5 of the flame tube is spaced from the outer casing wall 6 to form a coolant passage 7 and the inner wall of the flame tube comprises two skins 8, 9 forming a passage 10 supplied with air through a conduit 28 and ports 29 in the sleeve 12. In a modified construction, Fig. 4, the disc 11 and sleeve 12 are integral and the fuel is supplied to the disc 11 by an annular channel 25 and ports 27. An insert 32 carries spaced vanes 33 and defines with the disc 11 a fuel gallery 31. Ducts 34 convey the fuel to inclined, preferably helical, channels 35a formed on the periphery of an annular member 35 secured to the disc within the recess 13. The inwardly-facing wall of the recess 13 is formed with an annular depression 36. The fuel may be supplied through a conduit in the hollow rotor shaft. Specifications 853,110 and 917,704 are referred to.