GB955150A - Improvements in or relating to gas turbines - Google Patents

Abstract

955,150. Gas turbine plant. GASTURBINENBAU UND ENERGIEMASCHINENENTWICKLUNG PIRNA VEB. Sept. 2, 1960, No. 30277/60. Heading F1G. [Also in Division F4] A rotary fuel atomizer 44 for a gas turbine comprises a disc 52 mounted on the turbine rotor 35, a member 53 having a cylindrical external periphery and secured to the disc 52, and a ring shaped partition 54 mounted on webs 57 clamped between the disc 52 and the member 53. The inner surfaces of the disc 52 and the member 53 are continuous and form a hyperboloid of revolution over which the fuel flows to a combustion chamber 12. The region of the inner surface of the member 53 at its ejector edge is disposed at a small angle to a radial plane. The partition 54 is set back between the webs 57 to form a narrow converging slit 59 for the fuel. One or more sets of fuel ducts 72 ... 75 are formed in a fixed hub 67 projecting between the partition 54 and the rotor 35 and convey fuel to nozzles 76 obliquely disposed in the direction of rotation and arranged in a circle. The spaces between the end of the fixed hub 67 and the rotor 35 are sealed by labyrinths. Primary air enters the combustion chamber through openings 89, 90 and narrow gaps 87, 88 between a fixed member 86 and laterally projecting edges 53b, 84b on the rotary atomizing member 53 and on a ring 84 mounted on the fixed hub 67. In a modification, Fig. 3, (not shown) the rotary atomizing member 53 has a radial flange at its discharge edge forming an annular chamber and radial holes are provided for the discharge of the fuel. Specification 882,202 is referred to.