GB636612A - Improvements in compressors of gas turbine units - Google Patents

Abstract

636,612. Gas turbine plant. GREATREX, F. B., and MURRAY, F. R. June 20, 1947, Nos. 16413 and 25430. [Classes 110(i) and 110(iii)] To prevent icing hot gases are delivered into the air intake of a. compressor of a gas turbine engine by a distributer which entends radially from an axis about which it rotates in a plane transverse to the air intake. Hot gases from the engine are conveyed through pipes 16, an annular chamber 18 forming the leading edge of the nacelle 11, hollow struts 15 and a chamber 19 into a rotary distributer 21. The distributer 21 comprises a series of hollow, aerofoil section blade members 22 radiating from a hub 23 carried by a shaft 24. The hot gases leave the distributer through perforations in the leading or trailing edges of the blades 22. Swirl vanes 30 may be provided to give the hot gases a swirl in the direction of rotation. In the arrangement shown, the distributer is driven by the windmilling effect of the air entering the compressor, but a positive drive from the compressor rotor may by used. In an arrangement described, the distributer is driven through an epicyclic gear from the compressor shaft. A clutch is provided between the annular gear of the epicyclic gear and an extension of the compressor front bearing housing which is engaged when it is desired to put the distributer into operation. In a further modification, the leading edge of the nacelle 11 is provided with an additional chamber to which hot gases are supplied and the gases enter the blades 22 through a perforated shroud carried by the blades which forms part of the wall of the additional chamber. Seals are provided between the shroud and the fixed walls of this chamber. In this modification, the struts 15 are used to supply hot gases to the fairing 14 which is perforated to permit the hot gases to escape into the air flowing into the air intake. Specification 578.769 is referred to.