GB655784A - Means for anti-icing of compressors - Google Patents

Abstract

655,784. Gas turbine plant; compressors. LUTTMAN, H. C., and ROE CANADA Ltd., A. V. Nov. 18, 1948, No. 29948. [Classes 110(i) and 110(iii)] The whole or part of the surfaces of a gas turbine plant air compressor which are exposed to the air stream and are susceptible to the formation of ice thereon have a dark coloured finish applied to them and heat producing means are provided to project radiant heat on to these surfaces. The outer peripheral wall 10, the supporting struts 8 of the front compressor bearing housing 7, the inlet guide vanes 9 .and the first two or three rows of stator blades 5 are heated by conduction from a heating medium, such as tetracresyl silicate or oil circulated through conduits 14, 15 and jacket 13. The heating medium is heated in a heat exchanger located in the turbine exhaust gas stream. If desired, the parts referred to may be heated by means of electrical resistance elements embedded in them. The rotor blades 5 and the nose bullet 11 are heated by radiation from the above mentioned parts, and to facilitate this, the stator blades 5, the inlet guide vanes 9, the inner surfaces of the stator .casing 2, the surfaces of the rotor blades 6 and bullet 11 are finished in a matt black by any suitable chemical or dyeing process. The extreme forward portion B<SP>11</SP> of the bullet and leading edges B of the struts 8, which can be viewed perpendicularly through the compressor air intake entry, are left brightly polished to reduce to a minimum the radiation into the atmosphere. The demarcation lines D and D" are so located' that the normals to the surfaces of the bullet and struts through these lines are tangential to the curved surface at the leading edge of the intake fairing 10. The demarcation line D<SP>1</SP> is so drawn that normals to the surface of the fairing on this line will pass through the line D<SP>11</SP>.