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US 4,415,310 AGranted
System for cooling a gas turbine by bleeding air from the compressor
AssigneeSociete Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."
InventorsJean G. Bouiller, Francois E. G. Crozet, Marcel R. Soligny
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Abstract
A system for cooling a gas turbine by bleeding air from the compressor and channeling the air at the center of the engine towards the turbine in order to cool it. The air is bled from the plane of the disc bearing the blades of the compressor, said disc having radial ducts for the flow of the air. The invention is utilized in gas turbine engines to cool the turbine.
Claims5
A system of bleeding air from a compressor for cooling a gas turbine element having at least one compressor blade bearing disc, said system comprising:
- at least one radial duct in each said disc, each said duct extending in the plane of a respective at least one said disc to the radially outer periphery thereof;
- platforms associated with said compressor blades and covering at least a portion of the radially outer periphery of each said disc;
- and
- ports formed in said platforms for each said at least one radial duct, wherein said ports are elliptical in cross section, the large axis of each said elliptical shape being perpendicular to the overall flow of fluid in said turbine, whereby air is channeled through said ports and said radial ducts into the center of said gas turbine towards said turbine element.
1 more element
Dependencies are inferred from the claim text.