Cooling fluid bleed for axis of turbine rotor
AssigneeSociete Nationale d'Etude et de Construction de Moteurs d'Aviation
InventorsMichel R. Ayache, Jean-Claude L. Delonge, Daniel J. Marey
Life of this patent
Estimating the term…
Abstract
A device for moving air from the jet flow of an axial compressor of a gas rbine group, to be conducted along the axis of the group to the turbine to be cooled. The air is moved by a wheel having an outer rim serving as a brace between two adjacent compressor disks and centripetal blading which moves the air through openings formed in the rim, to accelerate it and discharge it into a space surrounding the axis of the compressor.
Claims3
In a device for moving air from the jet flow of an axial compressor for a gas turbine, said compressor having adjacent rotor disks, to be conducted along the axis of the turbine for cooling the same and including centripetal vanes in the form of spaced paddles extending radially between adjacent rotor disks, the improvement comprising:
- said paddles being part of a wheel between said disks and secured at its outer periphery to said disks to form a brace and torque transmitting member therebetween, said wheel including a central disk with said paddles extending axially from opposite sides thereof.
Dependencies are inferred from the claim text.