Device for cooling and gas turbine rotor
AssigneeSociete National d'Etude et de Construction de Moterus d'Aviation S.N.E.C.M.A.
InventorsAndre M. Barbot, Jacques E. J. Caruel, Marcel R. Soligny
Life of this patent
Estimating the term…
Abstract
This device embodies a centrifugal compressor secured to a joint-carrier disk secured to an upstream flange of the rotor disk to be cooled. The recompressed air is ejected through channels near the roots of the blades of the disk.
Claims11
A device for cooling the rotor of a gas turbine rotatable about a rotor axis, the gas turbine having a compressor, with relatively low pressure air taken from the compressor and supplied to the turbine through a common shaft, said device including means for compressing the cooling air comprising a disk forming an airtight circuit integral and rotatable with the rotor, the disk having an air intake adjacent to the rotor axis and cooling air ejection orifices, the airtight circuit communicating with the air intake and ejection orifices without a discontinuity for directing air to parts to be cooled while compressing the air, the disk further comprising a labyrinth joint, and being secured to an annular flange of the rotor on one side of the rotor, wherein the airtight circuit comprises radial passages inside the disk.
A device for cooling the rotor of a gas turbine, the rotor having front and rear faces and being rotatable about a rotor axis, the gas turbine having a compressor, with relatively low pressure air taken from the compressor and supplied to the turbine through a common shaft, said device including means for compressing the cooling air comprising a disk forming an airtight circuit integral and rotatable with the rotor, the disk having an air intake adjacent to the rotor axis and cooling air ejection orifices, the airtight circuit communicating with the air intake and ejection orifices without a discontinuity, for directing air to parts to be cooled while compressing the air wherein the airtight circuit includes an impeller mounted on the outside of and integral with the rotor, inlets to the impeller being located adjacent to a central axial bore of the rotor, outlets terminating in radial passages arranged, on the outside of and integral with the rotor in a radial plane of the rotor, the radial passages each having a transverse section that decreases in a direction away from its inlet and, wherein the impeller and the radial passages are arranged spaced from the rear face of the rotor, the cooling air flowing through the central bore of the rotor from front to rear before entering the impeller.
Dependencies are inferred from the claim text.