Gas turbine
AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorVolker Dr. Guemmer
Life of this patent
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Abstract
A gas turbine with a compressor area has a rotor shaft 2 to carry rotor blades 1 and a casing 4 to carry stator vanes 3, with the related rotor blades 1 and stator vanes 3 forming an axial clearance space 5 between one another, wherein, in the area of the axial clearance space 5, at least one wall of the rotor shaft 2 and/or of the casing 4 is provided with an arrangement of fins 6 which are in-lined against the axial direction.
Claims33
A gas turbine with a compressor area which has a rotor shaft carrying rotor blades and a casing carrying stator vanes, with adjacent rotor blades and stator vanes forming an axial clearance space between one another, wherein, in the area of the axial clearance space, an arrangement of fins inclined against an axial direction of the gas turbine is provided on at least one of a wall of the rotor shaft and a wall of the casing.
A gas turbine in accordance with claim 31, wherein the inclination is within a range of ±25°.
Dependencies are inferred from the claim text.