FLUID COOLED ROTOR FOR A GAS TURBINE
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United States of America Patent
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Aug 10, 2017
app pub date -
Feb 9, 2017
filing date -
Feb 9, 2016
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Abstract
The present disclosure relates to a rotor for a gas turbine having a plurality of rotor disks arranged one behind the other in a rotor axis and connected to one another, where the geometrical form of the disks leads to the formation of cavities between adjacent disks. The rotor extends from a compressor part to a turbine part and has a central part between the compressor part and the turbine part, wherein the first turbine disk, the last compressor disk and the central part enclose a central cavity. A cooling system extends at least partially through the rotor with a central cooling section disposed between at least one inlet pipe and at least one outlet pipe, at least partially through the first turbine disk and/or the last compressor disk.
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