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AssigneeGeneral Electric Company
InventorsArmando J. Quinones, Harold P. Rieck, Jr., Richard W. Albrecht, Michael A. Sullivan, Robert H. Weisgerber, Larry W. Plemmons
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A turbine disk cooling system for a gas turbine engine of a type having a compressor section including first and second disks connected by a seal and defining a compressor interstage volume, a turbine section including first and second stage disks connected by a seal and defining a turbine inner stage volume, and a compressor shaft interconnecting the compressor disks with the turbine disks including orifices located in the compressor seal for allowing air in the compressor section to enter the compressor interstage volume, and a radial inflow impeller for guiding the compressor air towards the compressor shaft. The impeller including a plurality of radially-extending conduits suspended in the compressor interstage volume, the conduits having a plurality of interior, radially-extending passages for conveying the compressor air from the orifice to the compressor shaft. The cooling system further including ducts concentric with the engine centerline for conveying air from the compressor interstage volume to the turbine section, wherein the first stage turbine disk includes an aft shaft having a plurality of openings therethrough allowing the flow of air from the ducts into the turbine interstage volume. The tubular conduit elements having a radially outer portion divided into a plurality of spaced longitudinal segments and a radially inner portion protruding from the conduit element and including a peripheral flange shaped to engage the peripheral flange of the conduit elements.
In a gas turbine engine of a type having a compressor section including first and second disks connected by a seal defining a compressor interstage volume, a turbine section including first and second stage disks connected by (a) an interstage seal defining a turbine interstage volume, and a compressor shaft interconnecting said compressor disks with said turbine disks, a turbine disk cooling system comprising:
In a gas turbine engine of a type having a compressor section including first and second disks connected by a seal defining a compressor interstage volume, a turbine section including first and second stage disks connected by a seal defining a turbine interstage volume, and a compressor shaft interconnecting said compressor disks with said turbine disks, a turbine disk cooling system comprising:
Dependencies are inferred from the claim text.