The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.
The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.
Patent No.:
Date of Patent:
Dec. 05, 1995
Filed:
Jun. 23, 1994
Armando J Quinones, Cincinnati, OH (US);
Harold P Rieck, Jr, West Chester, OH (US);
Richard W Albrecht, Fairfield, OH (US);
Michael A Sullivan, Ballston Spa, NY (US);
Robert H Weisgerber, Loveland, OH (US);
Larry W Plemmons, Fairfield, OH (US);
General Electric Company, Cincinnati, OH (US);
Abstract
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.