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:
Aug. 04, 2026
Filed:
Apr. 30, 2025
General Electric Company, Evendale, OH (US);
GE Avio S.r.l., Rivalta di Torino, IT;
Daniel Alan Niergarth, Norwood, OH (US);
Jorge De Luis, Cincinnati, OH (US);
Douglas Downey Turner, West Chester, OH (US);
Michael Macrorie, Winchester, MA (US);
Keith W. Wilkinson, Portsmouth, NH (US);
Arthur William Sibbach, Boxford, MA (US);
Vincenzo Martina, Turin, IT;
General Electric Company, Evendale, OH (US);
GE Avio S.r.l., Rivalta di Torino, IT;
Abstract
A gas turbine engine has a turbomachine comprising compressor, combustion, and turbine sections. The gas turbine engine defines a maximum exhaust gas temperature, a maximum drive turbine shaft torque, and a corrected specific power. The gas turbine engine includes a nozzle vane and an engine casing defining a fluid supply plenum. The engine casing is configured to route cooling fluid from the fluid supply plenum to the nozzle vane. The routing of the cooling fluid facilitates cooling of the nozzle vane and increases an overall pressure ratio of the gas turbine engine. Integration of the cooling fluid routing within the engine casing reduces parasitic bleed air losses, enables tighter turbine stage spacing, and improves the thermal efficiency of the engine, thereby enhancing performance at elevated pressure ratios.