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.

Date of Patent:
Feb. 10, 2026

Filed:

Feb. 09, 2024
Applicant:

Rtx Corporation, Farmington, CT (US);

Inventors:

Lawrence A. Binek, Glastonbury, CT (US);

Paul M. Lutjen, Kennebunkport, ME (US);

Jose R. Paulino, Jupiter, FL (US);

Robert B. Fowler, West Palm Beach, FL (US);

Assignee:

RTX CORPORATION, Farmington, CT (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 9/04 (2006.01); F01D 5/18 (2006.01); F15B 21/04 (2019.01); F15B 21/0423 (2019.01); F15B 21/0427 (2019.01); F23R 3/00 (2006.01); F23R 3/50 (2006.01);
U.S. Cl.
CPC ...
F01D 9/041 (2013.01); F01D 5/187 (2013.01); F15B 21/04 (2013.01); F15B 21/0423 (2019.01); F15B 21/0427 (2019.01); F23R 3/002 (2013.01); F23R 3/50 (2013.01); F05D 2240/35 (2013.01); F05D 2240/81 (2013.01); F23R 2900/00018 (2013.01);
Abstract

An assembly for a turbine engine includes a nozzle structure, a septum and a plurality of cooling vanes. The nozzle structure includes a first platform, a second platform and a plurality of nozzle vanes arranged circumferentially about an axis. The septum axially and circumferentially overlaps the first platform with a cooling cavity formed by and radially between the septum and the first platform. The septum includes a plurality of cooling apertures aligned with the nozzle vanes. Each of the cooling apertures extends radially through the septum to the cooling cavity. The cooling cavity includes a cavity outlet fluidly coupled to a flowpath. The cooling vanes are arranged circumferentially about the axis and project from the first platform into the cooling cavity. The cooling vanes are located between the cooling apertures and the cavity outlet along the cooling cavity.


Find Patent Forward Citations

Binek, Lawrence. (2026). Cooling nozzle vanes of a turbine engine (U.S. Patent No. 12546227). U.S. Patent and Trademark Office. https://idiyas.com/patent/badge/12546227

Data source: USPTO (United States Patent and Trademark Office) public patent records. Weekly synchronization. How IDiyas builds this profile

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