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:
Mar. 17, 2020

Filed:

May. 03, 2016
Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Ronald Scott Bunker, West Chester, OH (US);

Robert Charles Groves, II, West Chester, OH (US);

Assignee:

General Electric Company, Schenectady, NY (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F01D 9/06 (2006.01); F01D 5/18 (2006.01); F01D 25/14 (2006.01); F01D 9/04 (2006.01); F01D 25/12 (2006.01); F01D 25/24 (2006.01);
U.S. Cl.
CPC ...
F01D 9/065 (2013.01); F01D 5/18 (2013.01); F01D 5/187 (2013.01); F01D 9/041 (2013.01); F01D 9/048 (2013.01); F01D 25/12 (2013.01); F01D 25/14 (2013.01); F01D 25/24 (2013.01); F05D 2220/32 (2013.01); F05D 2240/12 (2013.01); F05D 2240/30 (2013.01); F05D 2240/307 (2013.01); F05D 2260/205 (2013.01); F05D 2260/213 (2013.01); F05D 2300/6033 (2013.01); Y02T 50/676 (2013.01);
Abstract

A method for cooling a component of a gas turbine engine includes flowing a cooling airflow through a cooling passage of a turbine rotor blade, wherein the cooling passage includes an inlet and an outlet formed on a blade tip of the turbine rotor blade. The method further includes receiving at least a portion of the cooling airflow exiting the outlet of the cooling passage with an aperture defined in a casing of the gas turbine engine, wherein the casing is spaced from the blade tip along the radial direction. In addition, the method includes providing the cooling airflow received with the aperture defined in the casing to the component of the gas turbine engine through a coolant duct assembly of the gas turbine engine.


Find Patent Forward Citations

Bunker, Ronald. (2020). System and method for cooling components of a gas turbine engine (U.S. Patent No. 10590786). U.S. Patent and Trademark Office. https://idiyas.com/patent/badge/10590786

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

Loading…