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:
Apr. 30, 2019

Filed:

Dec. 18, 2015
Applicant:

Pratt & Whitney Canada Corp., Longueuil, CA;

Inventors:

Roger Huppe, Chambly, CA;

Marc Tardif, Candiac, CA;

Herve Turcotte, Sainte-Julie, CA;

Assignee:

Pratt & Whitney Canada Corp., Longueuil, Quebec, CA;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 9/06 (2006.01); F01D 5/18 (2006.01); F01D 25/12 (2006.01); F02C 3/04 (2006.01); F01D 5/08 (2006.01); F02C 7/18 (2006.01);
U.S. Cl.
CPC ...
F01D 5/187 (2013.01); F01D 5/081 (2013.01); F01D 9/065 (2013.01); F01D 25/12 (2013.01); F02C 3/04 (2013.01); F02C 7/18 (2013.01); F05D 2220/32 (2013.01); F05D 2260/231 (2013.01);
Abstract

An air supply system is configured to provide cooling air with reduced heat pickup to a turbine rotor of a gas turbine engine. The system comprises a first cooling passage extending between a hollow airfoil and an internal pipe extending through the airfoil. The airfoil extends through a hot gas path. A second cooling passage extends through the internal pipe. The coolant flowing through the second cooling passage is thermally isolated from the airfoil hot surface by the flow of coolant flowing through the first cooling passage. The first and second cooling passages have a common output flow to a rotor cavity of the turbine rotor where coolant flows from the first and second cooling passages combine according to a predetermined ratio.


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