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. 28, 2023

Filed:

Jul. 02, 2021
Applicant:

Hamilton Sundstrand Corporation, Charlotte, NC (US);

Inventors:

Zhongtao Dai, West Hartford, CT (US);

Ram Ranjan, West Hartford, CT (US);

Robert H. Dold, Monson, MA (US);

Assignee:

Hamilton Sundstrand Corporation, Charlotte, NC (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F01D 5/18 (2006.01); B33Y 80/00 (2015.01); F01D 25/12 (2006.01); B33Y 10/00 (2015.01);
U.S. Cl.
CPC ...
F01D 5/187 (2013.01); B33Y 80/00 (2014.12); F01D 5/186 (2013.01); B33Y 10/00 (2014.12); F01D 25/12 (2013.01); F05D 2230/31 (2013.01); F05D 2260/202 (2013.01); F05D 2260/2212 (2013.01);
Abstract

A turbine rotor includes a base and a plurality of blades. The base and the blades curve such that radially outward portions of the base and the blades extend in a direction with a greater component in a radial direction than in an axial direction. Radially central portions of the base and the blade extend in a direction with the two components being closer. Radially inner sections of the base and the blades extend in a direction with a greater component in the axial direction than in a radial direction. There is a cooling channel arrangement in the turbine rotor. The cooling channel arrangement includes impingement cooling for a nose and serpentine passages for cooling sections of the platform circumferentially intermediate the blades, and distinct serpentine passages for cooling the plurality of blades. A turbomachine and method are also disclosed.


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