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:
Aug. 11, 2015

Filed:

Oct. 20, 2011
Applicants:

Richard Charron, West Palm Beach, FL (US);

Daniel Pierce, Port St. Lucie, FL (US);

Inventors:

Richard Charron, West Palm Beach, FL (US);

Daniel Pierce, Port St. Lucie, FL (US);

Assignee:

Siemens Energy, Inc., Orlando, FL (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F01D 5/08 (2006.01); F01D 25/08 (2006.01); F02C 7/12 (2006.01); F02C 7/20 (2006.01); F02C 7/36 (2006.01);
U.S. Cl.
CPC ...
F02C 7/12 (2013.01); F01D 5/08 (2013.01); F01D 25/08 (2013.01); F02C 7/20 (2013.01); F02C 7/36 (2013.01);
Abstract

A shaft cover support for a gas turbine engine is disclosed. The shaft cover support not only provides enhanced support to a shaft cover of the gas turbine engine, but also includes a cooling fluid chamber for passing fluids from a rotor air cooling supply conduit to an inner ring cooling manifold. Furthermore, the shaft cover support may include a cooling shield supply extending from the cooling fluid chamber between the radially outward inlet and the radially inward outlet on the radially extending region and in fluid communication with the cooling fluid chamber for providing cooling fluids to a transition section. The shaft cover support may also provide additional stiffness and reduce interference of the flow from the compressor. In addition, the shaft cover support accommodates a transition section extending between compressor and turbine sections of the gas turbine engine.


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