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.

Patent No.:

US 10329945 B1

PDF
Full Text
Expired
Date of Patent:
Jun. 25, 2019

Filed:

Apr. 21, 2015
Applicant:

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

Inventors:

Anil L. Salunkhe, Charlotte, NC (US);

Bogdan R. Raica, Oviedo, FL (US);

Christian K. Funk, Charlotte, NC (US);

Assignee:

SIEMENS ENERGY, INC., Orlando, FL (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F02C 6/08 (2006.01); F02K 1/12 (2006.01); F02K 1/16 (2006.01); F01D 17/14 (2006.01); F01D 25/24 (2006.01); F01D 25/30 (2006.01); F04D 29/56 (2006.01); F04D 29/68 (2006.01);
U.S. Cl.
CPC ...
F01D 17/14 (2013.01); F01D 17/141 (2013.01); F04D 29/563 (2013.01); F01D 25/24 (2013.01); F01D 25/30 (2013.01); F02C 6/08 (2013.01); F02K 1/12 (2013.01); F02K 1/16 (2013.01); F04D 29/681 (2013.01);
Abstract

An exhaust gas diffuser for a gas turbine engine whose inlet geometry can be selectively controlled to change the angular orientation of the diffuser at the location where the exhaust gas exits the last stage row of blades of the turbine section of the gas turbine engine. An end portion of the gas diffuser proximate the last stage row of blades can include one or more actuated sections that are independently controlled to change the angular orientation of the inlet geometry of the diffuser. In one embodiment, the angular orientation of the actuated sections is set at the manufacturing level for the service location of the engine. In another embodiment, the angular orientation of the actuated sections is selectively controlled based on the operating conditions of the engine. In another embodiment, the angular orientation of the actuated sections is controlled by pneumatic pressure from a compressor section of the engine.


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