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. 07, 2018

Filed:

Mar. 29, 2011
Applicants:

Vijay Anand Raghavendran Nenmeni, Atlanta, GA (US);

Michael Joseph Alexander, Simpsonville, SC (US);

Paul William Plummer, Houston, TX (US);

Timothy Lee Janssen, Ballston Lake, NY (US);

Inventors:

Vijay Anand Raghavendran Nenmeni, Atlanta, GA (US);

Michael Joseph Alexander, Simpsonville, SC (US);

Paul William Plummer, Houston, TX (US);

Timothy Lee Janssen, Ballston Lake, NY (US);

Assignee:

General Electric Company, Schenectady, NY (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F02C 6/08 (2006.01); F01D 13/00 (2006.01); F02C 9/18 (2006.01);
U.S. Cl.
CPC ...
F02C 6/08 (2013.01); F01D 13/00 (2013.01); F02C 9/18 (2013.01); F05D 2260/80 (2013.01); F05D 2270/301 (2013.01); F05D 2270/3061 (2013.01);
Abstract

The disclosed embodiments relate to a system and method that allows air to be extracted from a plurality of gas turbine engines and fed to a downstream process, even in situations in which one or more of the gas turbine engines are operating in a part load condition. For example, in an embodiment, a method includes monitoring signals representative of a header pressure of a header, or a pressure of extraction air flow from one or more gas turbine engines to the header, or both, and maintaining substantially continuous flows of extraction air from the gas turbine engines to the header. The substantially continuous flows are maintained when the gas turbine engines are under symmetric and asymmetric load conditions.


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