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:
Nov. 19, 2019

Filed:

Mar. 02, 2016
Applicants:

General Electric Company, Schenectady, NY (US);

Exxonmobil Upstream Research Company, Spring, TX (US);

Inventors:

Ilya Aleksandrovich Slobodyanskiy, Simpsonville, SC (US);

Igor Petrovich Sidko, Moscow, RU;

Derrick Walter Simons, Greer, SC (US);

Assignees:

General Electric Company, Schenectady, NY (US);

ExxonMobil Upstream Research Company, Spring, TX (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F23R 3/34 (2006.01); F23R 3/28 (2006.01); F02C 3/14 (2006.01); F02C 7/22 (2006.01); F02C 9/26 (2006.01); F23L 7/00 (2006.01); F23N 1/02 (2006.01); F23N 5/00 (2006.01); F02C 3/34 (2006.01); F02C 9/28 (2006.01); F23R 3/00 (2006.01);
U.S. Cl.
CPC ...
F23R 3/286 (2013.01); F02C 3/34 (2013.01); F02C 9/26 (2013.01); F23L 7/00 (2013.01); F23N 1/022 (2013.01); F23N 5/003 (2013.01); F23R 3/346 (2013.01); F02C 7/222 (2013.01); F02C 9/28 (2013.01); F05D 2270/31 (2013.01); F23L 2900/07002 (2013.01); F23L 2900/07003 (2013.01); F23R 3/002 (2013.01); F23R 3/283 (2013.01); F23R 3/34 (2013.01); Y02E 20/16 (2013.01); Y02T 50/677 (2013.01);
Abstract

A gas turbine system includes a turbine combustor. The turbine combustor includes one or more first fuel injectors coupled to a head end of the turbine combustor and configured to deliver a first portion of a fuel to a first axial position of a combustion section of the turbine combustor. The turbine combustor also includes one or more second fuel injectors coupled to the turbine combustor axially downstream of the head end and configured to deliver a second portion of the fuel to a second axial position of the combustion section of the turbine combustor, the second axial position being downstream of the first axial position. The gas turbine system also includes a controller configured to deliver the first and the second portions of the fuel such that combustion of the fuel and oxidant within the overall combustion section of the turbine combustor is at a defined equivalence ratio.


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