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Title: Staged fuel and air injection in combustion systems of gas turbines

Patent ·
OSTI ID:1435769
;

A gas turbine that includes a working fluid flowpath extending aftward from a forward injector in a combustor. The combustor may include an inner radial wall, an outer radial wall, and, therebetween, a flow annulus. A staged injector may intersect the flow annulus so to attain an injection point within the working fluid flowpath by which aftward and forward annulus sections are defined. Air directing structure may include an aftward intake section that corresponds to the aftward annulus section and a forward intake section that corresponds to the forward annulus section. The air directing structure may be configured to: direct air entering through the aftward intake section through the aftward annulus section in a forward direction to the staged injector; and direct air entering through the forward intake section through the forward annulus section in a forward direction to the forward injector.

Research Organization:
General Electric Co., Schenectady, NY (United States)
Sponsoring Organization:
USDOE
DOE Contract Number:
FC26-05NT42643
Assignee:
General Electric Company (Schenectady, NY)
Patent Number(s):
9,945,294
Application Number:
14/978,006
OSTI ID:
1435769
Resource Relation:
Patent File Date: 2015 Dec 22
Country of Publication:
United States
Language:
English

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Assemblies and apparatus related to integrating late lean injection into combustion turbine engines patent December 2014
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System for supplying a working fluid to a combustor patent July 2013
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Gas Turbine Combustor patent-application July 2014
Late Lean Injection Control Strategy patent-application July 2010
System for Controlling a Flow Rate of a Compressed Working Fluid to a Combustor Fuel Injector patent-application September 2014
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