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

Abstract

A gas turbine including 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, and a third radial wall formed about the outer radial wall that forms an outer 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 corresponding to the aftward annulus section and a forward intake section corresponding to the forward annulus section. The air directing structure may include a switchback coolant flowpath to direct air from the compressor discharge cavity to the staged injector. The switchback coolant flowpath may include an upstream section through the flow annulus, and a downstream section through the outer flow annulus.

Inventors:
;
Issue Date:
Research Org.:
General Electric Company, Schenectady, NY (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1434521
Patent Number(s):
9,938,903
Application Number:
14/978,019
Assignee:
General Electric Company (Schenectady, NY) NETL
DOE Contract Number:  
FC26-05NT42643
Resource Type:
Patent
Resource Relation:
Patent File Date: 2015 Dec 22
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Hughes, Michael John, and Berry, Jonathan Dwight. Staged fuel and air injection in combustion systems of gas turbines. United States: N. p., 2018. Web.
Hughes, Michael John, & Berry, Jonathan Dwight. Staged fuel and air injection in combustion systems of gas turbines. United States.
Hughes, Michael John, and Berry, Jonathan Dwight. Tue . "Staged fuel and air injection in combustion systems of gas turbines". United States. https://www.osti.gov/servlets/purl/1434521.
@article{osti_1434521,
title = {Staged fuel and air injection in combustion systems of gas turbines},
author = {Hughes, Michael John and Berry, Jonathan Dwight},
abstractNote = {A gas turbine including 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, and a third radial wall formed about the outer radial wall that forms an outer 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 corresponding to the aftward annulus section and a forward intake section corresponding to the forward annulus section. The air directing structure may include a switchback coolant flowpath to direct air from the compressor discharge cavity to the staged injector. The switchback coolant flowpath may include an upstream section through the flow annulus, and a downstream section through the outer flow annulus.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2018},
month = {4}
}

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