Abstract A novel method for operating gas turbine combustors while minimizing the formation and discharge of pollutants such as NOx is described. In one embodiment, the use of more than one catalyst in series is employed to effect fuel oxidation at temperatures below flame temperature, thereby minimizing NOx formation. In another embodiment, a staged catalytic combustor is employed comprising a two zone combustion chamber involving a noncatalytic zone in which fuel is partially combusted under fuel rich conditions and combustion is completed in the second zone, utilizing catalytic oxidation with excess air to complete the combustion and minimize NOx formation. Still another embodiment concerns the use of a novel design for the primary combustion zone by which fuel is partially burned with substoichiometric amounts of air and, thereafter, the partially burned primary zone effluent is mixed into the secondary air stream where continued combustion proceeds at a temperature below that needed for NOx production. The operation of the primary zone under fuel rich conditions minimizes NOx formation, and the novel primary combustion zone design provides good mixing of the hot, partially burned primary zone effluent into the secondary air stream.
Inventors
👤 Henry Shaw
👤 Alvin Skopp
Bibliographic Details
Application Number—
JurisdictionUS
Data Sourcegoogle_patents
Last Synchronized2026-10-25 07:49
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/40
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
140 words
A method for combusting fuels in a gas turbine which comprises: (a) partially combusting fuel with air within an open cannular combustor located within a primary, non-catalytic section of the combustor of said gas turbine to form a hot, partially burned effluent which emanates from an opening in said cannular combustor, the amount of air present within said cannular combustor varying from 50 to 70% of the stoichiometric requirements for complete combustion of said fuel; (b) quenching said hot, partially burned effluent with additional air within said combustor without continued high temperature combustion, the amount of such additional air being sufficient to support the subsequent combustion of the partially burned fuel contained in said effluent; and (c) passing said quenched effluent over an oxidation catalyst at a temperature above the catalyst light-off temperature to complete the combustion of said fuel.
Claim 2
Independent Claim
140 words
A method for combusting fuels in a gas turbine which comprises: (a) partially combusting fuel with air within an open cannular combustor located within a primary, non-catalytic section of the combustor of said gas turbine to form a hot, partially burned effluent which emanates from an opening in said cannular combustor, the amount of air present within said cannular combustor varying from 50 to 70% of the stoichiometric requirements for complete combustion of said fuel; (b) quenching said hot, partially burned effluent with additional air within said combustor without continued high temperature combustion, the amount of such additional air being sufficient to support the subsequent combustion of the partially burned fuel contained in said effluent; and (c) passing said quenched effluent over an oxidation catalyst at a temperature above the catalyst light-off temperature to complete the combustion of said fuel.
Claim 3
Dependent Claim
15 words
The method of claim 1 wherein said open cannular combustor is a perforated cannular combustor.