Combustion apparatus
AssigneeThe Secretary of State for Defence in Her Britannic Majesty's Government of the United Kingdom of Great Britain and Northern Ireland
InventorsJohn Philip Dabbs Hakluytt, John Ronald Tilston
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Abstract
The present invention provides gas turbine reheat combustion apparatus for aircraft propulsion. The apparatus includes means for producing a flame stabilization zone in a stream of combustion supporting gas flowing in a duct, said stabilization zone having a recirculatory flow region therein, an injector for introducing a fluid comprising an inert diluent such as, for example, nitrogen, into the recirculatory flow region, and means for supplying the fluid to the injector.
Claims7
Combustion apparatus comprising a duct for conveying a stream of combustion supporting gas, means located within said duct providing a recirculatory flow of said gas which defines a flame stabilisation zone, and a source of fluid comprising an inert diluent connected to said duct for supplying said stabilisation zone with said inert diluent.
Combustion apparatus comprising a duct for conveying a stream of combustion supporting gas, a bluff body having a step change of section at the downstream end thereof, said body inducing a recirculatory flow of said gas which defines a flame stabilisation zone immediately downstream of said body, a fluid injector in said duct for introducing a fluid comprising an inert diluent into said stabilisation zone, and a source of said fluid connected to said injector.
Dependencies are inferred from the claim text.