Low emission, fixed geometry gas turbine combustor
AssigneeWestinghouse Electric Corp.
InventorsBoris M. Kramnik, Walter Kunc
Life of this patent
Estimating the term…
Abstract
A fixed geometry combustor for a gas turbine comprising at least one combustion chamber, a dilution chamber disposed downstream of said combustion chamber and in communication with said combustion chamber, at least one primary inspirator for introducing a fuel/air mixture into said combustion chamber in communication with said combustion chamber, and means for introducing dilution air into the dilution chamber.
Claims29
A process for combustion of a fuel in a gas turbine combustor comprising:
- mixing a fuel and combustion air, forming a fuel/air mixture whereby the amount of combustion air is adjusted in response to a load on said gas turbine without employing any moving parts external to said gas turbine so as to maintain about a constant total amount of air flowing into said combustor;
- introducing said fuel/air mixture into at least one combustion chamber of a fixed geometry combustor;
- introducing a dilution air into a dilution chamber of said fixed geometry combustor whereby the amount of dilution air is adjusted in response to said load on said gas turbine without employing any moving parts external to said gas turbine so as to maintain about a constant total amount of air flowing into said combustor, said dilution chamber disposed downstream of said at least one combustion chamber and in communication with said at least one combustion chamber;
- burning said fuel/air mixture in said fixed geometry combustor, forming products of combustion;
- mixing said combustion products with said dilution air in said dilution chamber;
- and
- exhausting said dilute combustion products into said gas turbine.
In a fixed geometry combustor for a gas turbine comprising at least one combustion chamber wall defining at least one combustion chamber having an upstream end and a downstream end, a dilution chamber wall defining a dilution chamber downstream of said at least one combustion chamber and in communication with said at least one combustion chamber, said dilution chamber having a dilution upstream end and a dilution downstream end, said dilution downstream end in communication with a gas turbine inlet, means for introducing a mixture of fuel and combustion air into said at least one combustion chamber, and means for introducing dilution air into said dilution chamber, the improvement comprising:
- said means for introducing said mixture of fuel and combustion air into said at least one combustion chamber and said means for introducing dilution air into said dilution chamber adjusting the amount of combustion air and dilution air introduced into said at least one combustion chamber and said dilution chamber, respectively, in response to changes in the load on said gas turbine without employing any moving parts external to said gas turbine so as to maintain about a constant total amount of air flowing into said combustor.
A fixed geometry combustor for a gas turbine comprising:
- at least one combustion chamber wall defining at least one combustion chamber having an upstream end and a downstream end;
- at least one dilution chamber wall defining a dilution chamber disposed downstream of said at least one combustion chamber and in communication with said at least one combustion chamber;
- combustion means for introducing a fuel/air mixture into said at least one combustion chamber;
- and
- dilution means for introducing dilution air into said dilution chamber, said combustion means and said dilution means adjusting the amount of combustion air and dilution air introduced into said at least one combustion chamber and said dilution chamber, respectively, in response to changes in the load on said gas turbine without employing any moving parts external to said gas turbine so as to maintain about a constant total amount of air flowing into said combustor.
Dependencies are inferred from the claim text.