Fuel injector for low emissions premixing gas turbine combustor
AssigneeHoneywell International Inc.
InventorIan L. Critchley
Life of this patent
Estimating the term…
Abstract
The present invention provides a premix fuel injector for use in gas turbine engines and in combustion systems having controllable pressure drops. The premix fuel injector comprises a premix chamber having an inlet for receiving a flow of pressurized air and having an exit. A venturi is coupled to the exit of the premix chamber and an inlet of a combustion chamber. Gaseous fuel is flowed into the premix chamber by a plurality of circumferentially disposed tubes extending into the premix chamber with each of said tubes having at least one hole for flowing a stream of the gaseous fuel.
Claims20
A premix fuel injector for injecting a mixture of gaseous fuel and air into a combustion chamber comprising:
- a premix chamber having an inlet for receiving a flow of pressurized air and having an exit;
- a venturi in fluid communication with said exit of said premix chamber and an inlet of said combustion chamber;
- and
- a fuel injector having a plurality of circumferentially disposed tubes extending into said premix chamber each of said tubes having at least one hole for flowing a stream of said gaseous fuel into said premix chamber.
A gas turbine engine comprising:
- a compressor providing pressurized air;
- a turbine for expanding a hot gas;
- a combustor disposed between said compressor and said turbine;
- said combustor comprising:
- a combustion chamber defined by a combustor wall;
- a plenum circumscribing said combustor wall and receiving said pressurized air from said compressor;
- a premix fuel injector for injecting a mixture of gaseous fuel and air into said combustion chamber, said premix fuel injector comprising:
- a premix chamber having an inlet for receiving a flow of pressurized air from said plenum and having an exit;
- a venturi in fluid communication with said exit of said premix chamber and an inlet of said combustion chamber;
- and a fuel injector having a plurality of circumferentially disposed tubes extending into said premix chamber each of said tubes having at least one hole for flowing a stream of said gaseous fuel into said premix chamber;
- an igniter disposed in said venturi for igniting said fuel and air mixture;
- a dilution zone just upstream of said turbine, said dilution zone receiving a portion of the air in said plenum through at least one dilution hole;
- and
- a bypass system for controlling the flow of the remaining portion of said air in said plenum to said injector and said dilution zone.
A combustion system with a controllable pressure drop thereacross, comprising:
- a combustion chamber defined by a combustor wall and having an inlet and an exit;
- a plenum circumferentially disposed about said combustor wall and receiving pressurized air;
- a premix fuel injector for injecting a mixture of gaseous fuel and air into said combustion chamber, said premix fuel injector comprising:
- a premix chamber having an inlet for receiving a flow of pressurized air from said plenum and having an exit;
- a venturi in fluid communication with said exit of said premix chamber and an inlet of said combustion chamber;
- and a fuel injector having a plurality of circumferentially disposed tubes extending into said premix chamber each of said tubes having at least one hole for flowing a stream of said gaseous fuel into said premix chamber;
- an igniter disposed in said venture for igniting said fuel and air mixture;
- a dilution zone just upstream of said exit, said dilution zone receiving a portion of the air in said plenum through at least one dilution hole in said combustor wall;
- and
- an adjustable bypass means for diverting to said dilution zone a portion of the air flowing from said plenum to said injector, whereby the magnitude of the diverted air can be varied to obtain a desired pressure drop across said combustion system.
Dependencies are inferred from the claim text.