Gas turbine engine combustor can with trapped vortex cavity
June 11, 2022. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.Patent ReferencesAir fuel mixer for gas turbine combustor Dry low NOx single stage dual mode combustor construction for a gas turbine Low NOx combustor Dual fuel mixer for gas turbine combustor Cyclonic prechamber with a centerbody Dual fuel mixer for gas turbine combustor Air fuel mixer for gas turbine combustor Air fuel mixer for gas turbine combustor High inlet mach combustor for gas turbine engine Dual fuel mixer for gas turbine combustor InventorsApplicationNo. 10166960 filed on 06/11/2002US Classes:60/746, Plural distinct injectors60/750Having means to recycle combustion products internally of combustion zoneExaminersPrimary: Casaregola, Louis J.Attorney, Agent or FirmInternational ClassF02C 358AbstractA gas turbine engine combustor can downstream of a pre-mixer has a pre-mixer flowpath therein and circumferentially spaced apart swirling vanes disposed across the pre-mixer flowpath. A primary fuel injector is positioned for injecting fuel into the pre-mixer flowpath. A combustion chamber surrounded by an annular combustor liner disposed in supply flow communication with the pre-mixer. An annular trapped dual vortex cavity located at an upstream end of the combustor liner is defined between an annular aft wall, an annular forward wall, and a circular radially outer wall formed therebetween. A cavity opening at a radially inner end of the cavity is spaced apart from the radially outer wall. Air injection first holes are disposed through the forward wall and air injection second holes are disposed through the aft wall. Fuel injection holes are disposed through at least one of the forward and aft walls. | |
