Dilution pole combustor and method
A gas turbine engine annular combustor having a longitudinal centerline axis, outer and inner annular liners is described spaced radially apart coaxially about the centerline axis to define an annular combustion chamber there between, an annular dome at upstream ends of the liners having a plurality of circumferentially spaced apart carburetors for providing a fuel/air mixture into the combustion chamber to generate combustion gases therein, and an annular outlet defined at downstream ends of the liners for discharging the combustion gases, a method comprising: channeling the fuel/air mixture axially through the dome into the combustion chamber to generate the combustion gases; blocking flow of the combustion gases at a plurality of circumferentially spaced apart locations at an axial position spaced axially downstream from the dome and spaced axially upstream from the outlet to define an intermediate zone disposed axially between a forward zone extending upstream therefrom to the dome, and an aft zone extending downstream therefrom to the outlet, and radially between the outer and inner liners to accelerate the combustion gases between the blocking locations in a plurality of circumferentially spaced apart throats; injecting dilution air into the combustion gases being channeled through the throats and radially between the outer and inner liners channeling the combustion gases through the forward zone with a rich equivalence ratio; and wherein the injecting step mixes the dilution air with the combustion gases being channeled through the throats to quench the combustion gases channeled to the aft zone to a lean equivalence ratio.
- Assignee:
- General Electric Co., Cincinnati, OH (United States)
- Patent Number(s):
- US 5239818; A
- Application Number:
- PPN: US 7-860635
- OSTI ID:
- 6156070
- Resource Relation:
- Patent File Date: 30 Mar 1992
- Country of Publication:
- United States
- Language:
- English
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