Patent ID: 8776525

Claim:
A gas turbine engine, comprising: a compressor; a turbine; and a combustion system in fluid communication with the compressor and the turbine, wherein the combustion system includes a slinger injector and a single-sided recirculation combustor configured to generate a primary combustion zone having a recirculation vortex within the single-sided recirculation combustor, wherein the single-sided recirculation combustor includes a tubular compressor discharge air injector having an inlet exposed to the total pressure of the air exiting the compressor, and wherein the compressor discharge air injector is configured to discharge pressurized air into the recirculation vortex; and wherein the single-sided recirculation combustor includes an air scoop disposed downstream of the tubular compressor discharge air injector, and wherein the air scoop is configured to confine the vortex.