Gas turbine engine system and an associated method thereof

摘要

A gas turbine engine system includes a compressor, a combustor, and a turbine. The combustor is coupled to the compressor and disposed downstream of the compressor. The combustor includes a secondary combustor section coupled to a primary combustor section and disposed downstream of the primary combustor section. The combustor also includes a transition nozzle coupled to the secondary combustor section and disposed downstream of the secondary combustor section. The combustor further includes an injector coupled to the secondary combustor section, for injecting an air-fuel mixture to the secondary combustor section. The turbine is coupled to the combustor and disposed downstream of the transition nozzle; wherein the transition nozzle is oriented substantially tangential to the turbine.

主权项

1. A gas turbine engine system, comprising:
a compressor, a combustor coupled to the compressor and disposed downstream of the compressor; wherein the combustor comprises:
a primary combustor section;a secondary combustor section coupled to the primary combustor section and disposed downstream of the primary combustor section;a transition nozzle coupled to the secondary combustor section and disposed downstream of the secondary combustor section;an injector coupled to the secondary combustor section for injecting an air-fuel mixture to the secondary combustor section; andan inlet of a turbine coupled to the combustor and disposed downstream of the transition nozzle; wherein an exit of the transition nozzle is oriented substantially tangentially to a circumference of the inlet of the turbine.