System for Coupling Flow from a Centrifugal Compressor to an Axial Combustor for Gas Turbines

摘要

A system is provided for aerodynamically coupling air flow from a centrifugal compressor (200) to an axial combustor (202). The system includes a diffuser (204), a deswirl assembly (206), combustor inner and outer annular liners (226, 228), a combustor dome (230), and a curved annular plate (244). The diffuser (204) has an inlet (214) that communicates with the centrifugal compressor (200), an outlet (216), and a flow path (218) that extends radially outward. The deswirl assembly (206) has an inlet (220) that communicates with the diffuser outlet (216) to receive air flowing in a radially outward direction, an outlet (222), and a flow path (224) configured to redirect the air in a radially inward and axial direction through the deswirl assembly outlet (222) at an angle toward a longitudinal axis (207). The curved annular plate (244) is coupled to combustor inner and outer annular liner upstream ends (234, 238) to form a combustor subplenum (241) therebetween and has a first opening (250) and a second opening (252) formed therein, the first opening (250) aligned with the deswirl assembly outlet (222) to receive air discharged therefrom.