Diffuser for gas turbine system between compressor exit and combustor inlet

摘要

A diffuser (20) for a gas turbine system (10) having a longitudinal axis (90) is disclosed. The diffuser (20) includes a plurality of diffuser ducts (30). Each of the plurality of diffuser ducts (30) is disposed annularly about the longitudinal axis (90) and has an inlet (32), an outlet (36), and a passage (34) extending between the inlet (32) and the outlet (36). The outlet (36) of each of the plurality of diffuser ducts (30) is tangentially offset from the inlet (32) of the respective diffuser duct (30). Each of the plurality of diffuser ducts (30) is configured to flow a gas flow (80) therethrough, reducing the gas flow (80) velocity.