GAS TURBINE ENGINE WITH RADIAL DIFFUSER AND SHORTENED MID SECTION

摘要

An industrial gas turbine engine (10) including: a can annular combustion assembly (80) having a plurality of discrete flow ducts configured to receive combustion gas from respective combustors (82) and deliver the combustion gas along a straight flow path at a speed and orientation appropriate for delivery directly onto the first row (56) of turbine blades (62); and a compressor diffuser (32) having a redirecting surface (130 140) configured to receive an axial flow of compressed air and redirect the axial flow of compressed air radially outward