GAS TURBINE ENGINE WITH A RADIAL DIFFUSER AND A SHORT-TERM MEDIUM PART

摘要

FIELD: engines and pumps.;SUBSTANCE: industrial gas turbine engine (10) includes: a block (80) of tubular annular combustion chambers having a plurality of separate flow channels configured to receive combustion gas from respective combustion chambers (82) and supply gaseous products combustion along a straight flow path with speed and orientation suitable for supplying directly to the first row (56) turbine blades (62); and a compressor diffuser (32) having a change direction surface (130, 140) configured to receive an axial flow of compressed air and change the direction of the axial flow of compressed air radially outward.;EFFECT: ensuring the possibility of using a shorter rotor shaft and improving aerodynamics in shorter gas turbine engines.;20 cl, 7 dwg