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
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