| 摘要 |
<p>An industrial gas turbine engine (10) rated for at least 75 MW maximum output including: a can annular combustion assembly (80); and a single rotor shaft (114); wherein a combustion section length (112) between a trailing edge (28) of a last row of compressor airfoils (20, 22) and a leading edge (54) of first row of turbine blades (56) is less than 20% of an engine length (154) between a leading edge (26) of a first row of compressor airfoils and a trailing edge (66) of a last row of turbine airfoils (60, 62).</p> |
