FIELD: mechanical engineering; gas-turbine engines.
SUBSTANCE: proposed gas-turbine engine contains transition duct and compressor with guide working blades placed in passage part channel. Outer diameter of passage part channel is made variable-section, smoothly decreasing from first stages of compressor from side of intake to middle stages, and constant-section, from middle stages to last stages. Ratio of outer diameter over first working blade from side of its inlet edge to constant outer diameter over middle and last working blades is 1.1-1.25. Ratio of total number of stages of compressor to number of stages of compressor with constant outer diameter of working blades is 1.4-2.0. Ratio of heights of airfoil portions of first and last working blades of compressor is 4.5-7.5.
EFFECT: improved efficiency of gas-turbine engine owing to reduction of weight and axial length, decreased hydraulic losses.
3 dwg
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