CONTROLLED CONVERGENCE COMPRESSOR FLOWPATH FOR GAS TURBINE ENGINE Russian patent published in 2018 - IPC F01D5/00 F01D25/24 F04D29/52 

FIELD: machine building.

SUBSTANCE: controlled convergence compressor flowpath (10) configured to better distribute limited flowpath (10) within compressors (12) in turbine engines (14). Compressor (12) may have flowpath (10) defined by circumferentially extending inner and outer boundaries (16, 18) that have portions in which the rate of convergence changes to better distribute fluid flow therethrough. Rate of convergence may increase at surfaces (20, 22) adjacent to roots (24) of airfoils (26) and reduce convergence in axial gaps (28) between airfoil rows (30). In at least one embodiment, compressor flowpath (10) between leading and trailing edges (44, 46) of first compressor blade (42) may increase convergence moving downstream to trailing edge (46) of first compressor blade (42) due to increased convergence of inner compressor surface (22). Compressor flowpath (10) between leading and trailing edges (32, 34) of first compressor vane (36) immediately downstream from first compressor blade (42) may increase convergence moving downstream due to increased convergence of outer compressor surface (20).

EFFECT: reduced losses and higher efficiency.

15 cl, 2 dwg