GAS TURBINE ENGINE BYPASS CHANNEL, CONTAINING CHANNEL CLOSURE GRATE WITH DIFFERENT MOUNTING ANGLES Russian patent published in 2020 - IPC F02C9/18 F04D27/02 

FIELD: engine building.

SUBSTANCE: internal housing (2) of intermediate housing (1) of double-flow gas turbine engine. Bypass blades (20) are fixed in channel (18) of bypass passage at level of outlet hole (6) of external shell (5). At that, said bypass blades (20) include from the inlet to the outlet in the direction of the air flow passage in the second loop flow space (14) the upper upstream blade (22), which is located near upstream wall (18a) of the bypass passage channel (18) and which comprises the front edge (BA) located in opposition to the air flow (F18) in the bypass passage channel (18), and the middle line (C) and the lower flow blade (24), which is located next to downstream wall (18b) of channel (18) of bypass passage and which comprises front edge (BA) and middle line (C). At that, inner housing (2) of intermediate housing differs by the fact that upper upstream acute angle (α_{upper flow}) between bypass plane (P) and tangent line (T) to middle line (C) at the level of leading edge (BA) of upstream blades (22) smaller than downstream acute angle (α_{lower flow}) between bypass plane (P) and tangent line (T) to midline (C) at level of leading edge (BA) of downstream blade (24).

EFFECT: higher capacity of bypass valves of double-flow gas turbine engine and reduced risks of secondary circuit flow disruption or recirculation in flow path of gas turbine engine second circuit.

10 cl, 4 dwg