ROTARY GEAR PUMP Russian patent published in 2015 - IPC F04D13/12 F04C11/00 

FIELD: engines and pumps.

SUBSTANCE: invention relates to pump incorporated with oil systems of gas turbine engines for supersonic aircraft flying at M>2.3 and altitude H>25 km. It differs from know designs in that the gear hub inner feed channels are arranged in two lines and inclined to gear rotation axis and provided with opposed intake holes. Intake holes of every said row of feed channels communicate with independent suction chambers in the body on both gear sides to communicate with pump inlet. Opposite row feed channel outlet holes communicate via common spaces between teeth. Suction and pressure chambers separators are fitted in the body on both sides of gears to overlap feed channel intake holes in contact with separator walls.

EFFECT: better pump altitude performances, higher pump efficiency at high gear rpm.

2 dwg