FIELD: pumps.
SUBSTANCE: invention relates to pump engineering and can be used in pumps of aircraft and liquid-propellant rocket engines. Blade pump comprises housing (1), feed (2), impeller (4) with cover disc (7), non-contact seal (8) located on cover disk (7), annular cavity (9) at outlet of seal (8). Annular cavity (9) is connected to pump inlet (2) by bypass channels (10) made in supply (2), and is made on the side of supply (2) directly in its body.
EFFECT: invention is aimed at improving reliability and simplifying the design of the vane pump.
5 cl, 3 dwg
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Authors
Dates
2020-09-04—Published
2019-03-26—Filed