Horizontal type spatial multiphase crank pump

Abstract

The invention discloses a horizontal type spatial multiphase crank pump which comprises a bottom plate, an outer baffle plate, hydraulic cylinders, an inner baffle plate, two connecting rods, a secondcrank, a bearing pedestal, pistons, a first crank pin, a bearing transparent cover, a first crank, a second crank pin, a bearing end cover, a bearing, a third crank, a third crank pin, a motor rack and a motor. The horizontal type spatial multiphase crank pump has the following advantages: a sectional type crankshaft is adopted to drive the two connecting rods to move; and multiple groups of cylinder blocks work simultaneously to meet the long stroke requirement of the piston, realize large flow operation and greatly improve the overall performance of the pump. The three crank pins are distributed on the circumference in 120-degree phase difference; each of the crank pins drives the two connecting rods to move simultaneously; the pistons driven by the two connecting rods are in 180-degreephase difference; through flow superposition of the multiple cylinders, the pump is ensured to have smaller flow pulsation and liquid supply pressure; the six hydraulic cylinders adopt opposite horizontal type layout; and compared with the traditional reciprocating pump structure, the horizontal type spatial multiphase crank pump is more compact and stable in structure, so that the size and weight of the pump are reduced.

Description

technical field [0001] The invention belongs to the technical field of civil aviation special ground equipment, in particular to a horizontal space multi-phase crankshaft pump. Background technique [0002] In the severe cold and snowy weather in winter, when a civil aviation aircraft encounters supercooled water droplets or water vapor, it will gather on its surface to form an ice layer. Icing will damage the aerodynamic and flight characteristics of the aircraft, resulting in increased frictional resistance and pressure differential resistance, seriously affecting the normal flight of the aircraft. Therefore, in order to ensure flight safety and punctual release of the aircraft, it is a necessary task to de-ice the aircraft before take-off. [0003] Most of the reciprocating pumps used in the current deicing liquid supply system are single-crank linkages, which have low overall transmission efficiency, large volume and serious flow pulsation problems. During the working ...

AI Technical Summary

Problems solved by technology

[0003] Most of the reciprocating pumps used in the current deicing liquid supply system are single-crank linkages, which have low overall transmission efficiency, large volume and serious flow pulsation problems

During the working process, its fluid pressure fluctuations will cause wear and fatigue to the machine, which will cause the resonance of the whole system

In addition, fluid pulsation shock and resonance will also affect the service life of the machine and greatly increase the cost of maintenance

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