FIELD: machine engineering.
SUBSTANCE: invention relates to a method of operating electric pump unit (EPU) for thermal control systems of aircraft and spacecraft. A method of operating EPU includes ensuring fluid circulation through the electric motor (EM) is hermetically separated from housings made of titanium. Circulation is provided in the following order: inlet, entry and exit of the right impeller, going to one of the conversion channel, the input and output of the left impeller going to another transfer channel outlet. The circulation is carried out with respect to the diaphragm with a tightly coupled its outer perimeter with a holder, for a sealed composite channels, one transfer channel operate in areas yoke and sleeves and connect them to the output of the right wheel of the working cavity and the entrance of the left wheel of the working cavity, another transfer channel is operated in areas of holder and EPU housing and connect them to the output of the working cavity of the left wheel and the outlet housing EPU. Compound EM stator housing and the aluminium pump body are performed through a sealed monolithic transition bimetallic rings, respectively, titanium and aluminium sides. EM rotor body cavity communicating with the cavity operate on wheels of liquid through the rotor bearings. EPU are symmetrically placed to a plane passing through the inlet, the outlet and ball-shaped check valve installed at the intersection of the translated output channels EPU outlet channel. The check valve is sprung from the outside surface of the outlet. EPU housing is operated as a single structure.
EFFECT: increase the reliability, efficiency of work of EPU, simplifying design, reducing weight and expanding the application.
2 cl, 1 dwg
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Authors
Dates
2017-05-11—Published
2015-09-04—Filed