Thermoelectric electro-magnetic pump design for the SP-100 reference flight system

Author

Zarghami, F.M. ; Atwell, J.C. ; Salamah, S.A. ; Sinha, U.N.

Author_Institution

GE Astro Space Div., San Jose, CA, USA

fYear

1989

fDate

6-11 Aug 1989

Firstpage

1227

Abstract

The design of the thermoelectric electromagnetic (TEM) pump used in the SP-100 space power system is described. The TEM pump is designed to pump liquid (molten) lithium (Li) coolant in the primary heat transport subsystem and heat rejection subsystem. The pump utilizes advanced thermoelectric cells to generate electric current that induces magnetic flux in a Z-shaped magnetic structure. The electric current and magnetic flux pass through the liquid Li perpendicular to each other to create the pumping force. The design provides a minimum-mass, self-regulated pump that has no moving parts and is self-powered by an internal temperature gradient

Keywords

electromagnetic devices; pumps; space vehicle power plants; thermoelectric conversion; Li coolant; SP-100 space power system; TEM pump; Z-shaped magnetic structure; advanced thermoelectric cells; electric current generation; heat rejection subsystem; internal temperature gradient; magnetic flux; primary heat transport subsystem; reference flight system; self-regulated pump; thermoelectric electromagnetic pump; Ducts; Heat pumps; Heat sinks; Inductors; Lithium; Magnetic fields; Magnetic flux; Space heating; Temperature; Thermoelectricity;

fLanguage

English

Publisher

ieee

Conference_Titel

Energy Conversion Engineering Conference, 1989. IECEC-89., Proceedings of the 24th Intersociety

Conference_Location

Washington, DC

Type

conf

DOI

10.1109/IECEC.1989.74625

Filename

74625