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Title: Heat exchanger for electrothermal devices

Abstract

A heat exchanger is described for heating a gaseous propellant to a temperature between about 200/sup 0/C and about 2200/sup 0/C in an electrothermal thruster having a nozzle comprising a hollow housing forming a cylindrical chamber adjacent to the nozzle, the hollow housing having a textured inner surface to provide high absorptivity and an oppositely disposed textured outer surface to provide high emissivity, an outer housing surrounding the cylindrical chamber in spaced relationship thereto thereby forming an annular chamber for conducting the gaseous propellant to the nozzle, a porous heat exchanger material selected from the group consisting of refractories, ceramics, and cermets contained within the annular chamber, housing a wire coiled about the outer surface of the hollow housing in engagement with the outer housing for providing a lengthened spiral flow path for the propellant to the annular chamber, an electrical heating comprising a coiled tube having a wall thickness of about 0.25 mm and a textured surface for providing high emissivity mounted within the cylindrical chamber in spaced relationship with the textured inner surface for radiatively heating the hollow housing and heat exchanger material without contacting the gaseous propellant, means for supplying a gaseous propellant to the lengthened spiralmore » flow path and seal annular chamber whereby the propellant is uniformly heated by the hollow housing and the porous heat exchanger material as it flows therethrough in a minimum gas path length, and a thermal choke formed in the electrical heating element adjacent to the coiled wire for reducing conducted thermal energy.« less

Inventors:
; ; ; ;
Publication Date:
OSTI Identifier:
5286973
Patent Number(s):
US 4608821
Assignee:
NASA, Washington, DC
Resource Type:
Patent
Resource Relation:
Patent File Date: Filed date 31 Jul 1984
Country of Publication:
United States
Language:
English
Subject:
32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATION; 42 ENGINEERING; HEAT EXCHANGERS; DESIGN; OPERATION; PROPELLANTS; ELECTRIC HEATING; THRUSTERS; ABSORPTION; CERAMICS; CERMETS; GAS FUELS; HIGH TEMPERATURE; NOZZLES; POROUS MATERIALS; REFRACTORIES; SPACE DEPENDENCE; TEXTURE; THICKNESS; VERY HIGH TEMPERATURE; WIRES; COMPOSITE MATERIALS; DIMENSIONS; FUELS; HEATING; MATERIALS; 320201* - Energy Conservation, Consumption, & Utilization- Transportation- Air & Aerospace; 421000 - Engineering- Combustion Systems

Citation Formats

Zavesky, R J, Sovey, J S, Mirtich, M J, Marinos, C, and Penko, P F. Heat exchanger for electrothermal devices. United States: N. p., 1986. Web.
Zavesky, R J, Sovey, J S, Mirtich, M J, Marinos, C, & Penko, P F. Heat exchanger for electrothermal devices. United States.
Zavesky, R J, Sovey, J S, Mirtich, M J, Marinos, C, and Penko, P F. Tue . "Heat exchanger for electrothermal devices". United States.
@article{osti_5286973,
title = {Heat exchanger for electrothermal devices},
author = {Zavesky, R J and Sovey, J S and Mirtich, M J and Marinos, C and Penko, P F},
abstractNote = {A heat exchanger is described for heating a gaseous propellant to a temperature between about 200/sup 0/C and about 2200/sup 0/C in an electrothermal thruster having a nozzle comprising a hollow housing forming a cylindrical chamber adjacent to the nozzle, the hollow housing having a textured inner surface to provide high absorptivity and an oppositely disposed textured outer surface to provide high emissivity, an outer housing surrounding the cylindrical chamber in spaced relationship thereto thereby forming an annular chamber for conducting the gaseous propellant to the nozzle, a porous heat exchanger material selected from the group consisting of refractories, ceramics, and cermets contained within the annular chamber, housing a wire coiled about the outer surface of the hollow housing in engagement with the outer housing for providing a lengthened spiral flow path for the propellant to the annular chamber, an electrical heating comprising a coiled tube having a wall thickness of about 0.25 mm and a textured surface for providing high emissivity mounted within the cylindrical chamber in spaced relationship with the textured inner surface for radiatively heating the hollow housing and heat exchanger material without contacting the gaseous propellant, means for supplying a gaseous propellant to the lengthened spiral flow path and seal annular chamber whereby the propellant is uniformly heated by the hollow housing and the porous heat exchanger material as it flows therethrough in a minimum gas path length, and a thermal choke formed in the electrical heating element adjacent to the coiled wire for reducing conducted thermal energy.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1986},
month = {9}
}