1958
DOI: 10.1063/1.1723373
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Measured Thermal Efficiencies of a Diode Configuration of a Thermo Electron Engine

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Cited by 81 publications
(25 citation statements)
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“…The experimental conversion efficiencies eventually reached around 10-15 % [1,2], when the emitter electrode was heated up to 1260 o C with Cs + ions vapor to lower the work function. The space charge cloud on the emitter electrode is one major obstacle preventing the next electron emission.…”
Section: Introductionmentioning
confidence: 99%
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“…The experimental conversion efficiencies eventually reached around 10-15 % [1,2], when the emitter electrode was heated up to 1260 o C with Cs + ions vapor to lower the work function. The space charge cloud on the emitter electrode is one major obstacle preventing the next electron emission.…”
Section: Introductionmentioning
confidence: 99%
“…Thermionic energy conversion, which can directly convert heat energy into electricity, is one of the most promising technologies for waste heat recovery applications [1][2][3][4][5][6][7][8][9]. It is expected reutilize unused thermal energy such as exhaust from industrial plants, automobiles, and renewable resources such as geothermal and hot spring resources.…”
Section: Introductionmentioning
confidence: 99%
“…e = Electronic charge. :x THE use of the thermionic diode as a means of converting heat into electrical energy has already been discussed in detail (Hatsopoulos and Kaye 1958, Houston 1959} Grattidge 1960, Morgulis and Korchevori 1960. From these papers the existence of space charge would appear to be one of the major problems, but various means of overcoming this have been suggested (Grattidge 1960 has been neutralized in an unspecified manner and hence does not influence the current.…”
mentioning
confidence: 98%
“…Although there were significant advances in the design and methods for realizing TECs exhibiting efficiencies exceeding 15% (Hatsopoulos and Kaye, 1958), there were technical issues not satisfactorily resolved in the scale up, such as cathode stability, maintaining close electrode spacing, collector reflection losses, and magnetic field generation (Schock, 1960). Consequently, the continuation of TEC device development occurred only for use in space exploration where the device complexity and high unit cost could be offset by the savings in payload costs for compact kilowatt electrical power generation (Ponomarey-Stepnoi et al, 1995).…”
mentioning
confidence: 99%