Start-up in microgravity and local thermodynamic states of a hybrid loop thermosyphon/pulsating heat pipe

Mauro Mameli, Andrea Catarsi, Daniele Mangini, Luca Pietrasanta, Nicholas Michè, Marco Marengo, Paolo Di Marco, Sauro Filippeschi

Research output: Contribution to journalArticleResearchpeer-review

Abstract

A wickless passive two phase closed loop heat transfer device especially designed for a future implementation on the heat transfer host module of the International Space Station is tested in relevant environment on board a parabolic flight. The tube internal diameter (3 mm) is larger than the static capillary threshold evaluated in normal gravity for this working fluid (FC-72), leading the device to work as a loop thermosyphon on ground and in hyper-gravity conditions, and as a Pulsating Heat Pipe when micro-gravity occurs. Novel start up tests, where the heat load has been provided after the occurrence of microgravity, show that the 20 s microgravity period is enough for the device activation and, most important, that the device activation is purely thermally induced and not affected by the previous acceleration field. Two miniaturized pressure transducers and direct fluid temperature measurement via two micro-thermocouples, allow to provide a detailed insight on the fluid local thermodynamics states both in the evaporator and in the condenser zone during microgravity. It is shown that the two-phase fluid close to the evaporator and the condenser is subjected to several degrees (up to 5 K) of superheating or subcooling. The level of subcooling seems to increase with the heat input level both in terms of temperature difference and in terms of percentage time with respect to the whole microgravity period.

Original languageEnglish
Article number113771
JournalApplied Thermal Engineering
Volume158
DOIs
Publication statusPublished - 13 May 2019

Fingerprint

Thermosyphons
Heat pipes
Microgravity
Thermodynamics
Fluids
Evaporators
Gravitation
Chemical activation
Heat transfer
Pressure transducers
Space stations
Thermal load
Thermocouples
Temperature measurement

Keywords

  • International space station
  • Microgravity
  • Pulsating heat pipe
  • Start-up
  • Thermodynamic states

Cite this

@article{4f94fce3272045e4bf0b6d487c0fcfdd,
title = "Start-up in microgravity and local thermodynamic states of a hybrid loop thermosyphon/pulsating heat pipe",
abstract = "A wickless passive two phase closed loop heat transfer device especially designed for a future implementation on the heat transfer host module of the International Space Station is tested in relevant environment on board a parabolic flight. The tube internal diameter (3 mm) is larger than the static capillary threshold evaluated in normal gravity for this working fluid (FC-72), leading the device to work as a loop thermosyphon on ground and in hyper-gravity conditions, and as a Pulsating Heat Pipe when micro-gravity occurs. Novel start up tests, where the heat load has been provided after the occurrence of microgravity, show that the 20 s microgravity period is enough for the device activation and, most important, that the device activation is purely thermally induced and not affected by the previous acceleration field. Two miniaturized pressure transducers and direct fluid temperature measurement via two micro-thermocouples, allow to provide a detailed insight on the fluid local thermodynamics states both in the evaporator and in the condenser zone during microgravity. It is shown that the two-phase fluid close to the evaporator and the condenser is subjected to several degrees (up to 5 K) of superheating or subcooling. The level of subcooling seems to increase with the heat input level both in terms of temperature difference and in terms of percentage time with respect to the whole microgravity period.",
keywords = "International space station, Microgravity, Pulsating heat pipe, Start-up, Thermodynamic states",
author = "Mauro Mameli and Andrea Catarsi and Daniele Mangini and Luca Pietrasanta and Nicholas Mich{\`e} and Marco Marengo and {Di Marco}, Paolo and Sauro Filippeschi",
year = "2019",
month = "5",
day = "13",
doi = "10.1016/j.applthermaleng.2019.113771",
language = "English",
volume = "158",
journal = "Applied Thermal Engineering",
issn = "1359-4311",

}

Start-up in microgravity and local thermodynamic states of a hybrid loop thermosyphon/pulsating heat pipe. / Mameli, Mauro; Catarsi, Andrea; Mangini, Daniele; Pietrasanta, Luca; Michè, Nicholas; Marengo, Marco; Di Marco, Paolo; Filippeschi, Sauro.

In: Applied Thermal Engineering, Vol. 158, 113771, 13.05.2019.

Research output: Contribution to journalArticleResearchpeer-review

TY - JOUR

T1 - Start-up in microgravity and local thermodynamic states of a hybrid loop thermosyphon/pulsating heat pipe

AU - Mameli, Mauro

AU - Catarsi, Andrea

AU - Mangini, Daniele

AU - Pietrasanta, Luca

AU - Michè, Nicholas

AU - Marengo, Marco

AU - Di Marco, Paolo

AU - Filippeschi, Sauro

PY - 2019/5/13

Y1 - 2019/5/13

N2 - A wickless passive two phase closed loop heat transfer device especially designed for a future implementation on the heat transfer host module of the International Space Station is tested in relevant environment on board a parabolic flight. The tube internal diameter (3 mm) is larger than the static capillary threshold evaluated in normal gravity for this working fluid (FC-72), leading the device to work as a loop thermosyphon on ground and in hyper-gravity conditions, and as a Pulsating Heat Pipe when micro-gravity occurs. Novel start up tests, where the heat load has been provided after the occurrence of microgravity, show that the 20 s microgravity period is enough for the device activation and, most important, that the device activation is purely thermally induced and not affected by the previous acceleration field. Two miniaturized pressure transducers and direct fluid temperature measurement via two micro-thermocouples, allow to provide a detailed insight on the fluid local thermodynamics states both in the evaporator and in the condenser zone during microgravity. It is shown that the two-phase fluid close to the evaporator and the condenser is subjected to several degrees (up to 5 K) of superheating or subcooling. The level of subcooling seems to increase with the heat input level both in terms of temperature difference and in terms of percentage time with respect to the whole microgravity period.

AB - A wickless passive two phase closed loop heat transfer device especially designed for a future implementation on the heat transfer host module of the International Space Station is tested in relevant environment on board a parabolic flight. The tube internal diameter (3 mm) is larger than the static capillary threshold evaluated in normal gravity for this working fluid (FC-72), leading the device to work as a loop thermosyphon on ground and in hyper-gravity conditions, and as a Pulsating Heat Pipe when micro-gravity occurs. Novel start up tests, where the heat load has been provided after the occurrence of microgravity, show that the 20 s microgravity period is enough for the device activation and, most important, that the device activation is purely thermally induced and not affected by the previous acceleration field. Two miniaturized pressure transducers and direct fluid temperature measurement via two micro-thermocouples, allow to provide a detailed insight on the fluid local thermodynamics states both in the evaporator and in the condenser zone during microgravity. It is shown that the two-phase fluid close to the evaporator and the condenser is subjected to several degrees (up to 5 K) of superheating or subcooling. The level of subcooling seems to increase with the heat input level both in terms of temperature difference and in terms of percentage time with respect to the whole microgravity period.

KW - International space station

KW - Microgravity

KW - Pulsating heat pipe

KW - Start-up

KW - Thermodynamic states

UR - http://www.scopus.com/inward/record.url?scp=85065717895&partnerID=8YFLogxK

U2 - 10.1016/j.applthermaleng.2019.113771

DO - 10.1016/j.applthermaleng.2019.113771

M3 - Article

VL - 158

JO - Applied Thermal Engineering

T2 - Applied Thermal Engineering

JF - Applied Thermal Engineering

SN - 1359-4311

M1 - 113771

ER -