Open AccessProperties of Kerosene-Aluminium Nanofluid used to Estimate the Overall Heat Transfer Rates during Regenerative/Film Cooling of Thrust Chambers
Author(s) -
Abhinav Kumar,
Umar Mushtaq,
Muskan Raikwar,
Anil Chamoli,
Shahid Ullah Khan
Publication year - 2019
Publication title -
international journal of engineering and advanced technology
Language(s) - English
Resource type - Journals
ISSN - 2249-8958
DOI - 10.35940/ijeat.a1033.1291s319
Subject(s) - kerosene , nanofluid , rocket (weapon) , aerospace engineering , heat transfer , nozzle , thrust , propellant , materials science , spacecraft , aluminium , propulsion , nuclear engineering , mechanical engineering , spacecraft propulsion , environmental science , mechanics , engineering , composite material , thermodynamics , physics
Large heat transfer rates are always desired for rocket propulsion applications as high heat loads are associated at the nozzle exit. Different strategies have been employed in order to have high heat transfer coefficients including use of liquid nitrogen, spray cooling etc. ISRO has planned to use aluminium based nano-particles with kerosene in order to cool launching vehicles including GSLV Mk III as it is the heaviest rocket that can carry large payloads. Recently, ISRO has announced to install its own International Space Station (ISS) in future and in such applications larger payloads are to be carried by the rocket. In this work, an analytical study on the thermodynamic properties of the aluminium nano-particles based kerosene nanofluid has been done and an attempt has also been made to develop a temperature and pressure dependent correlation that can be used in computational analysis of thrust chambers while film/regenerative cooling.