Properties of Kerosene-Aluminium Nanofluid used to Estimate the Overall Heat Transfer Rates During Regenerative/Film Cooling of Thrust Chambers
Abhinav Kumar1, Umar Mushtaq2, Muskan Raikwar3, Anil Chamoli4, Shahid Khan5
1Abhinav Kumar, Department of Mechanical Engineering, Lovely Professional University, Phagwara (Punjab), India.
2Umar Mushtaq, Department of Aerospace Engineering, Lovely Professional University, Phagwara (Punjab), India.
3Muskan Raikwar, Department of Aerospace Engineering, Lovely Professional University, Phagwara (Punjab), India.
4Anil Chamoli, Department of Aerospace Engineering, Lovely Professional University, Phagwara (Punjab), India.
5Shahid Khan, Department of Aerospace Engineering, Lovely Professional University, Phagwara (Punjab), India.
Manuscript received on 14 December 2019 | Revised Manuscript received on 22 December 2019 | Manuscript Published on 31 December 2019 | PP: 165-169 | Volume-9 Issue-1S3 December 2019 | Retrieval Number: A10331291S319/19©BEIESP | DOI: 10.35940/ijeat.A1033.1291S319
Open Access | Editorial and Publishing Policies | Cite | Mendeley | Indexing and Abstracting
© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: 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.
Keywords: Film Cooling, Kerosene, Dodecane, Thrust Chambers, GSLV Mk III.
Scope of the Article: Heat Transfer