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To Calculation of Regenerative Cooling of a Liquid Fuel Rocket Engine Chamber

  • Aircraft and Rocket Engine Theory
  • Published:
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Abstract

This paper demonstrates that in transition from the one-dimensional longitudinal-channel motion of the coolant in the regenerative cooling system of the liquid propellant engine to the twodimensional (interchannel) channel motion (transpiration) through a porous mesh material (PMM), the hydraulic losses decrease. Experimental data on PMM hydraulic resistance coefficients and heat transfer in porous paths with the interchannel coolant transpiration (ICCT) is presented.

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Authors and Affiliations

  1. Bauman Moscow State Technical University (National Research University), ul. 2-ya Baumanskaya 5, Moscow, 105005, Russia

    F. V. Pelevin & A. V. Ponomarev

Authors
  1. F. V. Pelevin
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  2. A. V. Ponomarev
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Correspondence to F. V. Pelevin.

Additional information

Original Russian Text © F.V. Pelevin, A.V. Ponomarev, 2018, published in Izvestiya Vysshikh Uchebnykh Zavedenii, Aviatsionnaya Tekhnika, 2018, No. 1, pp. 71–77.

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Pelevin, F.V., Ponomarev, A.V. To Calculation of Regenerative Cooling of a Liquid Fuel Rocket Engine Chamber. Russ. Aeronaut. 61, 71–77 (2018). https://doi.org/10.3103/S1068799818010117

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  • DOI: https://doi.org/10.3103/S1068799818010117

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