Numerical investigation of phisical processes in cooling jacket of thrust chamber of LOx – LH2 LRE using 3D computer simulation methods

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Abstract

The problem solution of conjugate heat transfer in thrust chamber cooling jacket of liquid rocket engine is considered. Finding design data is compared with experiment.

About the authors

P. A. Yakub

OSC KBKhA, Voronezh

Author for correspondence.
Email: pavel-vrn@list.ru

Design-engineer

Russian Federation

A. V. Gumennyy

OSC KBKhA, Voronezh

Email: gav126@mail.ru

Chief of Gas Dynamics, Fluid Dynamics and Thermal Design Department

Russian Federation

References

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  3. ANSYS CFX Version 14.0 Documentation, 2011.
  4. Варгафтик, Н.Б. Справочник по теплофизическим свойствам газов и жидкостей [Текст] / Н.Б. Варгафтик.- М.: Наука, 1972. – 720 c.
  5. Шлихтинг, Г. Теория пограничного слоя [Текст] / Г. Шлихтинг. - М.: Наука, 1974. – 713 c.
  6. Kuhl, D. Thermomechanical analysis and optimization of cryogenic liquid rocket engines [Теxt] / D. Kuhl, J. Riccius // Journal of Propulsion and Power – 2002. - V.18. - №4.

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