Computation study of the low-thrust rocket engine chamber thermal state operating on the oxygen + methane gaseous propellant components with the structural elements regenerative external cooling by an oxidizer
Published: 01.11.2024
Authors: Novikov A.V., Andreev E.A., Bardakova E.I.
Published in issue: #11(155)/2024
DOI: 10.18698/2308-6033-2024-11-2402
Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts
The conducted computation and parametric study are making it possible to obtain recommendations on optimal values of the design and technological parameters for the low-thrust rocket engine (LTRE) chamber ensuring its reliable cooling by a gaseous oxidizer in a wide range of alteration in the oxidizer excess and combustion chamber pressure coefficients. In this case, optimization criterion is the chamber consumption system coefficient, i.e. maximum conversion of the fuel chemical energy into the combustion products thermal energy. Optimal configuration of the LTRE combustion chamber with zonal supply of the components is obtained by computation and confirms declared characteristics in the entire range of the studied parameters making it possible to recommend this configuration as the basic one in the thrust range in vacuum of 20...200 N.
EDN EVTFFE
References
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