Influence in a constructive and regime parameters antechamber by operation-in the combustion chamber liquid-propellant rocket engine thrusters on hypergolic liquid propellants
- Authors: Nigodjuk V.E.1, Sulinov A.V.1
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Affiliations:
- Samara State Aerospace University named after academician S.P. Korolyov (National Research University)
- Issue: Vol 10, No 3-3 (2011): Special Issue
- Pages: 269-276
- Section: AIRCRAFT AND SPACE ROCKET ENGINEERING
- URL: https://journals.ssau.ru/vestnik/article/view/6891
- DOI: https://doi.org/10.18287/2541-7533-2011-0-3-3(27)-269-276
- ID: 6891
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Abstract
The article presents the results of theoretical and experimental studies on intensification through antechamber major limiting stages of the flow of the working process in the combustion chamber: the gasification of liquid phase intermediates and evaporation of unreacted fuel components Comrade through the organization of effective secondary crushing and mixing of gas-phase and mouth-injuries of large-scale non-uniformity of the ratio of the fuel components in the cross section through heavy turbulence in gas-phase intermediates
About the authors
V. E. Nigodjuk
Samara State Aerospace University named after academician S.P. Korolyov (National Research University)
Author for correspondence.
Email: ke_src@ssau.ru
candidate of technical science, associate professor
Russian FederationA. V. Sulinov
Samara State Aerospace University named after academician S.P. Korolyov (National Research University)
Email: ke_src@ssau.ru
candidate of technical science, associate professor
Russian Federation