Investigation of transformation of intermediate products of liquid-phase interaction propellant at the onset of combustion for rocket engine

Abstract

The results of an experimental study of the conversion of intermediate (liquid-phase and gasified) product exothermic liquid-phase interaction of hypergolic propellant components in the initial stage of combustion are presented. To investigate the present step conversion of intermediates experimental method for the flow reactor is used. In the process of the experiment the centrifugal and wedge mixing elements is used as propellants mixing systems for flowing reactor. This mixing elements allowed interaction of components in the liquid phase and subsequent flow of the liquid-phase intermediates on the wall of the reactor. Thereby dividing the flow of liquid and gasified intermediates in cross-section is achieved. During the experiment the effect of the following basic parameters of the processes of transformation of intermediates is revealed: the effectiveness of liquid-phase mixing of the fuel components, the residence time of intermediate products in the channel and the pressure of gasified products. Results of the study of converting liquid-phase intermediates in the combustion stage confirm the assumption about the prospects of using of liquid-phase products for internal cooling of rocket engine chamber wall provided efficient organization of the chamber working process, because of the temperature of liquid-phase products, washing the inner surface of the channel changes slightly along the entire length of the channel. Exothermic processes of liquid-phase interaction between fuel components at this stage is substantially complete. Heat removal of energy from previously gasified intermediates is required for subsequent gasification of liquidphase intermediates. Unlike the liquid-phase conversion of intermediates, converting process of the gasified intermediates occurs quite rapidly in the initial stage of combustion. The temperature of gasified intermediates depending on the boundary conditions in preflame zone was ~ 900 ... 1100 K, and in the output section of the channel of the reactor reached ~ 1400 ... 2000 K.

About the authors

V. E. Nigodjuk

Samara State Aerospace University

Author for correspondence.
Email: ke_src@ssau.ru

Candidate of Science (Engineering)

Associate professor of the department of aircraft engines theory

Russian Federation

A. V. Sulinov

Samara State Aerospace University

Email: ke_src@ssau.ru

Candidate of Science (Engineering)

Associate professor of the department of aircraft engines theory and senior research fellow, research center of cosmic energy

Russian Federation

References

  1. Dubinkin Y.M., Nigodyuk V.E. Problems of organization of workflow in liquid rocket microthrusters // Russian Aeronautics. 1993. No. 2. P. 71-74.
  2. Nigodyuk V.E., Sulinov A.V. Research of laws of interaction of components in a liquid phase self-igniting liquid rocket fuel // Vestnik of the Samara State Aerospace University. 2009. No. 3(19), рart 2. P. 311-315. (In Russ.)
  3. Nigodyuk V.E., Sulinov A.V. The flowing reactor as the tool of an experimental research of processes of transformation selfigniting liquid rocket fuel // Vestnik of the Samara State Aerospace University. 2009. No. 3(19), рart 2. P. 311-315. (In Russ.)
  4. Nigodyuk V.E. Sulinov A.V. Investigation of the kinetic properties of gas products of liquid-phase interaction hypergolic liquid rocket fuel // Vestnik of the Samara State Aerospace University. 2011. No. 3(27), рart 3. P. 251-256. (In Russ.)

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