Influence of Heat Exchange Intensity in the Rocket Thrust Chamber on the Cooling Channel Efficiency

Authors: Aleksandrenkov V.P. Published: 03.08.2017
Published in issue: #4(115)/2017  

DOI: 10.18698/0236-3941-2017-4-4-10

Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts  
Keywords: annular channel, intensification of convective heat transfer, thermal and hydraulic efficiency and characteristics, maximum heat dissipation, heat transfer coefficients ratio, limiting efficiency

The study tested the efficiency of measures of heat transfer intensification in annular cooling channels of rocket thrust chambers. We calculated and analytically studied the influence of heat transfer coefficients ratio on opposite sides of the wall on the final cooling efficiency. The study showed that in the range of parameters under consideration the actual thermal and hydraulic efficiency is always lower than the limit values, and the greater the limit values and the level of the heat transfer ratio are the higher is the efficiency. We found that in terms of thermal and hydraulic efficiency, other things being equal, the forcing of heat transfer from the cooler side is justified, if its relative value does not exceed two units, and it is sufficiently highly effective as it decreases within the same order.


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