Influence of helix angle on heat transfer characteristics of regenerative cooling in spiral channel

Abstract

A rapid solution method for spiral line and a one-dimensional (1-D) heat transfer calculation model for spiral regenerative cooling channels (RCCs) are proposed to clarify the influence of the helix angle on the heat transfer characteristics of spiral RCCs in thrust chambers. The method based on the projection principle is characterized by a simple model and the ability to generate variable helix angles spiral line. The calculation model is characterized by high accuracy, with coolant pressure drop errors of less than 5 % coolant and coolant temperature errors of less than 20 % compared to experimental data. Utilizing the calculation model, research on the heat transfer characteristics of RCCs with varying helix angles is conducted. Results indicate that the coolant temperature rise and pressure drop increase as the helix angle increases. The peak values of the gas-side wall temperature occur at the throat and the contraction section. The throat peak value decreases with an increase in the helix angle, while the contraction section peak value increases. When the helix angle is 30°, the two peak values are close as well as the highest gas-side wall temperature is minimized. The highest wall temperature is only 1111K. The research results can provide guidance for the design and processing of spiral RCCs.

Keywords

• Liquid rocket engine (LRE)
• Regenerative cooling
• Spiral channels
• Helix angle
• Heat transfer characteristics