Abstract

There is a lack of understanding of the spray characteristics of gas-centered swirl coaxial (GCSC) injectors during self-pulsation occurs. Therefore, the self-pulsation of a GCSC injector was investigated experimentally in this study. Experiments were conducted at atmospheric pressure with filtered water and dried air supplied through a propellant feed system. A back-lighting high-speed photography technique was used to capture unsteady spray features. A laser-based particle size analyzer (LPSA) was used to measure the size of the droplets in the spray. The effects of recess and gas-liquid ratio on spray self-pulsation were analyzed. It was found that the recess of the injector strongly determines the spray pattern. When spray self-pulsation occurs without recess, both the center and periphery of the spray oscillate. With an increase in the mass flow rate of the gas, the boundary between the center and the periphery of the spray becomes more noticeable. Meanwhile, small droplets in the spray center oscillate, with the periphery of the spray being characterized by a periodic “shoulder.” Under the same operating conditions but with a small recess (2 mm), the spray adheres to the injector faceplate. With a larger recess (7 mm), when spray self-pulsation occurs, the spray periodically forms “shoulder” and “neck,” similar to the behavior of self-pulsation in a liquid-centered coaxial injector. Therefore, it can be concluded that spray self-pulsation enhances atomization at the center of the spray to a certain extent. However, atomization becomes worse in the periphery with an oscillating spray.

Highlights

  • Combustion instability has permanently restricted the development of liquid rocket engines

  • The spray angle was determined using the method described above. By applying these three steps to a series of spray images, the spray angles for all the operational conditions were obtained

  • This study suggests that the adhesion phenomenon is caused by self-pulsation

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Summary

INTRODUCTION

Combustion instability has permanently restricted the development of liquid rocket engines. Xu (Shun, 2016) summed up the method of liquid film breakup as segmented sheet, bubble, pure-pulsating, and perforated sheet breakups, by observing the spray image under conditions with different gas-liquid ratios He found that self-pulsation led to an increase in the spray angle in the GCSC injector. Kang (Kang et al, 2016) and Bai (Bai et al, 2018; Bai et al, 2019; Bai et al, 2020) used Yang’s theory to develop the mechanism of self-pulsation for LCSC injectors They believed that when the recess angle of the injector equals the angle of the liquid film, the spray is in a critical mixing mode. Mechanisms of spray self-pulsation in a GCSC injector have been proposed

EXPERIMENTAL METHODS
RESULTS AND DISCUSSION
CONCLUSION
DATA AVAILABILITY STATEMENT
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