Advancements in liquid propellant rocket engines (LPRE) are requiring higher thermal loads for long duration times. Regenerative cooling has been shown to be a highly effective cooling technique for LPRE. To authors' knowledge, there have not been any previous work published that explores the use of turbulators in regenerative cooling channels for LPRE application. In the present study, regenerative cooling of a high performance engine is modeled numerically to explore the effects of introducing turbulence inducing structures to the coolant passages. The addition of longitudinal ribs at critical locations within the coolant channel have shown to reduce the maximum temperature experienced by the nozzle casing by 32K with a less than 1% pressure rise compared to the conventional design. The addition of ribs is observed to provide a relatively uniform increase in the local heat transfer on the coolant channel surface.
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