Influence of plasma-enhanced combustion on RBCC engine using URANS

Area of Science:

• Aerospace Engineering
• Plasma Physics
• Combustion Science

Background:

• Rocket-based combined-cycle (RBCC) engines are key for single-stage-to-orbit vehicles.
• Sustained subsonic combustion is challenging in RBCC engines due to low flow temperatures.
• RBCC engine mode transition control is critical for efficient operation.

Purpose of the Study:

• To investigate the use of plasma combustion support for improving RBCC engine performance during mode transitions.
• To analyze the impact of multi-channel gliding arc (MCGA) plasma-assisted combustion on RBCC engine flow fields.
• To evaluate the effectiveness of plasma support across different Mach numbers and transition phases.

Main Methods:

• Numerical simulation and validation of a full-path RBCC engine configuration.
• Investigation of multi-channel gliding arc (MCGA) plasma-assisted combustion technology.
• Analysis of flow fields during transitions from ejector/ramjet to ramjet/scramjet modes.

Main Results:

• At low Mach numbers, plasma support enhances heat release and flame range, increasing thrust and reducing drag.
• At high Mach numbers, plasma support stabilizes combustion, reduces thrust fluctuations, and shortens transition times.
• Plasma-assisted combustion improves overall engine thrust and reduces resistance during critical transition phases.

Conclusions:

• Plasma combustion support is a viable method to enhance RBCC engine performance during mode transitions.
• MCGA plasma technology offers significant benefits for RBCC engines operating across a wide range of conditions.
• This approach addresses key challenges in RBCC engine efficiency and operational stability for space launch applications.