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Gear-Shaped High-g Combustion Chamber for Micro Turbojet Engine Applications
Haozhong Huang1, Guixin Chen1, Huigui Long1
1College of Mechanical Engineering, Guangxi University, Nanning 530004, China.
ACS Omega
|April 29, 2024
Summary
This study introduces a high-centrifugal (high-g) combustion chamber for micro turbojet engines, improving thrust-to-weight ratio and reducing engine length. The new design enhances temperature uniformity and enables significant weight reduction.
Area of Science:
- Aerospace Engineering
- Thermodynamics
- Combustion Science
Background:
- Micro turbojet engines face challenges in combustion efficiency and thrust-to-weight ratio.
- Traditional turbojet engines have lengthy combustion chambers.
- Previous high-g combustor designs exhibited uneven rotor temperature distribution.
Purpose of the Study:
- To investigate the feasibility of integrating a high-centrifugal (high-g) combustion chamber (HGC) into micro turbojet engines.
- To analyze and optimize HGC structural design for improved performance and integration.
- To enhance combustion efficiency and thrust-to-weight ratio while reducing engine size.
Main Methods:
- Experimental testing on a 120 N thrust micro turbojet engine.
- Simulation analysis of HGC structural designs.
- Iterative design process focusing on inlet geometry and baffle plate optimization.
Main Results:
- Achieved a stable, highly centrifugal environment for improved combustion.
- Reduced axial combustion chamber length by nearly 30%.
- Significantly improved temperature uniformity at the combustion chamber outlet.
- Reduced engine weight by approximately 10.7% and increased thrust-to-weight ratio by up to 12%.
Conclusions:
- The optimized HGC design effectively addresses temperature distribution issues.
- The HGC offers substantial benefits for micro turbojet engine lightweighting and performance enhancement.
- This research provides a viable design pathway for future compact and efficient micro turbojet engines.
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