Abstract
The performance of the engine highly depends on the fuel mixing process as a significant process to achieve efficient supersonic flight. Current article has attempted to release the effects of different annular lobe-injectors on fuel mixing when Ma>1. Three various annular jet nozzles are expansively investigated for injection of the sonic hydrogen jet at supersonic air crossflow with Mach-4. Comprehensive comparison of the jet structure of these models are performed through the evaluation of Mach and fuel concentration downstream of these lobe-injectors. Comparison of mixing efficiency also indicates that the nozzle with 3-lobe configuration has 25% more fuel mixing performance than other configurations. Our findings also show that mixing performance of annular lobe-injector is about 15% more than simple one for cases with 2-lobe and 4-lobe injectors.
| Original language | English |
|---|---|
| Pages (from-to) | 22215-22225 |
| Number of pages | 11 |
| Journal | International Journal of Hydrogen Energy |
| Volume | 47 |
| Issue number | 52 |
| DOIs | |
| State | Published - 22 Jun 2022 |
UN SDGs
This output contributes to the following UN Sustainable Development Goals (SDGs)
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SDG 7 Affordable and Clean Energy
Keywords
- Annular jet
- CFD
- Compressible
- Fuel mixing
- Lobe-injector
- Supersonic combustion
- flow
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