Transactions of Nanjing University of Aeronautics & Astronautics
Effects of Lobe Peak-to-Trough Width Ratio on Mixing and Combustion Performance in ATR Combustors
- Article
- Figures
- Metrics
- Preview PDF
- Reference
- Related
- Cited by
- Materials
Abstract:
The air-turbo-rocket （ATR） engine is a promising propulsion plant for achieving numerous surface and air launched missile missions. The application of lobed mixer in the ATR combustor can promote the mixing of the fuel-rich gas and the air， thus improving the engine performance significantly. The numerical simulation method was conducted to explore the effects of lobe peak-to-trough width ratio on mixing and combustion performance in ATR combustors. Results show that： For a given peak lobe width b1， the combustion efficiency and total pressure loss decrease with the increase of trough lobe width b2； For a given b2， the combustion efficiency and total pressure loss decrease with the increase of b1； The fan-type lobed mixer with smaller b2 has a better effect on promoting the combustion efficiency in the region near the ATR combustor center line than that with a pair of parallel side walls. The total pressure recovery coefficient reaches more than 0.99 at the exit of combustor in nonreactive combustion while the total pressure loss reaches more than 4% in the reacting combustion. Compared with the mixing process， more than 80% of the total pressure loss is caused during combustion.
Keywords:
Project Supported:
This work was supported by the National Science and Technology Major Project （No.
Clc Number:
V19
Mobile website
