마하 4 유동장 내 연료 분사 위치에 따른 초음속 연소 현상 연구 = Effect of Fuel Injector Location on Supersonic Combustion in a Mach 4 flow

다국어 초록 (Multilingual Abstract)

Supersonic combustion experiments have been performed using three different hydrogen-fuel injection configurations in a cavity-based combustor at three combustor-entrance flow conditions. Angled injection is located upstream of the cavity with 15° angle, parallel injection is positioned on the front step, and upstream injection is on the rear ramp. Planar laser-induced fluorescence of the hydroxyl radical is used to investigate the flow characteristics. Angled injection generates a weak bow shock in front of the injector and recirculation zone to maintain the combustion as the equivalence ratio increases. Parallel and upstream injection tests show similar flame structure over the cavity at low equivalence ratio. Upstream injection enhances the fuel diffusion arid enables ignition with a shorter delay length than with parallel injection. The presence of a flame near the cavity is sensitive to the fuel injection location, the equivalence ratio and total enthalpy of the air flow. The flame characteristics agree with the correlation plot of the stable flame limit of non-premixed conditions.

목차 (Table of Contents)

• ABSTRACT
• 1. 서론
• 2. 실험 방법
• 3. 결과 및 분석
• 4. 결론
• 후기
• 참고문헌