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상류 분사 공동 화염 지지부를 가지는 스크램제트 엔진에 관한 실험적 연구
Jeong, Eun-Ju,Jeung, In-Seuck,O'Byrne, Sean,Houwing, A.F.P. 한국연소학회 2006 한국연소학회지 Vol.11 No.4
The model cavity scramjet engine experiments are carried out using T3 free-piston shock tunnel. Upstream hydrogen fuel is injected before the cavity with different injection pressure. OH planar laser-induced fluorescence is used to investigate the combustion zone and piezoelectric pressure transducers are used to define the pressure rise due to the combustion. Main combustion region is a mixing layer which is between air and fuel. Also high OH fluorescence signal is appeared in the shear layer above the cavity in high equivalence ratio. From the OH signal in the cavity, this fuel injection system can be a role as a flame-holder.
공동 상류 경사 분사를 이용한 초음속 연소기의 실험적 연구, Part 2 : 압력 측정
정은주(Eunju Jeong),정인석(In-Seuck Jeung),Sean O’Byrne,A.F.P Houwing 한국연소학회 2007 한국연소학회지 Vol.12 No.1
The supersonic combustion experiments are carried out using T3 free-piston shock tunnel. Different shock tube fill pressures have various inflow conditions. 15˚ inclined hydrogen fuel injection is located before the cavity. Oblique shock is generated at the trailing edge of the cavity and reflects off the top and bottom wall. For non-reacting flow, static pressures in low equivalence ratio are similar to those in no fuel injection. As equivalence ratio is increased, static pressures are increased in the duct. In the similar equivalence ratio, static pressures are increased when total enthalpy is decreased. For reacting flow, the flame is occurred near the cavity. The combustion is weak locally in the middle of the duct. The up and down pressure distribution in the duct means that the supersonic combustion is generated.
공동 상류 경사 분사를 이용한 초음속 연소기의 실험적 연구, Part 1 : OH-PLIF 측정
Jeong, Eun-Ju,Jeung, In-Seuck,O'Byrne, Sean,Houwing, A.F.P 한국연소학회 2007 한국연소학회지 Vol.12 No.1
The supersonic combustion experiments are carried out using T3 free-piston shock tunnel. Different shock tube fill pressures have various inflow conditions. $15^{\circ}$ inclined hydrogen fuel injection is located before the cavity. Oblique shock is generated from the cavity and reflects off the top and bottom wall. For non-reacting flow, fuel makes the shear layer thicker above the cavity therefore, the shock is generated just before the trailing edge. This research has self-ignition in the combustor. For reacting flow, as the equivalence ratio increases, flame starts to generate near the injector or occur in the recirculation zone before the injector. High fuel injection sustains the jet shape in the cross flow and air can mix with fuel along the shear layer. Therefore, two flame layers find above the cavity for high equivalence ratio.
공동 상류 경사 분사를 이용한 초음속 연소기의 실험적 연구, Part 2 : 압력 측정
Jeong, Eun-Ju,Jeung, In-Seuck,O'Byrne, Sean,Houwing, A.F.P 한국연소학회 2007 한국연소학회지 Vol.12 No.1
The supersonic combustion experiments are carried out using T3 free-piston shock tunnel. Different shock tube fill pressures have various inflow conditions. $15^{\circ}$ inclined hydrogen fuel injection is located before the cavity. Oblique shock is generated at the trailing edge of the cavity and reflects off the top and bottom wall. For non-reacting flow, static pressures in low equivalence ratio are similar to those in no fuel injection. As equivalence ratio is increased, static pressures are increased in the duct. In the similar equivalence ratio, static pressures are increased when total enthalpy is decreased. For reacting flow, the flame is occurred near the cavity. The combustion is weak locally in the middle of the duct. The up and down pressure distribution in the duct means that the supersonic combustion is generated.
공동 상류 경사 분사를 이용한 초음속 연소기의 실험적 연구, Part 1 : OH-PLIF 측정
정은주(Eunju Jeong),정인석(In-Seuck Jeung),Sean O’Byrne,A.F.P Houwing 한국연소학회 2007 한국연소학회지 Vol.12 No.1
The supersonic combustion experiments are carried out using T3 free-piston shock tunnel. Different shock tube fill pressures have various inflow conditions. 15˚ inclined hydrogen fuel injection is located before the cavity. Oblique shock is generated from the cavity and reflects off the top and bottom wall. For non-reacting flow, fuel makes the shear layer thicker above the cavity therefore, the shock is generated just before the trailing edge. This research has self-ignition in the combustor. For reacting flow, as the equivalence ratio increases, flame starts to generate near the injector or occur in the recirculation zone before the injector. High fuel injection sustains the jet shape in the cross flow and air can mix with fuel along the shear layer. Therefore, two flame layers find above the cavity for high equivalence ratio.
공동 내부로의 평행분사방법을 이용한 초음속 연소의 실험적 연구
정은주(Eunju Jeong),정인석(In-Seuck Jeung),Sean O"Byrne,A.F.P Houwing 한국연소학회 2007 한국연소학회지 Vol.12 No.2
The supersonic combustion experiments are carried out using T3 free-piston shock tunnel. Hydrogen Fuel is injected in the cavity parallel with air(or nitrogen) flow. The equivalence ratios in this study are 0.132 and 0.447. Experimental measurements use OH-PLIF near the cavity and pressures in the combustor. For parallel fuel injection case, direct fuel add into cavity leads to increase of cavity pressure. And Flame exists just near the bottom wall for low equivalent ratio. There is no flame in the cavity because of no mixing in it. Compared to the inclined fuel injection, ignition delay length is longer for low equivalence ratio in both case. OH distribution is not a single line but a repeatable fluctuation flame structure by turbulence. Pressure distributions have nothing to do with the fuel injection position.
공동 내부로의 평행분사방법을 이용한 초음속 연소의 실험적 연구
Jeong, Eun-Ju,Jeung, In-Seuck,O'Byrne, Sean,Houwing, A.F.P 한국연소학회 2007 한국연소학회지 Vol.12 No.2
The supersonic combustion experiments are carried out using T3 free-piston shock tunnel. Hydrogen Fuel is injected in the cavity parallel with air(or nitrogen) flow. The equivalence ratios in this study are 0.132 and 0.447. Experimental measurements use OH-PLIF near the cavity and pressures in the combustor. For parallel fuel injection case, direct fuel add into cavity leads to increase of cavity pressure. And Flame exists just near the bottom wall for low equivalent ratio. There is no flame in the cavity because of no mixing in it. Compared to the inclined fuel injection, ignition delay length is longer for low equivalence ratio in both case. OH distribution is not a single line but a repeatable fluctuation flame structure by turbulence. Pressure distributions have nothing to do with the fuel injection position.
상류 분사 공동 화염 지지부를 가지는 스크램제트 엔진에 관한 실험적 연구
정은주(Eunju Jeong),정인석(In-Seuck Jeung),Sean O"Byrne,A.F.P. Houwing 한국연소학회 2006 한국연소학회지 Vol.11 No.4
The model cavity scramjet engine experiments are carried out using T3 free-piston shock tunnel. Upstream hydrogen fuel is injected before the cavity with different injection pressure. OH planar laser-induced fluorescence is used to investigate the combustion zone and piezoelectric pressure transducers are used to define the pressure rise due to the combustion. Main combustion region is a mixing layer which is between air and fuel. Also high OH fluorescence signal is appeared in the shear layer above the cavity in high equivalence ratio. From the OH signal in the cavity, this fuel injection system can be a role as a flame-holder.