| Autor: |
Noboru Sakuranaka, Kiyoshi Nojima, Yu Suzuki, Sadatake Tomioka |
| Rok vydání: |
2014 |
| Předmět: |
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| Zdroj: |
50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. |
| Popis: |
Experiments and a quasi-one-dimensional equilibrium calculation were conduced to estimate performances of a dual-mode combustor with ethylene fuel injection in a directconnect wind-tunnel facility in JAXA Kakuda Space Center (JAXA-KSPC). In the facility, a gaseous H2 fueled lean combustion heater was used to make high enthalpy flow. The high enthalpy flow was then accelerated with a Mach 2.5 supersonic nozzle. The experiments were executed with a rectangular dual-mode combustor with constant area section and following diverging section at various fuel equivalence ratios. Fuel injectors upstream of cavity flameholders were installed in the constant area section and the diverging section on opposite walls. Heat flux distributions in the streamwise were measured using heat flux transducers mounted flush with the combustor inner wall. The compositions of gas at the exit cross-section of the combustor were sampled using a water-cooled reaction-quench sampling probe. The compositions of sample gas were eccentrically located on the fuel injection side under both of scramjet and dual-mode operation. Therefore, there is a need to consideration of the non-uniformity to estimate state quantities like combustion efficiency and heat flux by quasi-one-dimensional calculation. Heat flux distributions calculated using the “two-flow tubes model” indicated good agreement to measured heat flux. The combustion efficiency defined as the fraction of the oxygen rate that reacted over the total oxygen flow rate was closer to the experimental value than that defined as the fraction of the reacted fuel rate. |
| Databáze: |
OpenAIRE |
| Externí odkaz: |
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