Supersonic Combustion with Supersonic Injection Through Diamond-Shaped Orifices

Tomioka, Sadatake; Kohchi, T.; Masumoto, Ryota; Mizumikawa, M.; Matsuo, Akiko

doi:10.2514/1.55960

Cited by 2 publications

(2 citation statements)

References 17 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In contrast to hydrogen, hydrocarbon fuels package better, exhibiting a greater energy per unit volume, so that they require less room onboard than hydrogen fuel for an equivalent amount of energy [7]. And now, to model the performance of a dual-mode scramjet engine, the heat release distribution must be accurately predicted, because the heat release distribution have an influence on the thermal choking point, the profiles of pressure and Mach number et al Tomioka et al carried out dual-mode combustion tests with hydrogen fuel injection in diverging section and a one-dimensional calculation to estimate combustion efficiency [8]. In hydrogen fuel, the combustion efficiency can be expressed as fuel consumption rate, because most of combustion products of hydrogen fuel are water vapor.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Ethylene Fuel Combustion in a Dual-Mode Combustor

Nojima¹,

Suzuki²,

Tomioka³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

View full text Add to dashboard Cite

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 H 2 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. NomenclatureA = cross-sectional area H = lower heating value M = Mach number P = pressure T = Temperature Y i = mass fraction of chemical species i x = streamwise location from onset of duct divergence y = spanwise location from center of the duct z = height from center of the duct η c = local combustion efficiency Φ = bulk fuel-equivalence ratio = local fuel-equivalence ratio * Graduate Student, Department of Aerospace Engineering. Student Member AIAA. † Graduate Student, Department of Aerospace Engineering.

show abstract

Section: Introductionmentioning

confidence: 99%

Investigation of Ethylene Fuel Combustion in a Dual-Mode Combustor

Nojima¹,

Suzuki²,

Tomioka³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

View full text Add to dashboard Cite

show abstract

“…to penetrate the fuel into the supersonic main flow, 16 b) how to spread the fuel in the flow by generating vertical vortex, 17 and c) others. It is needed to improve the fuel injection in order to increase and confirm the engine performance.…”

mentioning

confidence: 99%

Virtual Experiment for Optimization of Fuel Distribution in a Scramjet Engine

Sato¹,

Fukui²,

Watanabe³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

View full text Add to dashboard Cite

Japan Aerospace Exploration Agency (JAXA) has been investigating scramjet engines in KakudaSpace Center using RamJet Engine Test Facility (RJTF) et al. The engine tested at the flight condition of Mach 6 showed very steep fuel distribution. The authors are researching the influence of shock wave from strut-cowl system on the fuel distribution by using CFD based on RJTF tests, and have found advantages of strut in the engine. Here describe the authors the result of virtual experiments for optimization trial of fuel distribution in the engine by means of tracing back along streamlines in the view point where to set the fuel injection positions in order to let the fuel go into high mass flux area in the engine.Ⅰ．Introduction n hypersonic air-breathing engine researches many different trials have been done in order to obtain better propulsion performance or to create new systems. 1-4 In Japan since around 1985 National Aerospace Laboratory (present JAXA) has been carrying out scramjet engine research, and Ramjet Engine Test Facility (RJTF) was built in Kakuda Research Center (present Kakuda Space Center) in 1993 for the research.Kakuda Space Center has been conducting the scramjet engine tests for flight condition of Mach 4, 6, 8 and the higher in RJTF and another facility respectively. [5][6][7][8][9][10][11][12][13][14][15] In the scramjet engine tests carried out in the RJTF it has been found that the difference of engine inner configuration, mainly strut shape, produces large difference of thrust performance in the condition of Mach 6. 5 In addition to the above it has been also found that the fuel cannot spread all over the engine cross section and concentrates to the top wall side. 5 Some fraction of the fuel is exhausted without burning and does not contribute the thrust production. This prevents the engine from fully performing. Optimization for the fuel distribution is needed.In this viewpoint researches have been made on fuel injection for scramjet engines. Roughly classifying, they are a) how I 1 Senior Researcher,

show abstract

Supersonic Combustion with Supersonic Injection Through Diamond-Shaped Orifices

Cited by 2 publications

References 17 publications

Investigation of Ethylene Fuel Combustion in a Dual-Mode Combustor

Investigation of Ethylene Fuel Combustion in a Dual-Mode Combustor

Virtual Experiment for Optimization of Fuel Distribution in a Scramjet Engine

Contact Info

Product

Resources

About