• Journal of ILASS-Korea
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• v.13 no.3
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• pp.149-155
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• 2008

An experimental study was performed to understand spray characteristics of the rotary atomizer for the slinger combustor. In this fuel injection system, fuel is injected and atomized in the combustor by centrifugal forces to engine shaft. The experimental apparatus consists of a high speed rotational spindle, rotary atomizer, pressure tank and acrylic case. The droplet size and velocity were measured by PDPA (phase Doppler particle analyzer), and spray was visualized by using high speed camera and Nd:Yag laser-based flash photography. From the test results, the droplet size (SMD) is largely affected by rotational speed, mass flow rate and the number of orifice. As the experimental results, we could understand the spray characteristics of the rotary atomizer for the slinger combustor and obtain the optimum shape of the rotary atomizer which is suitable for the small gas turbine engine.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.149-152
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• 2008

A slinger combustor which can be applied to micro turbojet engine has been developed with the combustor rig test. A rotating fuel injector with high speed rpm was designed, manufactured and tested to apply into slinger combustor through spray test and adequate droplet size and spray distribution were achieved. The CFD was used to analyze internal flow of the combustor. We found out that the combustor shows 11.2% of pressure loss and 99.8% of combustion efficiency at full combustor rig test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.2
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• pp.68-74
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• 2006

An experimental study was carried out to investigate the combustion characteristics of the slinger combustor. A combustion test rig was manufactured and installed in KARI combustor test facility. From the ignition test results, we found that there were two major factors influencing the ignition limits; by increasing the rotational speed and the air mass flow rate, a better ignition performance was attained. From the combustion test results, we obtained 99.6% combustion efficiency, 15% pattern factor, and 3% profile factor. The results in this work indicate that the ignition and combustion characteristics of a slinger combustor are markedly different from those of a conventional annular combustor.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.173-178
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• 2003

The study was performed to understand combustion characteristics of the slinger combustor. Liquid fuel is discharged radially outwards through injection holes drilled in the high speed rotating shaft. We observed atomizing characteristics with variation of fuel nozzle rotating speed by using PDPA system. The mean drop diameter highly depends on fuel nozzle rotating speed. In KARI combustion test facility, Ignition and combustion tests were performed by using real scale combustor. In the test results, ignition and combustion efficiency were increased according to increasing fuel nozzle rotating speed. The measured radial temperature distribution at the combustor exit shows stable and fairly good distribution.

• 한국전산유체공학회:학술대회논문집
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• 2008.03a
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• pp.155-158
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• 2008

A practical modeling approach of a small slinger combustor is proposed and a 2-dimensional axisymmetric computational model is developed. Based on numerical results from the full 3-dimensional configuration, model reduction is achieved toward 2-dimensional axisymmetric configuration. By simplifying the complex model, computing time can be significantly reduced and it makes easy to find effects of geometry modification. Numerical results show that the flow characteristic of 2-D model is quite similar to that of the 3-D configuration.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.1
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• pp.38-43
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• 2004

The study was performed to understand combustion characteristics of the slinger combustor. Liquid fuel is discharged radially outwards through injection holes drilled in the high speed rotating shaft. The spray test was peformed to verify atomizing characteristics with variation of fuel nozzle rotational speed by using PDPA system. SMD was measured at different RPM and values are 70$\mu\textrm{m}$ at 5,000RPM rpm, 60$\mu\textrm{m}$ at 10,000RPM and 40$\mu\textrm{m}$ at 20,000RPM. In the results, we found out that SMD is grown smaller with increasing rotational speed. In KARI combustion test facility, Ignition and combustion tests were performed by using combustor test rig. In the test results, ignition and combustion efficiency were improved according to increasing rotational speed. The measured radial temperature distribution at the combustor exit shows stable and fairly good distribution.

• 한국연소학회:학술대회논문집
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• 2012.11a
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• pp.287-289
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• 2012

The research and development history of the gas turbine combustor in Korea is introduced briefly. It is very important to understand the fuel spray, mixing phenomena in achieving combustion performance. In this paper, two kinds of fuel injection system such as duplex fuel injector and rotary spray system are introduced in developing gas turbine combustor in Korea. The extensive experimental research of fuel spray, ignition, performance and endurance rig test makes gas turbine combustor successfully in Korea.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.309-312
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• 2005

High altitude ignition test was performed to understand high altitude ignition characteristics of slinger combustor. To verify ignition limits, test was carried out with variation of altitude and fuel nozzle rotational speed using AETF(Altitude Engine Test Facility) in KARI(Korea Aerospace Research Institute). From the result, the effect of major factors which affect on ignition characteristics was observed. The reduction of ignition limit with increasing altitude and expansion of ignition limit with increasing rotational speed of fuel nozzle was verified. Also minimum rotational speed of fuel nozzle at high altitude must be greater than that of seal level condition.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.4
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• pp.59-70
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• 2021

An experimental study was conducted to observe the spray characteristics for different flow rates and rotating speeds of a rotating fuel nozzle of a slinger combustor. The water spray ejected from the nozzle orifice was visualized using a high-speed camera and a light source. It was confirmed that the atomization was improved, as the flow rate decreased and rotating speed increased. The characteristic maps for the spray characteristics and performance parameters showed that the aerodynamic Weber number and the liquid-air momentum flux ratio were associated with the liquid primary breakup, and the liquid-air momentum flux ratio and Rossby number were closely correlated with the liquid ejection mode.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.354-358
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• 2007

An experimental study was performed to understand spray characteristics of the slinger injector. system for the micro turbojet engine. In this fuel injection system, fuel is sprayed and atomized in the combustor by centrifugal forces of engine shaft. This experimental apparatus consist of a high speed rotating Spindle, slinger injector, pressure tank and acrylic case. The droplet size and velocity were measured by PDPA(Phase Doppler Particle Analyzer) and spray was visualized by using Nd-Yag laser-based flash photography. From the test results, the droplet size(SMD) is largely affected to rotational speed, mass flow rate and the number of injection orifice. From the this experimental study, we could understand the spray characteristics of the slinger injection system and obtain the optimum shape of the slinger injector nozzle which is suitable for the micro turbojet engine.