• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.381-385
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• 2005

Recently, spacecraft technology trends can be expressed three words, i.e. 'faster, cheaper and smaller'. Among these systems, micro propulsion device is an essential component. Also micro nozzle is the most important part in the micro propulsion device. In case of cold-gas thruster, micro nozzle converts the stored energy in a pressurized gas into kinetic energy through expansion ratio. In this paper we report characteristics of micro nozzle with throat expansion ratio and ratio of specific heats. We measure thrusts using strain gauge based thrust measurement system. We can estimate the micro nozzle performance through experiments.

• Journal of the Korean Society of Visualization
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• v.8 no.2
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• pp.31-39
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• 2010

Hysteresis is an effect by which the order of previous events influences the order of subsequent events. Hysteresis phenomenon of supersonic internal flows with shock waves has not yet been clarified satisfactorily. In the present study, experiments are carried out on internal flow in a supersonic nozzle to clarify the hysteresis phenomena for the shock waves. Flow visualization is carried out separately on the straight and divergent channels downstream of the nozzle throat section. Results obtained were compared with numerically simulated data. The results confirmed hysteresis phenomenon for shock wave in the Laval nozzle at a certain specific condition. The relationship between hysteresis phenomenon and the range of the rate of change of pressure ratio with time was shown experimentally. The existence of hysteretic behavior in the formation, both the location and strength, of shock wave in the straight part of the supersonic nozzle with a range of pressure ratio has also been confirmed numerically.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.323-326
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• 2006

This paper presents the computational results for the two-dimensional compressible non-reacted flow in a converging-diverging micro thrust nozzle of which the ratio of exit to throat width (0.541 in.) is 1.8. The RNG model is applied to calculate the turbulence by loading the standard coefficients. The results agreed very well with the experiments in the view of the shock structure and the pressure distribution at the various pressure ratios between the stagnation and the environmental states. The plume structures are also discussed on the view of the shock-cell structure.

• Proceedings of the KSME Conference
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• 2000.11b
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• pp.479-484
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• 2000

For the purpose of a cost effective design of practical subsonic/supersonic ejector systems, an experiment was carried out using a superheated steam as a primary driving flow. The superheated steam jet was produced by several different kinds of subsonic and supersonic nozzles. The secondary flow of atmospheric air inside a plenum chamber was drawn into the primary steam jet. The vacuum performance of the plenum chamber was investigated for a wide range of the ejector operation pressure ratio. The result showed that the static pressure of the mixed flow at the ejector throat is only a function of the ejector operation pressure ratio, regardless of the primary nezzle type employed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.357-361
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• 2010

When high-pressure gas is exhausted through nozzle exit to the atmosphere, expanded supersonic jet is formed with the Mach disk at a specific condition. In two-dimensional supersonic jets, the hysteresis phenomenon of the reflected shock waves is found to occur under quasi-steady flow conditions. Transitional pressure ratio between the regular reflection and Mach reflection in the jet is affected by this phenomenon. In the present study, experiments are carried out on internal flow in a supersonic nozzle to clarify the hysteresis phenomena for the shock waves and to discuss its interdependence on the rate of the change of pressure ratio with time. Flow visualization is carried out separately on the straight and divergent channels downstream of the nozzle throat section. The influence that the hysteresis phenomena have on the location of shock wave in a supersonic nozzle is also investigated experimentally.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.4
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• pp.392-398
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• 2009

Theoretical thrust equations for the diverse nozzle expansion condition were derived. By using the obtained thrust equations, parametric studies were carried out to estimate the effect of pressure exponent, minimum operation pressure, ambient pressure and extinguishment pressure on thrust modulation performance in pintle-nozzle solid rocket motors. Analysis results showed that thrust turndown ratio can be easily attained by small nozzle-throat area variation at high pressure exponent, low minimum operation pressure, high ambient pressure and high extinguishment pressure condition. At those conditions, the highest chamber pressure to obtain the intended thrust turndown ratio can be minimized.

• Journal of Advanced Marine Engineering and Technology
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• v.10 no.1
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• pp.74-84
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• 1986

Ejectors, having no moving, lubricating and leaking parats, are widely used as marine pumps because of its high working confidence. For instance, uses in ships are stripping in crude oil tank, bilge discharge in engine room, ballast water pumping on are carrier, and brine discharge from fresh water generator. And it is also used as cooling water recirculating pump in boiling water type nuclear reactor and deep-well pump. It is not easy to determine the optimal dimension for designing each ejector agreed with its suggested performance condition, because complicated calculations must be repeated to obtain the maximum efficiency affected by flowrate ratio, head ratio, area ratio and so on. Therefore, it is considered that the CAD (Computer-Aided Design) for ejector is a powerful method for design according to the individual design condition. In this paper, a computer program for water ejector design is developed based on the previous paper on theoretical analysis and experimental results for water ejector. And from the theoretical approach, an equation for the working limit and an equation for determing the shape of throat are obtained. The validity of the present computer program is sufficiently confirmed through the comparison of the computed results with the main dimension of the previous manufactured water ejector. This program will be easily developed as the CAD for various kinds of ejectors, including steam ejector.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.24 no.11
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• pp.1535-1539
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• 2000

A sonic nozzle is used as a reference flow meter in the area of gas flow rate measurement. The critical pressure ratio of sonic nozzle is an important factor in maintaining its operating condition. ISO9300 suggested the critical pressure ratio of sonic nozzle as a function of area ratio. In this study, 13 sonic nozzles were made by the design of ISC9300 with different half diffuser angles of 2。 to 8。 and throat diameters of 0.28 to 4.48 mm. The test results of half diffuser angles below 8。 ar quite similar to those of ISO9300. On the other hand, the critical pressure ratio for the nozzle of 8。 decreases by 5.5% in comparison with ISO9300. However, ISO9300 does not predict the critical pressure ratio at lower Reynolds numbers than 10(sup)5. Therefore, it is found that it is a better way for the flow of low Reynolds number to express the critical pressure ratio of sonic nozzle as a function of Reynolds number than area ratios. A correlation equation of critical pressure is introduced with uncertainty $\pm$3.2 % at 95% confidence level.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.627-630
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• 2009

Ejector system can induce the secondary flow or affect the secondary chamber pressure by both shear stress and pressure drop which are generated in the primary jet boundary. Ejectors are widely used in a range of applications such as a turbine-based combined-cycle propulsion system and a high altitude test facility for rocket engine, pressure recovery system, desalination plant and ejector ramjet etc. The primary interest of this study is to set up an configuration and operating conditions for an ejector in the condition of sonic and subsonic. Experimental and theoretical investigation on the sonic and subsonic ejectors with a converging-diverging diffuser was carried out. Numerical simulation was adopted for an optimal geometry design and satisfying the required performance. Also, some ejectors with a various of nozzle throat and mixing chamber diameter were manufactured precisely and tested for the comparison with the calculation results.

• Journal of the Korean Society of Laryngology, Phoniatrics and Logopedics
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• v.9 no.2
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• pp.115-127
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• 1998

Laryngopharyngeal reflux(LPR) is one firm of the gastroesophageal reflux diseases(GERD). It is known to cause various kinds of otolaryngologic symptoms such as hoarseness, foreign body sensation in throat, chronic throat clearing, chronic cough, etc. Disease entities diagnosed by otolaryngologists as posterior laryngitis, globus pharyngeus should be suspected as LPR-related diseases. In this multi-center trial, we tried to evaluate the effect of cisapride(10mg tid) on LPR-related symptoms as the part I study(CIS-KOR-051) in 19 centers, and as the part II study(CIS-KOR-052) comparative evaluation of effect between cisapride(10mg tid) and ranitidine(150mg bid) on LPR-related symptoms in 4 centers. In part I study, efficacy of cisapride on LPR-related symptoms after 4 weeks was 53.5% and that of after 8weeks was 77.9% in per protocol(PPA) analysis group. In part II study, efficacy of the cisapride was much better than that of ranitidine not only from 8 weeks trial(p<0.001) but also from 4 weeks trial(p<0.021) in PPA group. In the multiple logistic regression analysis among the parameters which affect the efficacy of the treatment, cisapride prescribed group showed 10 times greater than that of ranitidine prescribed group(p<0.0001, Odds ratio : 10) in PPA group. LPR was proved by 24Hr double probe pHmetry in 13 patients out of 19 patients tested(68.4%). Thus these results indicated that inducing the improvement of motility functions could affect the amelioration of the LPR-related symptoms much better than reducing acid secretion from the stomach. And maybe it suggests that LPR-related symptoms mainly developed by the reduced motility functions of the esophagus and/or delayed gastric emptying.