• Transactions of the Korean Society of Automotive Engineers
• /
• v.3 no.6
• /
• pp.250-261
• /
• 1995

In this study, a rapid compression and expansion machine(RCEM) equipped with a swirl generator was designed and developed, in order to clarify normal and abnormal combustion(knocking phenomena). This RCEM is intended to simulate combustion process in actual automotive S.I.engines, having a high reproducibility in the compression stroke. Flame propagation and autoignition processes associated with normal and abnormal combustion were captured by the high speed schlieren photography. And swirl intensity. equivalence ratio and ignition position were varied to investigate the effect of turbulence, concentration in the unburnt gas region and flame propagation length. The knock intensity, knock mass fraction and knock mass fraction after autoignition were calculated by use of history of measured cylinder pressure.

• Journal of Advanced Marine Engineering and Technology
• /
• v.28 no.4
• /
• pp.624-631
• /
• 2004

The experimental study on heat transfer characteristics of protruding heated block array as conducted to investigate and to compare the performance of impinging single circular jet in fully developed tube with a twisted tape as a swirl generator. The effects of jet Reynolds number(Re=8700, 13800, 20000. 26500), dimensionless jet-to-block distance(H/d=1. 3, 5. 7) and swirl number(S=0.11, 0.23, 0.30) of the swirl jet on the average Nusselt number for each block and all blocks have been examined. Measurements of heat transfer rate on block surfaces were used naphthalene sublimation technique. Mean velocity and turbulence intensity of the jet along the axis were measured. Potential core length of the jet was 5 times of nozzle diameter because it was fully developed and initially turbulent. With the twisted tape in the nozzle, heat transfer coefficients were higher than those without the twisted tape. which are mainly caused with increasing the jet Reynolds number and swirl number.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.34 no.4
• /
• pp.63-69
• /
• 2006

Experimental tests have been done with swirl injector and helical grain configuration to increase the regression rate of hybrid rocket solid fuel. Two types of injector were designed to evaluate the swirl effect of oxidizer stream on the increase in the regression rate. Results showed Type II injector with swirl number of 3.61 induced the better regression rate than Type I injector. Meanwhile, fuels with two different pitch number of 6 and 100 were used to analyzes the flow characteristics on the enhancement of regression rate. Test with fuels of pitch 6 showed better increase in the regression rate than in the pitch 100 when no swirler was imposed. This is due to the generation of strong turbulences in the oxidizer stream along the pitch 6 configuration. However, the regression rate could be increased further in the fuel with pitch 100 than with pitch 6 when swirl flow was imposed by Type II injector. This result implied that the fuel with pitch 100 could take a role of sustainer of the imposed swirl by swirler II instead of turbulence generator.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.11a
• /
• pp.594-596
• /
• 2010

Hot-firing tests were performed on a sub-scale gas generator for development of a 75 ton-class liquid rocket engine. This paper deals with the analysis results of low-frequency combustion instability that encountered during combustion tests of the gas generator.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.04a
• /
• pp.69-72
• /
• 2011

Hot-firing tests were performed on the third sub-scale gas generator for development of a 75 ton-class liquid rocket engine. This paper deals with the analysis results of low-frequency combustion instabilities that were encountered during combustion tests of the gas generator. The low-frequency pressure fluctuations seem to be related to chamber pressure and pressure drops through oxidizer/fuel injectors.

• Transactions of the Korean Society of Mechanical Engineers B
• /
• v.25 no.10
• /
• pp.1346-1354
• /
• 2001

The heat transfer characteristics off swirling air jet impinging on a heated flat plate have been investigated experimentally. The main object is to enhance the heat transfer rate by increasing turbulence intensity of impinging jet with a specially designed swirl generator. The mean velocity and turbulent intensity profiles of swirling jet were measured using a hot-wire anemomety. The temperature distribution on the heated flat surface was measured with thermocouples. As a result the swirl effect on the local heat transfer rate on the impinging plate is confined mainly in the small nozzle-to-plate spacings such as L/D<3 at the stagnation region. For small nozzle-to-plate spacings, the local heat transfer in the stagnation region is enhanced from the increased turbulence intensity due to swirl motion, compared with the conventional axisymmetric impinging jet without swirl. For example, the local Nusselt number of swirling jet with swirl number Sw=0.75 and Sw=1 is about 9.7-76% higher than that of conventional impinging jet at the radial location of R/D=0.5. With the increase of the nozzle-to-plate distance, the stagnation heat transfer rate is decreased due to the diminishing axial momentum of the swirling jet. However, the swirling impinging jet for all nozzle-to-plate spacings tested in this study does not enhance the average heat transfer rate.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.22 no.6
• /
• pp.56-63
• /
• 2018

In low swirl combustors the flame is lifted above the nozzle to achieve balance between the flame speed and velocity field at the exit of the nozzle. Characterization of the flame liftoff height is important because it affects the stability of the combustor and degradation of the nozzle material. In experiments, a counter-intuitive trend of flame liftoff heights with respect to inlet velocities was observed. To elucidate the complicated flow field in a low swirl combustor having swirl vanes and a turbulence generator, a series of numerical simulations of non-reacting flows was conducted by varying the inlet velocity. The flow structures at the exit of the nozzle with respect to the inlet velocities are investigated to support the observation in the experiments.

• Proceedings of the KSME Conference
• /
• 2007.05b
• /
• pp.2873-2878
• /
• 2007

The mixing vanes attached to the spacer grid of rod bundles are used to improve the heat transfer in heat exchanger devices by controlling the characteristics of the flow structures and turbulence. In this study, velocity patterns induced by two types of mixing vane(split and swirl vane) are measured by the PIV technique to better understand how to effect on the cross and secondary vortex flow patterns in $5{\times}$ rod bundle simulating the fuel assembly of the nuclear reactor. A successful measurement of the lateral velocity patterns was conducted using a specially designed beam sheet generator and experimental loop at KAERI. As the result, we found that for the cross flow between subchannels, the split vane is more effective than the swirl vane, while for the secondary vortex flow in each subchannel, the swirl vane's one is larger and longer than split vane's one.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.5 no.4
• /
• pp.83-93
• /
• 2001

A swirler with turbulence generator is designed and manufactured for generating many small-scale eddies in the combustor which contribute to enhancing mixing effect between fuel and air. The method results in not only the disadvantage of pressure loss but also the advantage of promoting combustion and reducing NOx. For the purpose of the study, four kinds of swirler with different turbulence generator area (0%, 3%, 7%, and 12% of reducing flow area) are designed to confirm the effect of mixing according the variation in the area of the turbulence generator. The mixing of combustor in the radial direction is significantly improved and the distributions of flames and temperature are well distributed throughout the cross section of a combustor as area of swirl generator is increased.

• Journal of Advanced Marine Engineering and Technology
• /
• v.18 no.4
• /
• pp.94-101
• /
• 1994

실험 데이터는 급확대비 3:1 팽창의 시험관에서의 실험결과를 나타내고 있으며, 실험에 이용된 동작유체로써는 공기가 사용되었다. 입구관에서 레이놀즈수는 60,000으로부터 120,000까지 변하게 하였고, 스월강도는 0으로부터 16까지 변화되게 하였다. 균일한 열 플럭스 경계조건이 사용되었는데, 그 결과 관벽온도 및 체적온도는 24$^{\circ}C$로부터 71$^{\circ}C$까지에 걸쳐 나타났다. 플롯상에 국소 Nusselt수는 최대 열전달점에서 정점을 이루는 모습을 보여 주고 있다. 스월강도가 0으로부터 최대값으로 증가 되었을때, 최고 Nusselt수의 위치는 시험관에서 4로부터 1스텝 하이트로 변경되는 것이 조사되었다. 이러한 최대 Nusselt수의 상류부 이동은 완전 발달된 유동에서의 값보다 2.2배에서 8.8배나 많은 그의 크기를 증가시킨다고 할 수 있다.