• 설비공학논문집
• /
• 제21권2호
• /
• pp.126-130
• /
• 2009

The present study describes an investigation into the characteristics of combustion oscillation and its suppression instability of a silo type gas turbine combustor in commercial power plant. Combustion oscillation is occurred the combustor in near full load during operation. As a result of FFT analysis of the combustion dynamics, the frequency of the oscillation is analyzed as the 1'st longitudinal mode of acoustic resonance of the combustor. For suppress of the instability, combustion tuning with adjust of fuel valve schedule is carried out, which changes equivalent ratio of each burners. As the result, the oscillation is successfully reduced with meeting the level of NOx emission regulation.

• 한국연소학회지
• /
• 제9권2호
• /
• pp.18-29
• /
• 2004

Partial quenching structure of diffusion flames in a turbulent mixing layer has been investigated by the method of flame hole dynamics in oder to develope a prediction model for the phenomenon of turbulent flame lift off. The present study is specifically aimed to remedy the shortcoming of the stiff transition of the conditioned partial burning probability across the crossover condition by employing the level-set method which enables us to include the effect of finite flame edge propagation speed. In light of the level-set simulation results with two models for the edge propagation speed, the stabilizing conditions for turbulent lifted flame are suggested. The flame hole dynamics combined with the level-set method yields a temporally evolving turbulent extinction process and its partial quenching characteristics is compared with the results of the previous model employing the flame-hole random walk mapping based on three critical scalar dissipation rates. The probability to encounter reacting state, conditioned with scalar dissipation rate, demonstrated that the conditional probability has a rather gradual transition across the crossover scalar dissipation rate. Such a smooth transition is attributed to the finite response of the flame edge propagation.

• 한국자동차공학회논문집
• /
• 제17권4호
• /
• pp.63-71
• /
• 2009

The elastic effects of the valve train components are analyzed by using the finite element models of the rocker arm and valve. The whole equations of motion of the valvetrain of an internal combustion engine formulated by finite element techniques are solved by imposing the contact conditions with the augmented Lagrange multiplier method. The velocity and acceleration constraints as well as the displacement constraints are imposed on the contact points. The numerical simulations show that, even if the magnitude of the elastic deformation of the components is very small, it may have large effects on the valvetrain dynamics of a high-speed engine.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2008년도 제31회 추계학술대회논문집
• /
• pp.447-448
• /
• 2008

The goal of this study is to find flame dynamic behavior using a transverse fuel injection in a model combustor, and is to investigate main causes of unstable combustion in a liquid-fueled combustor. For transverse fuel injection into air cross flow, spray result shows similar tendency with Wu et al.[1998] until spray arrives at flame-holder. However, passing through flame-holder, fuel inflow into recirculation region of flameholder is not sufficient so it makes large difference between shear flame and recirculation flame behind flameholder. In combustion tests, the stable flame shows a kind of shear flames and low peaks of dynamic pressure frequencies. On the other hand, unstable flame shows periodic detached flame in recirculation zone and a strong peak of dynamic pressure frequency. The instability frequency is highly affected by influx air velocity, air temperature, equivalence ratio and wake or vortex shedding frequency behind the flameholder.

• 한국자동차공학회논문집
• /
• 제16권6호
• /
• pp.74-80
• /
• 2008

A combustion of CAI engine is purely dominated by fuel chemical reactions. In order to simulate the combustion of CAI engine, it should be considered the effect of fuel components and chemical kinetics. So it needs enormous computational power. To overcome this problem reduced problem of needing massive computational power, chemical kinetic mechanism and multi-zone method is proposed here in this paper. A reduced chemical kinetic mechanism for a gasoline surrogate was used in this study for a CAI combustion. This gasoline surrogate was modeled as a blend of iso-octane, n-heptane, and toluene. For the analysis of CAI combustion, a multi-zone method as combustion model for a CAI engine was developed and incorporated into the computational fluid dynamics code, STAR-CD, for computing efficiency. This coupled multi-zone model can calculate 3 dimensional computational fluid dynamics and multi-zoned chemical reaction simultaneously in one time step. In other words, every computational cell interacts with the adjacent cells during the chemical reaction process. It can enhance the reality of multi-zone model. A greatly time-saving and yet still relatively accurate CAI combustion simulation model based on the above mentioned two efficient methodologies, is thus proposed.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2003년도 제20회 춘계학술대회 논문집
• /
• pp.127-130
• /
• 2003

This paper presents the numerical thermal analysis for regeneratively cooled rocket thrust chambers. An integrated numerical model incorporates computational fluid dynamics for the hot-gas thermal environment, and thermal analysis for the liner and coolant channels. The flow and temperature fields in rocket thrust chambers is assumed to be axisymmetric steady state which is presumed to the combustion liner. The heat flux computed from nozzle flow is used to predict the temperature distribution of the combustion liner. As a result, we present the wall temperature of combustion liner and the temperature change of coolant.

• 한국연소학회지
• /
• 제20권4호
• /
• pp.10-18
• /
• 2015

Combustion instability is a major issue in design and maintenance of gas turbine combustors for efficient operation with low emissions. With the thermoacoustic view point the instability is induced by the interaction of the unsteady heat release of the combustion process and the change in the acoustic pressure in the combustion chamber. In an effort to study the combustion dynamics of gas turbine combustors, Morgans et al (2014) have developed OSCILOS (open source combustion instability low order simulator) code and it is currently available online. In this study the code has been utilized to predict the combustion instability of a reported case for lean premixed gas turbine combustion, and then its prediction results have been compared with the corresponding experimental data. It turned out that both the predicted and the experimental combustion instability results agree well. Further the effects of some typical inlet acoustic boundary conditions on the prediction have been investigated briefly. It is believed that the validity and effectiveness of the open source code is reconfirmed through this benchmark test.

• 한국정밀공학회:학술대회논문집
• /
• 한국정밀공학회 2013년도 춘계학술대회 논문집
• /
• pp.1201-1202
• /
• 2013

• 대한기계학회논문집B
• /
• 제38권9호
• /
• pp.773-779
• /
• 2014

가스터빈 희박 예혼합 연소기에서 발생하는 연소 불안정 현상을 모델링하기 위해서는 화염의 동 특성에 대한 정량적, 정성적 분석이 필수적이다. 이를 위하여 화염전달함수가 전산유체역학을 통하여 모델링되었다. 기존 화염전달함수의 연구 결과로부터, 화염전달함수의 결과는 화염의 구조에 크게 의존하는 것으로 알려졌다. 본 연구에서는 실제 계측된 화염의 구조와 유사한 형상을 갖도록 열전달 조건을 최적화한 후, 동일 조건에서 화염전달함수가 모델링되었다. 화염의 형상을 정확하게 예측할 수 있다면, 이로부터 전달함수의 이득값과 위상차의 모델링 결과 역시 실험값과 유사한 거동을 확인할 수 있었다.

• 에너지공학
• /
• 제23권3호
• /
• pp.203-210
• /
• 2014

본 연구에서는 목재펠릿보일러의 연소현상에 대하여 이론적으로 분석하고 예측 값과 실제 실험데이터를 비교하여 분석했다. 목재펠릿보일러의 개발과정에 있어서 연소실형상, 투입 공기의 속도, 연료의 양, 온도 및 연료특성 등에 따라 다양한 문제점이 발생됨에 따라 여러 방향의 연구 개발이 이루어지고 있으며 이에 많은 시간과 비용이 소모되고 있다. 따라서 해석모델의 개발을 통한 수치해석 방법이 유용하게 활용될 수 있다. 본 연구에서는 전산유체역학(Computational Fluid Dynamics, CFD)을 이용한 모의실험(Simulation)을 통하여 목재펠릿의 종류 및 구성 원소의 변화에 따른 목재펠릿보일러의 연소실 출구온도 및 배기가스의 구성성분을 예측하고자 하며 그 결과를 바탕으로 목재펠릿 연소특성을 파악하여 최적의 이용 및 활용방법을 제시하고자 한다. 예측값과 실험값은 : $CO_2$ 0.60 % $O_2$ 0.73 % 오차를 나타내었다.