• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.2
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• pp.19-27
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• 2002

The smokeless liner, was required to propulsion system of gas generator, was developed by appling oxamide as a filler and HTPB system as a binder. Relative quantities of smoke produced during burning of liner by propellant combustion was measured by using smoke chamber. The smoke of the smokeless liner containing 50% of oxamide as filler was reduced to 1/10 as compared with conventional liner containing silica as filler. This result was showed by ground test of gas generator.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.04a
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• pp.25-25
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• 2000

가스발생기와 같이 로켓모터에서 추력이 아닌 기체압 형태의 에너지를 일정한 시간동안 얻고자 하는 경우, 로켓모터의 크기 및 추진제 충전율을 고려하여 그레인 형태를 단면 연소형으로 선택할 수 있다. 단면 연소형 그레인을 가진 로켓모터는 그레인의 연소시, 일찍 연소된 부분의 라이너가 추진제 연소 화염에 노출되면서 표면부터 서서히 분해가 진행되며, 분해물질의 일부는 추진제에 포함된 산화제 성분에 의해 산화되어 기체화 될 수 있다. 산화제 성분이 충분치 않은 경우에는 고체 입자 형태로 추진제 연소 기체와 함께 배출되며, 이는 일차연기(primary smoke)의 일종으로 볼 수 있다. 가스 발생기에서 얻고자 하는 기체는 고체 입자가 포함되지 않은 깨끗한 기체형태인 경우가 대부분이며, 따라서, 무연 라이너 및 내열재의 연구가 필요하다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.254-257
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• 2017

As a part of the development of aircraft gas turbines, combustion performance tests have been conducted in the single combustor sector. The effects of change in the amount of air supplied to the main combustion zone to the performance of the combustor, such as a pollutant emission, a liner temperature distribution and an exit temperature patterns, were studied. Emissions of CO and NOx increased with the main air-ratio and exit temperature pattern was improved. When changing the pattern of the dilution holes, it was shown that the temperature patterns on the exit plane of the combustor and the surface of liner changed depending on the main flame structure and mixing with diluent air. These observations will be applied to combustor liner designs to improve combustor durability and emissions reduction performance.

• 한국연소학회:학술대회논문집
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• 2014.11a
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• pp.239-242
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• 2014

• Proceedings of the KSME Conference
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• 2008.11b
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• pp.2862-2867
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• 2008

High-temperature components of gas turbine operated for certain period of time can be reused by being repaired or rejuvenated. In case of the gas turbine combustion liners, the biggest and the most important one in the high-temperature components, come in a repair shop after operated for 8,000 or 12,000 hours according to the model and go through the repair and rejuvenation in order to be reused. A stated combustion liner is the first channel which has the combustion gas reached a nozzle from a fuel nozzle. Materials and coating properties of old and new model combustion liners were investigated. To repair these components after the visual inspection, the coatings of combustion liners were removed and then FPI(Fluorescent Penetrant Inspection), a kind of the NDI(Non-Destructive Inspection), was conducted. Damage patterns and the number of the damaged components were classified and analyzed based on data provided from the visual inspection over a long period of time. Focusing on the difference between old model and new model combustion liners, we analyzed the damage distribution and changes and consequently concluded that new model combustion liner would increase repair rate.

• 한국연소학회:학술대회논문집
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• 1997.06a
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• pp.135-151
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• 1997

The preliminary design and performance test for determining dimensions of gas turbine combustor were investigated. The combustor design program was developed and applied to design our combustor. and detailed design for determining of swirler. dome and liner holes were performed experimentally. The swirler. which govern the combustion characteristics of combustor, was determined $40^{\circ}$ as swirl angle at first performance test. After second performance test the swirler was re-determined by 24 mm i.d.. 34 mm o.d., and swirl angle of $45^{\circ}$. The geometry of liner holes were determined by considering the flame stability and recirculation zone size. It was found that flame can be more easily stabilized by adjusting the swirier dimensions rather than liner holes. The geometry of swirler and liner holes were re-determined by final performance test with dilution holes. Also. the performance of combustor was evaluated by analysis of exhaust gases.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.149.1-149.1
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• 2012

고성능 다단연소싸이클 엔진은 산화제과잉 예연소기를 사용한다. 예연소기 후류에 위치한 배관 및 연소기 헤드 등은 고온/고압 산화제 과잉 환경에 놓이게 되며, 운용 조건에서는 국부적으로 온도를 상승시키는 외부 발화제에 의하여 녹는점보다 낮은 온도에서 재질이 발화될 수 있다. 따라서, 이러한 환경에 적합한 재질 및 코팅은 내산화성, 내인화성 및 자발화성도 중요하나, 외부 발화제에 의한 내발화성이 가장 중요한 특성이 된다. 여기서는 이러한 환경에 적합하며 지상 시험용 노즐 및 배관에 적용될 수 있는 재질 및 코팅에 대하여 조사한다. 러시아는 이미 이러한 환경에 적합한 재질 및 코팅들을 개발하여 RD-170, 180에 적용 중이다. 그러나 미국은 최근에 이러한 연구를 시작한 것으로 추정된다. 따라서 자료 접근이 가능한 범위에서 러시아의 재질 및 코팅을 조사하며, 미국 자료에서는 산소 시스템 안전 등과 같이 간접적인 자료들을 통하여 대체가 가능한 후보 재질 및 코팅을 조사한다. 다단연소싸이클 연소시험 배관에 적용할 수 있는 방법은 다음과 같다. 코팅 없이 Monel K500을 사용하거나, OFHC 혹은 Ni 라이너에 고강도 외피를 사용하는 방법이 있으나, 두 방법 모두 재질의 가격 및 수급, 라이너 적용 방법 등이 어려울 수 있다. 국내에서 산화제과잉 가스 환경에서 적용할 수 있는 법랑을 개발하거나 수급이 용이한 법랑을 찾아 오스테나이트 스테인리스강에 적용하는 방법이 있다. 이 방법은 외부 발화제에 대한 내발화성을 증가시키는 경제적이고 용이한 방법으로 판단된다.

• Aerospace Engineering and Technology
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• v.11 no.2
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• pp.57-64
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• 2012

Although the APU combustors were developed successfully, it could face many unexpected hardships in an engine or a system operating under the severe environments. But, it is not easy to change the combustion field or combustor structure at the engine/system development stage. So we must suggest practical ways to optimize the value quantitatively by engine test and flow analysis, and verify those by the cyclic test. This paper describes reverse-annular type combustor troubleshooting processes for verifying and settling of the problems and issues occurred in various engine and system operation tests by experiment and analysis.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.37 no.2
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• pp.161-170
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• 2013

The flow and combustion characteristics in a premixed swirl combustor with a double cone burner are numerically analyzed to adopt a swirler model. The internal recirculation zone formed at the burner exit can be realized by a swirler with inner and outer diameters of 56 and 152 mm, respectively, and accordingly, the flow rate and radial velocity were determined. To select the tangential velocity, swirl and recirculation angles are introduced. A tangential velocity of 40 m/s produces an internal recirculation zone similar to that in a combustor. At the liner exit, the errors in temperature and velocity are 2.8% and 0%, respectively, and they are negligibly small. However, NOx emissions are underestimated by 67% in the numerical results obtained using the swirler model. Although considerable quantitative errors are induced by the swirler model, it can be useful numerical model for the EV burner because it can approximately simulate the essential flow and combustion characteristics in a premixed swirl combustor with a double cone burner and it is expected to make combustion analysis efficient in a gas turbine combustor with complex geometries.

• Proceedings of the KSME Conference
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• 2000.11b
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• pp.142-149
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• 2000

The results of stand and field testing of a combustion chamber for a heavy-duty 150 MW gas turbine are discussed. The model represented one of 14 identical segments of a tubular multican combustor constructed in the scale 1:1. The model experiments were executed at a pressure smaller than in the real gas turbine. The combustion efficiency, pressure loss factor, pattern factor, liner wall temperature, flame radiation, fluctuating pressure, and NOx emission were measured at partial and full load for both model and on-site testing. The comparison of these items of information, received on similar modes in the stand and field tests, has allowed the development of a method of calculation and the improvement of gas turbine combustors.