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보조동력장치용 환형 역류형 연소기 (TS2) 성능 시험
고영성,한영민,이강엽,양수석,이대성,Ko, Young-Sung,Han, Yeoung-Min,Lee, Kang-Yeop,Yang, Soo-Seok,Lee, Dae-Sung 대한기계학회 2002 大韓機械學會論文集B Vol.26 No.6
Development of a small gas-turbine combustor for 100㎾ class APU(Auxiliary Power Unit) has been performed. This combustor is a reverse-annular type and has a tangential swiller in the liner head to improve the fuel/air mixing and flame stability. Three main and three pilot fuel injectors of the simplex pressure-swirl type are used. The performance target at the design condition includes a turbine inlet temperature of l170k, a combustion efficiency of 99%, a pattern factor of 30%, and an engine durability of 3000 hours. Under developing the combustor, we conducted the performance test of our first prototype(TS1) with some variants. As a result of the test, the performance targets of the combustor are satisfied except that the pattern factor is about 4% higher than the target value. Therefore, the second prototype(TS2) was redesigned and the performance test was conducted with the critical focus on the pattern factor and the exit mean temperature. We adopted TS2 four variants to check the improvement of the pattern factor. As a result, the pattern factors of several variants were satisfied with the performance target. Finally, the TS2A variant was chosen as a final combustor fur our APU model.
박상수(Sang Soo Park),신동해(Dong Hae Shin),오정화(Jeong Hwa Oh),진솔(Sol Jin),승아현(A Hyeon Seung),고영성(Young sung Ko) 한국추진공학회 2019 한국추진공학회 학술대회논문집 Vol.2019 No.5
한국형 발사체 75 ton 연소기의 공진 주파수를 모사하기 위한 비원통형 가진장치 및 가진 시퀀스 검증을 위해 고온/저압(10 bar) 환경에서의 가진 시험을 진행하였다. 가진 시퀀스 설정을 위해 사전 테스트를 수행하였고, 가장 유해한 주파수로 알려진 1T 모드 모사를 위한 가진 시퀀스를 설정하였다. 가진장치 및 시퀀스의 검증을 위해 연소를 동반한 가진 시험을 수행하였다. 검증은 오차범위 5% 이내에서 공진 주파수 모사에 성공하였다. 이를 통해 가진장치 및 시퀀스의 검증을 완료하였다. 추후 본 연구의 데이터를 바탕으로 설계압인 60 bar에서 가진시험을 수행하도록 하겠다. A non-circular excitation device for simulating the resonance frequency of a Korean launch vehicle 75tons combustor and excitation tests were carried out in a high temperature/low pressure(10 bar) environment for the excitation sequence verification. We conducted a preliminary test to set up the sequences and set up an excitation sequence which is known as the most harmful frequency for simulating 1T mode. An excitation test with combustion was carried out for verification of the excitation device and sequence. Verification succeeded in simulating the resonance frequency within the error range of 5%. Through this, verifications of the excitation device and sequence have been completed. based on the data of this study, we will carry out the excitation test with the designed pressure of 60 bar.
한영민,고영성,양수석,이대성,Han, Yeoung-Min,Ko, Young-Sung,Yang, Soo-Seok,Lee, Dae-Sung 대한기계학회 2002 大韓機械學會論文集B Vol.26 No.8
In this paper, the test results of the combustion for 2 IAFR lean fuel models are described. The need for the low emission combustor has been issued from the concern on the increase of green house and the destruction of ozone layer. To evaluate the flow and combustion performance of newly designed 21AFR lean modules, the hydraulic tests in stereolithographic airflows models, the low pressure combustion tests in three injectors model for weak extinction and ignition and the high pressure combustion tests in single sector for NOx, SAE and efficiency are performed. The low pressure tests reveal that the governing parameters in weak extinction and ignition at atmospheric condition are prefilmer length, swirl flow rotation direction, secondary swirl angle and flow split. As a result of combustion test at high pressure, the efficiency and smoke level are satisfied with performance targets, but EINOx of 17.8 is higher than target value of 13.1 The high pressure tests show that the main parameters influenced on NOx are primary swirl angle, swirl flow rotation direction, heatshield exit angle and liner mixing hole location.
박상수(Sang Soo Park),신민규(Min Kyu Shin),오정화(Jeong Hwa Oh),진솔(Sol Jin),조영석(Yeong Suk Cho),고영성(Young sung Ko) 한국추진공학회 2019 한국추진공학회 학술대회논문집 Vol.2019 No.5
한국형 발사체 75 ton 연소기의 공진 주파수를 모사하기 위해 제작한 비원통형 연소기를 이용하여 저압 연소시험을 진행하였다. 본 연구에서는 원통형 연소실이 아닌 비원통형 연소실을 사용하며, 고압(60 bar)에서의 연소시험을 통해 최종적으로 연소불안정 현상을 모사하는 것이 목표이다. 따라서 고압에서의 안정적 연소시험을 위해 저압에서 연소 시퀀스의 검증이 반드시 필요하다. 안정적인 이차유동 공급을 위해 설비를 수정하였고, 사전 테스트를 통해 효과를 입증하였다. 또한 연소시험을 통해 안정적 연소를 확인하였고, 연소 시퀀스를 확립하였다. 추후 본 시퀀스를 바탕으로 설계압인 60bar에서 연소시험을 수행할 예정이다. A low - pressure combustion test was conducted using a non - cylindrical combustor designed to simulate the resonance frequency of a Korean launch vehicle 75 ton combustor. In this study, it is aimed to simulate the combustion instability by conducting the combustion test at high pressure(60 bar) using a non-cylindrical combustion chamber rather than a cylindrical combustion chamber. Therefore, it is essential to verify the combustion sequence at low pressure for stable combustion test at high pressure. The liquid nitrogen supply system was modified to provide a stable secondary flow and the effect was prove by a pre-cooling test. In addition, stable combustion was confirmed by combustion test and combustion sequence was established. Based on this sequence, the combustion test will be performed at design pressure of 60 bar.