Performance tests of a turbopump for the developing 7-tonf liquid rocket engine were conducted. The performance of turbopump components and their power matching were measured and examined firstly under the LN2 and water environment.. In the real propellant(LOX and kerosene) environment tests, design and off-design performances of turbopump were fully verified. During the off-design tests, turbopump running time was set the same as engine operating time and pump inlet pressure were set lower than nominal operating value in order to investigate pump suction capability. It have been verified that subject turbopump satisfies required performance -flow rate, head, suction performance and operational time -in the operating regime of developing liquid rocket engine.
A turbopump real-propellant test facility(TPTF) is to verify the performance of a turbopump unit(TPU) based on liquid oxygen and kerosene. One of the most important sub-facilities is a hot-gas generation system which makes the driving force of the TPU with an alcohol burner. The alcohol burner generates the required flow rates and temperature at the facility using high pressure air and ethanol. In the study, the verification tests of the alcohol burner which was manufactured entirely with domestic technology were performed and fabrication technique and operation skill for the burner could be obtained ahead of the construction of the facility. Two burners will be operated simultaneously for the real-propellant test of 75tf class turbopump and satisfy the power requirement from the turbine of the TPU. 초 록 터보펌프 실매질 시험설비는 액체산소와 케로신을 토대로 터보펌프 조립체의 성능을 검증하는 시험 설비이다. 이 시험설비 중에서 가장 핵심적인 부분은 터보펌프의 구동력을 생성시키는 고온공기 생성 시스템이다. 고압공기와 에탄올을 사용하는 알코올버너에 의해 시험시설에서 요구되는 유량과 온도가 생성된다. 본 연구에서는 국내기술로 제작한 알코올버너의 개발시험을 수행하였으며, 터보펌프 실매질 시험설비 구축에 앞서 버너의 제작기술과 운용경험을 확보할 수 있었다. 75톤급 터보펌프 실매질 시험 에서는 이 알코올버너가 2기 동시 운용되어 터빈이 요구하는 구동력을 충족시킬 것으로 보인다.
Performance tests of a 75-tonf liquid rocket engine turbopump were conducted. The performance of sub-components -two pumps and a turbine -and their power matching were measured and examined firstly near the design speed under the LN2 and kerosene environment. In the real propellant -LOX and kerosene -environment tests, design and off-design performance of turbopump were fully verified in regime of the rocket engine operation. During the off-design performance tests, turbopump running time was set longer than the engine operating time to verify the pump operability and set the pump inlet pressure close to design NPSHr to investigate pump suction capability in parallel. It has been found that developed-turbopump satisfied all of the engine required performances.
[Abstract]In this study, the system was composed of the booster chopper and the power converter, which is a pulse width modulation (PWM) voltage inverter using a hybrid power generation system solar cell energy and wind force, Furthermore, in order to compensate the PWM voltage type inverter was linked with the general commercial power source, and through a normal operation of energy storage system (ESS), the system operated the LED Taxi Light by Wavelength according to Meteorological Changes at the airport in an efficient manner.The performance of the system was compared with the solar cell characteristics specification. In addition, for phase synchronization with the PWM voltage type inverter, the grid voltage was detected so as to operate the grid voltage and inverter output in the same phase and to connect the surplus electric power with the system. Finally, by developing a control circuit at the same time from which an excellent dynamic characteristics can be obtained through applying to the airport runway taxi light, it was concluded that a variety of taxi light can be pursued.
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