• Title/Summary/Keyword: Gas Generator

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Implementation of Constant Power Controlled Starter for A Turbo Generator System (터보 발전기 시스템을 위한 정 출력 제어 방식 시동기 구현)

  • 권정혁;양현섭;노민식;차영범
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2003.10a
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    • pp.219-222
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    • 2003
  • Turbo generator system need starter for gas turbine engine. Turbo generator has high rate gearbox for reduce rotating speed. Because a conventional generator could not operate same speed of gas turbine engine. But Recently turbo generator system is directly connected a gas turbine engine with a super high-speed generator. In this paper, starter driver are implemented direct coupled turbo generator system, Which is directly connected 100kW, 60,000rpm gas turbine engine and 25kW 60,000rpm super high speed generator.

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Ultra fast Marx Generator of N2, SF6, N2-SF6 Mixture Gas based on Research Output Characteristics (초고속 Marx Generator의 N2, SF6, N2-SF6 혼합가스에 따른 출력 특성 연구)

  • Doo, Jin-Suk;Han, Seung-Moon;Huh, Chang-Su;Choi, Jin-Soo
    • The Transactions of The Korean Institute of Electrical Engineers
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    • v.59 no.10
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    • pp.1850-1855
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    • 2010
  • The application field of the pulse power is very wide. Recently, Pulse power technologies take a large place in several applications. Then, many civil and military applications proceed. Marx generator is widely used in high voltage applications. Marx generator is widely used in high voltage applications, such as eletromagnetic wave and power lasers. This paper, we described about the high voltage pulse generator. A compact size high voltage pulse generator with nanosecnd rise time has been fabricated and investigated experimentally. The marx generator has 2 stages. Each stage was constructed one charging capacitor, two electrodes and one charging resistor. A inductance structure is used in order to improve the switching performances fo the whole generator. The experiments of rise time in pure gas and mixtures of gases were described. We tested the Marx generator at different insulation gas. the results show that the dielectric strength of the $N_2-SF_6$ mixture was significantly increased compared with pure nitrogen gas. The experimental results show that the rise time characteristics of the Marx generator can be controlled through varying insulation gas.

Combustion Characteristics of Gas Generator for Liquid Rocket Engine (액체로켓엔진 가스발생기 연소특성)

  • Kim, Seung-Han;Han, Yeoung-Min;Moon, Il-Yoon;Lee, Kwang-Jin;Seol, Woo-Seok;Lee, Chang-Jin;Kim, Seung-Han
    • 한국연소학회:학술대회논문집
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    • 2004.11a
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    • pp.213-216
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    • 2004
  • The results of combustion performance test of fuel-rich gas generator(GG) using LOx and kerosene as propellant at design and off-design point are described. The parameters used in this analysis are the average exit temperature($T_{GG}$) and the characteristic velocity($C^{\ast}$). The average gas temperature at the exit of gas generator is found to be a function of propellant O/F ratio. For the gas generator having residence time of 4msec or more, the effect of flame residence time and combustion chamber pressure on the exit temperature is not significant. The exit characteristic velocity is found to be linearly proportional to the gas temperature at the exit of gas generator.

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A Numerical Study of Supersonic Combustion of Gas Generator (Gas generator의 초음속 연소현상에 대한 연구)

  • Kim, Seong-Jin;Seo, Bong-Gyun;Yeom, Hyo-Won;Sung, Hong-Gye;Gil, Hyun-Yong;Yoon, Hyun-Gull
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.11a
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    • pp.419-422
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    • 2010
  • An unsteady numerical combustion analysis was performed to investigate the combustion characteristics of A Dual Combustion Ramjet(DCR) engine using a gas generator. According to a variance of the equivalence ratio of the gas generator, the flow pattern in the combustor was analyzed. A typical acoustic frequency in the combustor was observed by detail analysis of pressure fluctuation at each location of the combustor.

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Optimal Design and Test of Fuel-Rich Gas Generator

  • Lee, Changjin;Kwon, Sun-Tak
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2004.03a
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    • pp.560-564
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    • 2004
  • The optimal design and combustion analysis of the gas generator for Liquid Rocket Engine (LRE) were performed. A fuel-rich gas generator in open cycle turbopump system was designed for 10ton$_{f}$ in thrust with RP-1/Lox propellant. The optimal design was done for maximizing specific impulse of main combustion chamber with constraints of combustion temperature and power matching required by turbopump system. Design variables were selected as total mass flow rate to gas generator, O/F ratio in gas generator, turbine injection angle, partial admission ratio, and turbine rotational speed. Results of optimal design show the dimension of length, diameter, and contraction ratio of gas generator. Also, the combustion test was conducted to evaluate the performance of injector and combustion chamber. And the effect of the turbulence ring was investigated on the mixing enhancement in the chamber.r.

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Combustion Performance Tests of Fuel-Rich Gas Generator for Liquid Rocket Engine Using an Impinging Injector (충돌형 분사기 형태의 액체로켓엔진용 가스발생기 연소성능시험)

  • 한영민;김승한;문일윤;김홍집;김종규;설우석;이수용;권순탁;이창진
    • Journal of the Korean Society of Propulsion Engineers
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    • v.8 no.2
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    • pp.10-17
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    • 2004
  • The results of the combustion performance tests of gas generator which supplies hot gas into the turbine of turbo-pump for liquid rocket engine and uses LOx and kerosene as propellant are described. The gas generator consists of a injector head with F-O-F impinging injector, a water cooled combustion chamber, a gas torch igniter, a turbulence ring and an instrument ring. The effect of turbulence ring and combustion chamber length on performance of gas generator are investigated. The ignition and combustion at design point are stable and the pressure and gas temperature at gas generator exit meets the target. The turbulence ring installed at middle of chamber effectively mixes hot gas with cold gas and the effect of residence time of hot gas in gas generator on combustion efficiency is small. Test results show that the main parameter controlling the gas temperature at gas generator exit is overall O/F ratio.

The Characteristic Study on Mixture Ratio Stabilizer for Gas Generator of LRE(Liquid Rocket Engine) (액체로켓엔진 가스발생기 혼합비 안정기의 특성 연구)

  • Jung, Tae-Kyu;Lee, Joong-Yeop;Han, Sang-Yeop;Kwon, Se-Jin
    • 유체기계공업학회:학술대회논문집
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    • 2006.08a
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    • pp.509-512
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    • 2006
  • The propellant mixture ratio of gas generator changes when thrust control valve operate to change LRE thrust level. The mixture ratio change of gas generator result in gas temperature change and failure of turbine blade or deterioration of LRE specific impulse. The mixture ratio stabilizer has been developed to maintain propellant mixture ratio of gas generator. This article deals with design and static/dynamic characteristic of stabilizer. Also gas generator system simulation test has shown that the stabilizer can maintain propellant mixture ratio effectively within tolerable range.

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Comparison of Effectiveness for Performance Tuning of Liquid Rocket Engine

  • Cho, Won Kook;Kim, Chun Il
    • International Journal of Aerospace System Engineering
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    • v.5 no.2
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    • pp.16-22
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    • 2018
  • An analysis has been made on the performance variation due to pressure drop change at propellant supply pipes of liquid rocket engine. The objective is to compare the effectiveness of control variables to tune the liquid rocket engine performance. The mode analysis program has been used to estimate the engine performance for different modes which is realized by controlling the flow rate of propellant. The oxidizer of combustion chamber, the fuel of combustion chamber, the oxidizer of gas generator and the fuel of gas generator are the independent variables to control engine thrust, engine mixture ratio and temperature of gas generator product gas. The analysis program is validated by comparing with the powerpack test results. The error range of compared variables is order of 4%. After comparison of tuning effectiveness it is turned out that the pressure drop at oxidizer pipe of gas generator and pressure drop at combustion chamber fuel pipe and the pressure drop at the fuel pipe of gas generator can effectively tune the thrust of engine, mixture ratio of engine and temperature of product gas from gas generator respectively.

Hot Firing Tests of a Gas Generator for Liquid Rocket Engine using a Turbine Manifold Simulator (터빈 매니폴드 모사장치를 이용한 액체로켓엔진 가스발생기 연소시험)

  • Lim, Byoungjik;Kim, Munki;Kim, Jonggyu;Choi, Hwan-Seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.19 no.5
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    • pp.22-30
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    • 2015
  • A gas generator which generates turbine driving gas by burning a part of propellants is used in an open cycle liquid rocket engine and as a main component of an open cycle liquid rocket engine autonomous hot firing tests are required to investigate the combustion performance and characteristics of the gas generator. However, since the combustion gas generated by a gas generator is choked at the turbine nozzle in the turbine manifold, it is necessary to consider the internal volume of turbine manifold as well as that of the gas generator for correct investigation of the combustion performance, characteristics, and acoustic characteristics of the gas generator. Therefore, in the paper hot firing test results of a gas generator with a turbine manifold simulator are described and characteristic prediction using the autonomous test of a gas generator is explained.

Hydrogen Peroxide Gas Generator Design and Investigation of Power Measurement Method Utilizing Turbocharger (과산화수소 가스발생기 설계와 터보차저를 이용한 동력 측정 방법 검토)

  • Park, Dae-Jong;An, Sung-Yong;Kwon, Se-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.11a
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    • pp.41-44
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    • 2008
  • In this paper, the gas generator using hydrogen peroxide catalytic decomposition was designed for turbine generator operation. The gas generator used 90wt% rocket-grade of hydrogen peroxide and manganese dioxide as a catalyst. Turbine generators utilizing gas generators were investigated and the prestudy was prepared using automobile turbocharger instead of turbine generator.

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