• Title/Summary/Keyword: 파이로 시동기

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Numerical Study of Turbine Blade Surface Gas Temperature with Various RPM and Pyro Starter Pressure (파이로 시동기의 압력변화와 터빈 블레이드 회전수 변화에 따른 충동형 터빈 블레이드 입구의 가스온도 분포 해석)

  • Lee, In-Chul;Byun, Yong-Woo;Koo, Ja-Ye;Lee, Sang-Do;Kim, Kui-Soon;Moon, In-Sang;Lee, Soo-Young
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.11a
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    • pp.94-97
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    • 2008
  • As the partial admission turbine has a intrinsically unsteady and three dimensional flow region, numerical calculation time of these study has been too long time. The numerical analysis for gas temperature of turbine blade surface has been performed to investigate development of temperature with various pyro start pressure. Computations have been carried out several turbine rotational speeds in the range from 0 to 16000 rpm and inlet conditions with 1423K, 7.2MPa. As a result, the more rotational speed and pyro starter pressure of turbine increased, the more turbine blade's temperature decreased. It is also found that flow field of turbine blade inlet area at pyro starter pressure of 5.75MPa and rotational speed of 12100 rpm formed surface temperature uniformly.

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A Study of the Transient Characteristics of LRE Startup Using Several Starting Gases (다양한 구동가스를 사용한 액체로켓엔진의 시동특성 연구)

  • Moon, Yoon-Wan;Cho, Won-Kook;Seol, Woo-Seok
    • Aerospace Engineering and Technology
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    • v.7 no.2
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    • pp.170-175
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    • 2008
  • In this study, it was investigated that the characteristics of startup and compatibility using several type hot and cold gases. The characteristics of starting LRE by pyro starter was compared with that by a Helium spinner. The compatibility of pyro gas, a gaseous Helium, Hydrogen+Nitrogen mixture gas, and air was investigated by a simple 1D turbine analysis considered the properties of each gas and turbine efficiency. Most of them were compatible to start up the LRE however air was properly used only for low power mode of turbine.

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A Study of the Transient Characteristics of LRE Startup for Using Several Starting Gases (다양한 구동가스를 사용한 액체로켓엔진의 시동특성 연구)

  • Moo, Yoon-Wan;Kim, Seung-Han;Seol, Woo-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.11a
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    • pp.216-220
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    • 2006
  • In this study, it was investigated that the characteristics of startup and compatibility using several type hot and cold gases. The characteristics of starting LRE by pyro starter was compared with that by a He spinner. The compatibility of pyre gas, a gaseous He, H2+N2 mixture gas, and air was investigated by a simple 1D turbine analysis considered the properties of each gases and turbine efficiency. Most of them were compatible to start up the LRE but air was properly used only when the turbine was low power mode.

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The current status of the development of pryostarters (파이로스타터 개발 현황)

  • Hong, Moon-Geun;Lee, Soo-Yong
    • Aerospace Engineering and Technology
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    • v.9 no.2
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    • pp.204-209
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    • 2010
  • The current status of the development of pyrostarters, which play a role as a turbo pump starter in liquid propellant propulsion systems by supplying pressurized gas to power turbines for engine start, has been introduced. Firstly, the development history is briefly summarized, and secondly the current technical status in core parts for the development of pryrostarters such as solid propellants, internal ballistics, rupture discs, and igniters are presented. The current technical achievements could make it feasible to fulfill the development requirements for pyrostarters.

Preliminary Study of a Turbopump Pyro Starter (터보펌프 파이로 시동기 기초연구)

  • Hong, Moon-Geun;Lee, Soo-Yong
    • Journal of the Korean Society of Propulsion Engineers
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    • v.12 no.2
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    • pp.74-80
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    • 2008
  • The feasibility study into the development of turbine spinners, which start up the turbo-pump, has been carried out and the design requirements and parameters ranges have been presented. Turbine spinners use the solid propellant as such composite propellant based AN compound with high energy plasticizers, coolants, and phase stabilizer which relieves a sensible volume change due to the phase transformation of AN near room temperature. Propellants which have a homing rate of $0.2{\sim}0.3\;mm/s$ and pressure exponent ranged from 0.3 to 0.6, showed stable burn-out in the standard motor tests. Both the magnitude of ignition energy and its thermal transfer mechanism have been proved to have a tangible effect on the ignition of the pyre starter, and the results of this study showed that a flame temperature of 1400K would be quite adequate to get a stable ignition for the AN composite propellant.

Research on the Torque and Starting Characteristics of a Turbopump Turbine (터보펌프 터빈의 토크 및 시동특성 연구)

  • Jeong, Eunhwan;Lee, Hang-Gi;Park, Pyun-Goo;Hong, Moongeun;Kim, Jinhan
    • Journal of the Korean Society of Propulsion Engineers
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    • v.17 no.1
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    • pp.35-41
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    • 2013
  • Torque characteristics of a turbopump turbine was analyzed using the turbine performance test result. Specific torque of the subject turbine could be expressed as a linear function of corrected rotor speed at a fixed pressure ratio and it has been confirmed by the test result. It also found that corrected rotor speed-specific torque characteristics does not change anymore if the turbine pressure ratio is set bigger than a certain value. Using the turbine torque characteristics and pyro-starter performance test results, rotational speed development behavior of the turbopump was predicted. Prediction revealed that the lap time reaching 50% of turbopump design speed is less than 0.7 second. Effect of the thermal loss between pyro-starter and turbopump was negligible.

Research on the Torque and Starting Characteristics of a Turbopump Turbine (터보펌프 터빈의 토크 및 시동특성 연구)

  • Jeong, Eun-Hwan;Lee, Hang-Gi;Park, Pyun-Goo;Hong, Moon-Geun;Kim, Jin-Han
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2012.05a
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    • pp.4-10
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    • 2012
  • Torque characteristics of a 75-tonf turbopump turbine was analyzed using the turbine performance test result. Specific torque of the subject turbine could be expressed as a linear function of corrected rotor speed at a fixed pressure ratio and it has been confirmed by the test result. It also found that corrected rotor speed-specific torque characteristics does not change anymore if the turbine pressure ratio is set bigger than a certain value. Using the turbine torque characteristics and pyro-starter performance test results, rotational speed development behavior of the turbopump was predicted. Prediction revealed that the lap time reaching 50% of turbopump design speed is less than 0.7 second. Effect of the thermal loss between pyro-starter and turbopump was negligible.

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Development of a Rupture Disk for Pyrostarters (파이로스타터용 럽쳐디스크 개발)

  • Park, Ho-Jun;Hong, Moon-Geun;Lee, Soo-Yong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.05a
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    • pp.219-222
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    • 2009
  • Pyrostarters play a role as a turbopump starter in liquid propellant propulsion systems by supplying pressurized gas to power turbines for engine start. A rupture disk in pyrostarters, which is usually installed behind a nozzle throat, not only isolates the charged solid propellants from the external environment but also improves the ignitability of the solid propellants by increasing a chamber pressure at the beginning of combustion. Experimental tests have been performed to study the effects of rupture disk thickness, depth and shape of scores, and pressure build-up rates on burst pressures and burst diameters. The experimental results show that the developed rupture disk fulfills the performance requirements expected in a real operational condition.

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Estimation of the operating characteristics of a turbopump driven by a pyro-starter (파이로시동기로 작동되는 터보펌프의 구동특성 예측)

  • Kim Cheul-Woong;Seol Woo-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.05a
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    • pp.167-170
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    • 2006
  • For a short time a pyre-starter should turn the blades of a turbine to the adequate rotational speed by a single operation. Through this process the pressures of the components of a propellant rise rapidly up to the operating point, and the components enter into a gas-generator. Combustion in the gas-generator occurs to keep the turbopumps working. In this research characteristic parameters of a pyre-starter which correspond to the required performance of the turbopump before the gas-generator starts to work were selected

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Development of Propellant for Turbopump Pyro Starter (터보펌프 시동기용 추진제 개발)

  • Song, Jong-Kwon;Choi, Sung-Han;Hong, Moon-Geun;Lee, Soo-Yong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.05a
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    • pp.7-10
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    • 2009
  • The development and evaluation of solid propellant were performed for the turbopump pyro starter, which start up the liquid propellant rocket engine for the Space Launch Vehicle (SLV). Requirements for the turbopump pyro starter propellant include the production of low flame temperature, low burning rate and nontoxic gas to protect the mechanical corrosion or air pollution. This study describes the development of the solid propellant composition which is based on PCP binder. DHG (Dihydroxy glyoxime), which has advantages of oxygen balance and ignition, was used as coolant. The mechanical properties and burning rate of the propellants were measured. Finally, static fired test was performed to prove the possibility of development.

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