• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.11-15
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• 2012

A rotordynamic analysis is performed for a 7 ton class turbopump applied to the third stage LRE(Liquid Rocket Engine) of the KSLV(Korea Space Launch Vehicle). Based on the heritage of the developed experimental 30 ton class turbopump and developing 75 ton class turbopump for the KSLV first and second stage LRE, the 7 ton class turbopump is designed as an one-axis rotor turbopump. Two rotor systems comprised of one oxidizer pump assembly and the other fuel pump-turbine assembly are connected each other using a spline shaft and operating at a design speed. Through the rotordynamic analysis, it is investigated that the turbopump acquires sufficient separate margin of critical speed as a sub-critical rotor.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.317-320
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• 2011

Hydrogen peroxide turbopump was designed for bi-propellant liquid rocket engine using hydrogen peroxide and kerosene as propellants. Turbopump operation was verified through water tests. Design conditions of hydrogen peroxide turbopump were determined, and impeller was designed. Turbine which drives pump was selected from commercial turbocharger. Gas generator was designed by reference from turbine map. Pump, turbine, gas generator were integrated, and turbopump system was constructed. Turbopump supplied water by 1.47 bar of pressure and as well as 3.4 kg/s of mass flow rate.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.1
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• pp.93-100
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• 2019

The cavitation of a turbopump inducer develops from the inception to a critical point, and encounters breakdown finally. In this study, we evaluated the characteristics and predictions of cavitation inception for the turbopump inducer using empirical equations. The empirical equation for the elliptical plate predicted the generation of cavitation inception of the turbopump inducer relatively well. However, in case of the marine propeller, it showed a considerable difference owing to the Reynolds number of the operating point. The cavitation inception occurred earlier as the number of blades increased. However, the solidity had no major impact on the cavitation inception because the cavitation occurred locally at the tip of the leading edge.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.605-609
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• 2010

The present paper describes a conceptual design of a turbopump which employs a planetary gear system. In a launcher system, weight is one of the most important design factor. In turbopump systems using propellants such as kerosene, or methane, single shaft systems are employed because of simplicity. One of the main disadvantages of this system, however, is the same rotational speed of both pumps and a turbine which forces to operate under non-optimum condition. To operate each component in optimum or favorable rotational speeds, a planetary gear system may be the best choice when the compactness and efficiency of a turbopump system is considered. A conceptual design and feasibility of the turbopump system adopting a planetary gear system is suggested.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.3
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• pp.58-63
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• 2011

The present paper describes a conceptual design of a turbopump which employs a planetary gear system. In a launcher system, weight is one of the most important design factor. In turbopump systems using propellants such as kerosene, or methane, single shaft systems are employed because of simplicity. One of the main disadvantages of this system, however, is the same rotational speed of both pumps and a turbine which forces to operate under non-optimum condition. To operate each component in optimum or favorable rotational speeds, a planetary gear system seems to be the best choice when the compactness and efficiency of a turbopump system is considered. A conceptual design and feasibility of the turbopump system adopting a planetary gear system is suggested.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.3
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• pp.20-26
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• 2009

Turbopump test for a 30-ton-thrust liquid rocket engine was carried out using real-propellant. Liquid oxygen, kerosene, cold hydrogen gas were used for the oxidizer pump, the fuel pump, and the turbine, respectively. The turbopump was reliably operated at the design and off-design conditions and the performance requirements were satisfied, which implies that the turbopump development at the engine subsystem level is successfully accomplished in the point of performance validation. This paper presents the results of a test where the turbopump was run for 75 seconds at three operating modes. In terms of performance characteristics of pumps and turbine, the results of turbopump assembly test using real-propellant showed a good agreement with those of the turbopump component tests using simulant working fluid.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.359-365
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• 2008

Turbopump test for a 30-ton-thrust liquid rocket engine was carried out using real-propellant. Liquid oxygen, kerosene, cold hydrogen gas were used for the oxidizer pump, the fuel pump, the turbine, respectively. The turbopump was run stably at the design and off-design conditions and the performance requirements were satisfied, which implies that the turbopump development at the engine subsystem level is successfully accomplished in the point of performance validation. This paper presents the results of a test where the turbopump was run for 75 seconds at three operating modes. In terms of performance characteristics of pumps and turbine, the results from turbopump assembly test using real-propellant showed a good agreement with those from the turbopump component tests using simulant working fluid.

• Journal of Aerospace System Engineering
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• v.14 no.5
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• pp.100-106
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• 2020

Turbopumps for liquid rocket engines are exposed to various cavitation instabilities under their operating conditions. The instabilities affect the stability of the turbopumps. To make sure of the stability of the turbopump of KSLV-II, the present work examined the characteristics of the cavitation instabilities during the turbopump assembly test. In the test, the LOx pump was operated under super-synchronous rotating cavitation and attached to uneven cavitation. In the vibration analysis of the fuel pump, the characteristic frequency by the super-synchronous cavitation of the LOx pump was clearly shown.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.125-128
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• 2008

As a interstage of the 30tonf level LOx/kerosene liquid rocket engine development, turbopump-gas generator open-loop coupled tests are performed. Test schematic and test results of open-loop coupled tests are presented. In engine system operation environment simulating combustion chamber by flow control orifice, chill-down procedure, startup characteristics, nominal operability of turbopump+gas generator open-loop coupled Test Plant are confirmed The results of open-loop coupled test were used for the preparation on turbopump+gas generator closed-loop test.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.5
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• pp.73-78
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• 2008

The development of turbopump in Korea has been practically started from 1999. Recently, the turbopump for a LRE with 30-ton level thrust has been successfully developed, which is able to work for all the required LRE regimes. This success is considered as a breakthrough in development of LRE because the turbopump, a core component of LREs, has been considered as a critical barrier in domestic technology point of view. In this paper, status of the turbopump development in Korea is provided and some suggestions are made for the prospective future.