Development of a Turbopump for a 30 Ton Class Engine

Kim, Jinhan; Hong, Soon-Sam; Jeong, EunHa; Choi, Changho; Jeon, Seong-Min

doi:10.2514/6.2007-5516

Cited by 16 publications

(5 citation statements)

References 4 publications

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“…The pump is designed to operate under the nominal condition of mass flow rate 29.1 kg/ s, inlet pressure 0.28 MPa, outlet pressure 13.2 MPa, and rotational speed 20,000 r/min. 13 A full-scale impeller and inducer are used in the tests. Both a pump test with the inducer and a pump test without the inducer are carried out to investigate the effect of the inducer on the pump performance.…”

Section: Test Facilitiesmentioning

confidence: 99%

“…Conventional hydraulic and cavitation performance tests are performed with a fuel pump for a liquid rocket engine, 13 and then, pump tests without the inducer are performed. Additionally, autonomous inducer tests are carried out to evaluate the performance of the inducer itself and to discover the correlation between the inducer and the impeller in terms of cavitation.…”

Section: Introductionmentioning

confidence: 99%

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Study on inducer and impeller of a centrifugal pump for a rocket engine turbopump

Hong

Kim

et al. 2012

Proceedings of the Institution of Mechanical Engineers, Part C:

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A hydraulic performance test is conducted for a fuel pump of a liquid rocket engine turbopump. The pump driven by an electric motor is tested in a water environment. Experimental results indicate that the inducer has a negligible effect on the head and efficiency of the pump but a significant effect on the cavitation performance. Additionally, an autonomous inducer test is carried out to investigate the effect of the inducer on the pump performance in more detail, and it is found out that the pump reaches a critical cavitation point when the inducer head is dropped by 55%. A reduction of required net positive suction head of the centrifugal pump by attachment of an inducer is also calculated considering the flow interference between the inducer and the centrifugal impeller, and it is found that the calculation shows a reasonable agreement with the test.

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Section: Test Facilitiesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Study on inducer and impeller of a centrifugal pump for a rocket engine turbopump

Hong

Kim

et al. 2012

Proceedings of the Institution of Mechanical Engineers, Part C:

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“…높은 무게 대 추력비를 요구하는 우주발사체는 고효 율의 터보펌프 가압 방식 액체로켓엔진을 사용하게 된 다. 터보펌프는 엔진에 산화제와 연료를 공급하는 역할 을 담당하는데, 지금까지 국내에서는 30톤급 저추력 액 체로켓엔진에 적용가능한 실험용 터보펌프를 개발하여 국외 실매질 시험을 진행해 오고 있다 [1,2]. 저추력급 엔 진용 터보펌프는 회전체동역학 [3], 베어링 [4], 실 [5,6] 등 국산화 개발을 위한 심층적인 연구들이 수행되어 왔다.…”

Section: 서 론unclassified

Evaluation of Friction Torque for a Turbopump Ball Bearing

Jeon

Kwak²,

Kim³

2011

Journal of the Korean Society of Tribologists and Lubrication E

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Rolling contact ball bearings are utilized almost exclusively for liquid propellant rocket engine turbopump. Turbopump ball bearings are required to endure high speed and high load for a poor lubricated condition in cryogenic environment. To evaluate bearing heat generation performance, friction torque is investigated as a function of rotation speed, bearing load and cooling flow rate through an experimental study using water coolants. Radial and axial loads are simultaneously applied to the test bearing by gas pressurized cylinder rod. Endurance performance of bearing has been also verified under the bearing required load for operating condition during total accumulated test time 2,100 sec.

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“…현재 한국 항공우주연구원 (이하 항우연)에서는 액체산소와 케로신을 추진제로 하는 가스 발생기 사이클의 30톤급 액체로켓엔진에 적용 가능한 터보펌프를 개발하고 있다 [1][2][3]. 이 터보펌프는 단단 원심형 의 산화제펌프와 연료펌프, 그리고 단단 충동형 의 터빈으로 구성되어 있으며 한 개의 터빈이 동 일 축 선상에 있는 두 개의 펌프를 구동하는 형 식이다 (Fig.…”

Section: ⅰ 서 론unclassified

Liquid Oxygen Test of Oxidizer Pump of a Liquid Rocket Engine

홍순삼

김대진²,

김진선³

et al. 2009

Journal of the Korean Society for Aeronautical Space Science

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An oxidizer pump of a turbopump for a 30-ton class gas generator cycle engine was tested in the medium of liquid oxygen. The turbine was driven by cold hydrogen gas in the test. The oxidizer pump was operated stably at both design and off-design conditions, satisfying the performance requirements. The pump head coefficient from the liquid oxygen test was 2～3% lower than that from the water test. The power required to run the oxidizer pump was well balanced with the power produced by the turbine.

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Development of a Turbopump for a 30 Ton Class Engine

Cited by 16 publications

References 4 publications

Study on inducer and impeller of a centrifugal pump for a rocket engine turbopump

Study on inducer and impeller of a centrifugal pump for a rocket engine turbopump

Evaluation of Friction Torque for a Turbopump Ball Bearing

Liquid Oxygen Test of Oxidizer Pump of a Liquid Rocket Engine

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