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Partial admission effect on the performance and vibration of a supersonic impulse turbine

Autor: Hang Gi Lee, Chang-Ho Choi, Sejin Kwon, Ju Hyun Shin, Eun-Hwan Jeong

Publikováno v: Acta Astronautica. 145:105-115

This study experimentally investigates the effects of partial admission on the performance and vibration outcomes of a supersonic impulse turbine with circular nozzles. The turbine of a turbopump for a gas-generator-type liquid rocket engine in the K

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=doi_________::54692431069fcc8a9ef4549a017f5719
https://doi.org/10.1016/j.actaastro.2018.01.025

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Turbine Performance Experiments for the Turbopump of a Liquid Rocket Engine

Autor: Hang-Gi Lee, Eun-Hwan Jeong, Ju Hyun Shin, Chang-Ho Choi

Publikováno v: International Journal of Aerospace System Engineering. 3:25-29

This paper highlights the performance of an impulse turbine which is a part of turbopump in a liquid rocket first stage engine. The turbopump,...

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=doi_________::6e34692f97193214c1735a738545b5e4
https://doi.org/10.20910/ijase.2016.3.1.25

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Performance Test of a 75-tonf Rocket Engine Turbopump

Publikováno v: Journal of the Korean Society of Propulsion Engineers. 20:86-93

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 e

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=doi_________::146306047f058f54dedf8590128c9c8f
https://doi.org/10.6108/kspe.2016.20.2.086

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Critical Suction Peformance Test of Turbopump Assembly for a Liquid-Propellant Rocket Engine

Autor: Suk Hwan Yoon, Chang-Ho Choi, Hang gi Lee, Dae-Jin Kim, Jun Hwan Bae, Ju Hyun Shin

Publikováno v: Volume 2B: Turbomachinery.

This study investigates the behavior of a turbopump assembly during critical cavitation of the propellant pumps in the upper rocket engine of the Korea Space Launch Vehicle-II. Turbopumps operate under conditions involving low pressure at the pump in

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=doi_________::b385a6f167c396a253e7f0ddcab39b06
https://doi.org/10.1115/gt2018-76430

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Performance Test of a 7 tonf Liquid Rocket Engine Turbopump

Autor: Jin-Han Kim, Eun-Hwan Jeong, YeongMin Han, Hang-Gi Lee, Suck-Hwan Yoon, Chang-Ho Choi, Jin-Sun Kim, Ju Hyun Shin, Jun-Gu Noh, Jun-Hwan Bae, Seong-Min Jeon, Soon-Sam Hong, Daejin Kim, Seung-Han Kim, Seong-Lyong Kim, Hyun Duck Kwak, Pyun-Goo Park

Publikováno v: Journal of the Korean Society of Propulsion Engineers. 19:65-72

Performance tests of a turbopump for the developing 7-tonf li quid rocket engine were conducted. The performance of turbopump components and their power matchin g were measured and examined firstly under the LN2 and water environment.. In the real pr

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=doi_________::2163d7969a2a225727a3ce74a73ac433
https://doi.org/10.6108/kspe.2015.19.2.065

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Turbine Rotor-Pyrostarter Coupled Test for the Verification of Thermo-Structural Suitability of a Turbopump Turbine

Autor: Sang Hun Kang, Soo Yong Lee, Moongeun Hong, Hang-Gi Lee, Eun-Hwan Jeong, Jin-Han Kim

Publikováno v: Journal of the Korean Society of Propulsion Engineers. 18:65-72

Turbine rotor-pyrostarter coupled test was performed for the verification of thermo-structural suitability of a turbopump turbine. Newly developed solid propellant and design concept were used in pyrostarter development. In case of turbine rotor, rot

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=doi_________::0efc2ce2c19e888b1c653323e12283f8
https://doi.org/10.6108/kspe.2014.18.1.065

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Effect of Shroud Split on the Performance of a Turbopump Turbine Rotor

Autor: Sukhwan Yoon, Hang-Gi Lee, Pyun-Goo Park, Jin-Han Kim, Eun-Hwan Jeong

Publikováno v: Journal of the Korean Society of Propulsion Engineers. 17:25-31

hglee@kari.re.krABSTRACT A blisk with rotor shroud is usually adopted in LRE turbine to maximize its performance. However it experiences the severe thermal load and resulting damage dur ing engine stating and stop. Shroud splitting is devised to reli

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=doi_________::08de7dcd090d085cbfe08b3e1552ba03
https://doi.org/10.6108/kspe.2013.17.4.025

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Research on the Torque and Starting Characteristics of a Turbopump Turbine

Autor: Jin-Han Kim, Pyun-Goo Park, Moongeun Hong, Eun-Hwan Jeong, Hang-Gi Lee

Publikováno v: Journal of the Korean Society of Propulsion Engineers. 17:35-41

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 co

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=doi_________::4e722d94ccd52a257b1e61ac36832825
https://doi.org/10.6108/kspe.2013.17.1.035

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Tip Clearance Effect on the Performance of a Shrouded Supersonic Impulse Turbine

Autor: Jin-Han Kim, Pyun-Goo Park, Eun-Hwan Jeong, Hang-Gi Lee

Publikováno v: Journal of Propulsion and Power. 24:1295-1300

An experimental investigation of the effect of tip clearance on the performance of a shrouded supersonic impulse turbine was performed in this study. A single-staged axial flow impulse turbine designed to have a rotor inlet relative Mach number of 1.

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=doi_________::1de6288c3194cdbc64afc5941ea92537
https://doi.org/10.2514/1.37504

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