Hyun-Duck Kwak
Current Organizations / Institutes
The organizations/institutes from the scholar's latest article
Previous Organizations / Institutes
The organizations / institutes from the scholar's other articles in the past ten years
Hyun-Duck Kwak has a total of 37 co-authors. Here are the top co-authors by number of shared publications:
Jinhan Kim
4 shared publicationsSeong Min Jeon
3 shared publicationsSuk Hwan Yoon
3 shared publicationsChang-Ho Choi
Korea Aerosp Res Inst, Daejeon, South Korea
2 shared publicationsChang-Ho Kim
2 shared publicationsNam-Soo Lee
2 shared publications
Latest Publications
- 31 May 2025
- Published by Springer Nature in Journal of Mechanical Science and Technology
- Vol. 39 (6) , 3039-3048
Prediction of lateral and angular eccentricity effects on plain annular seal performance using transient 3D CFD
- 31 May 2025
- Published by Springer Nature in Journal of Mechanical Science and Technology
- Vol. 39 (6) , 3039-3048
Prediction of lateral and angular eccentricity effects on plain annular seal performance using transient 3D CFD
- Open Access
Numerical and Experimental Study of Nose for LOx Floating Ring Seal in Turbopump
Floating ring seals are widely used as a leakage control solution for turbomachines because they effectively operate with small clearances between the shaft and seal. The oxidizer pump of the 7 tonf liquid engine in the Korea Space Launch Vehicle II (KSLV-II) operates at high rotational speeds and under cryogenic conditions and has floating ring seals in the bearing cooling path to reduce leakages. In this study, we evaluated the frictional force acting on the nose of the floating ring in the oxidizer pump of the 7 tonf turbopump using numerical analysis, and we investigated the radial force on the floating ring induced by the vibration of the rotor and the flow characteristics around the floating ring seal. Through a comparison of the frictional and floating forces according to the change in the diameter of the floating ring noses, we also estimated the dynamic positioning of the floating ring. In addition, we examined the leakage of the floating ring seals with the rotational speed and gap size of the floating ring, and we used the results as data for designing a floating ring seal. Finally, we performed turbopump real-propellant tests with the floating ring seal of the high and the middle noses, finding that the test result was in good agreement with the results of numerical analysis.
Open AccessNumerical and Experimental Study of Nose for LOx Floating Ring Seal in Turbopump
Floating ring seals are widely used as a leakage control solution for turbomachines because they effectively operate with small clearances between the shaft and seal. The oxidizer pump of the 7 tonf liquid engine in the Korea Space Launch Vehicle II (KSLV-II) operates at high rotational speeds and under cryogenic conditions and has floating ring seals in the bearing cooling path to reduce leakages. In this study, we evaluated the frictional force acting on the nose of the floating ring in the oxidizer pump of the 7 tonf turbopump using numerical analysis, and we investigated the radial force on the floating ring induced by the vibration of the rotor and the flow characteristics around the floating ring seal. Through a comparison of the frictional and floating forces according to the change in the diameter of the floating ring noses, we also estimated the dynamic positioning of the floating ring. In addition, we examined the leakage of the floating ring seals with the rotational speed and gap size of the floating ring, and we used the results as data for designing a floating ring seal. Finally, we performed turbopump real-propellant tests with the floating ring seal of the high and the middle noses, finding that the test result was in good agreement with the results of numerical analysis.
- Open Access
- 1 June 2018
- Published by Elsevier in Aerospace Science and Technology
- Vol. 77, 67-82
Performance assessment of electrically driven pump-fed LOX/kerosene cycle rocket engine: Comparison with gas generator cycle
- 1 June 2018
- Published by Elsevier in Aerospace Science and Technology
- Vol. 77, 67-82
Open AccessPerformance assessment of electrically driven pump-fed LOX/kerosene cycle rocket engine: Comparison with gas generator cycle
- 1 February 2018
- Published by The Korean Society for Aeronautical & Space Sciences in Journal of the Korean Society for Aeronautical & Space Sciences
- Vol. 46 (2) , 175-181
Conceptual design of electric-pump motor for 50kW rocket engine
Electric pump system is new technology for next generation propulsion unit. The system has simple structure which dose not need gas generator, injector and turbine and might better pump for low cost and low payload rocket. Therefore, this paper suggests conceptual design of electric-pump Permanent-Magnet Synchronous Motor (PMSM) which has 50 kW & 50,000 RPM for rocket. To satisfy the system's requirement, electromagnetic analysis is conducted for suitable inner and outer diameter of stator and rotor which uses 4000 Gauss cylinder magnet and Inconel 718 can to fix whole rotor. Futhermore, to confirm rotational vibration, rotordynamics analysis is conducted. By this analysis, Campbell diagram is printed. From the diagram, natural frequency could be determined for the only motor and dynamo meter test bench.
- 1 February 2018
- Published by The Korean Society for Aeronautical & Space Sciences in Journal of the Korean Society for Aeronautical & Space Sciences
- Vol. 46 (2) , 175-181
Conceptual design of electric-pump motor for 50kW rocket engine
Electric pump system is new technology for next generation propulsion unit. The system has simple structure which dose not need gas generator, injector and turbine and might better pump for low cost and low payload rocket. Therefore, this paper suggests conceptual design of electric-pump Permanent-Magnet Synchronous Motor (PMSM) which has 50 kW & 50,000 RPM for rocket. To satisfy the system's requirement, electromagnetic analysis is conducted for suitable inner and outer diameter of stator and rotor which uses 4000 Gauss cylinder magnet and Inconel 718 can to fix whole rotor. Futhermore, to confirm rotational vibration, rotordynamics analysis is conducted. By this analysis, Campbell diagram is printed. From the diagram, natural frequency could be determined for the only motor and dynamo meter test bench.
- 1 April 2015
- Published by The Korean Society of Propulsion Engineers in Journal of the Korean Society of Propulsion Engineers
- Vol. 19 (2) , 65-72
Performance Test of a 7 tonf Liquid Rocket Engine Turbopump
- 1 April 2015
- Published by The Korean Society of Propulsion Engineers in Journal of the Korean Society of Propulsion Engineers
- Vol. 19 (2) , 65-72
Performance Test of a 7 tonf Liquid Rocket Engine Turbopump
- 1 April 2013
- Published by Elsevier in Aerospace Science and Technology
- Vol. 26 (1) , 169-175
Rotordynamic analysis of a high thrust liquid rocket engine fuel (Kerosene) turbopump
- 1 April 2013
- Published by Elsevier in Aerospace Science and Technology
- Vol. 26 (1) , 169-175
Rotordynamic analysis of a high thrust liquid rocket engine fuel (Kerosene) turbopump
- 1 May 2008
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of Propulsion and Power
- Vol. 24 (3) , 433-436
Rotordynamic Analysis of a Turbopump with the Casing Structural Flexibility
- 1 May 2008
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of Propulsion and Power
- Vol. 24 (3) , 433-436
Rotordynamic Analysis of a Turbopump with the Casing Structural Flexibility