scholarly journals Thrust Performance Improvement for a Water/Liquid Nitrogen Rocket Engine

2010 ◽  
Vol 3 (1) ◽  
pp. 24-37
Author(s):  
Rikio WATANABE ◽  
Ryo MIKAMI
Keyword(s):  
Liquid Nitrogen ◽  
Performance Improvement ◽  
Rocket Engine ◽  
Thrust Performance

scholarly journals Thrust Performance of Rotary-Valved Four-Cylinder Pulse Detonation Rocket Engine

2015 ◽  
Vol 58 (4) ◽  
pp. 193-203 ◽  
Author(s):  
Ken MATSUOKA ◽  
Ryuki SAKAMOTO ◽  
Tomohito MOROZUMI ◽  
Jiro KASAHARA ◽  
Akiko MATSUO ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Pulse Detonation ◽  
Pulse Detonation Rocket Engine ◽  
Thrust Performance

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

2018 ◽  
Author(s):  
Hang Gi Lee ◽  
Ju Hyun Shin ◽  
Suk Hwan Yoon ◽  
Dae Jin Kim ◽  
Jun Hwan Bae ◽  
...  
Keyword(s):  
Liquid Nitrogen ◽  
Performance Test ◽  
Rocket Engine ◽  
Lightweight Design ◽  
Cavitation Number ◽  
Inlet Pressure ◽  
Liquid Oxygen ◽  
Pump Failure ◽  
Critical Cavitation ◽  
Suction Performance

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 inlet and high rotational speeds to allow for a lightweight design. This severe environment can easily cause cavitation to occur in the pump. This cavitation can then cause the pump operation to fail. As the cavitation number in the pump decreases below the critical point, the pump fails to operate. There is concern regarding the behavior of the turbopump assembly arising from pump failure due to cavitation. It is necessary to verify the problems that may occur if the turbopump assembly operates under extreme conditions, such like the critical cavitation. This study performed tests to investigate the breakdown of pumps in the turbopump assembly. Tests were conducted with liquid nitrogen, water, and high-pressure air instead of the mediums used during actual operation of liquid oxygen, kerosene, and hot gas. The turbopump was tested at the design point of 27,000 rpm, while the inlet pressure of each pump was controlled to approach the critical cavitation number. The turbine power output was maintained during the tests. The results show that the breakdown point of the oxidizer pump using liquid nitrogen, which is a cryogenic medium, occurred at a lower cavitation number than during an individual component suction performance test using water. The fuel pump using water, meanwhile, experiences breakdown at similar cavitation numbers in both tests. As the breakdown of the pump occurs, the power required by that pump decreases, and the rotational speed of the turbopump increases. Compared with individual pump suction performance tests, this breakdown test can be used to determine the limit of the propellant inlet pressure of the turbopump and to characterize the behavior of the turbopump assembly when a breakdown occurs. Vibrations were also analyzed for tests at a high cavitation number and at the critical cavitation number. The vibration increased with breakdown and notable frequencies were analyzed.

scholarly journals Effects of Nozzle Geometries on Thrust Performance Improvement of Micro-Multi-Nozzle-Array Thrusters

2009 ◽  
Vol 7 (ists26) ◽  
pp. Pb_77-Pb_82
Author(s):  
Fujimi SAWADA ◽  
Atsushi KOSHIYAMA ◽  
Shuji HAGIWARA ◽  
Hideyuki HORISAWA ◽  
Ikkoh FUNAKI
Keyword(s):  
Performance Improvement ◽  
Nozzle Geometries ◽  
Thrust Performance

Study on Cooling Characteristics of Mixed Gases with Hot Gas of Liquid Rocket Engine and Injected Liquid Nitrogen

2012 ◽  
Vol 36 (10) ◽  
pp. 1001-1009
Author(s):  
Jun-Su Jeon ◽  
I-Sang Yu ◽  
Joong-Il Kim ◽  
Jai-Ho Kim ◽  
Young-Sung Ko
Keyword(s):  
Liquid Nitrogen ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Hot Gas ◽  
Liquid Rocket ◽  
Mixed Gases

Thrust Performance Improvement for PMSLM Through Double-Layer Reverse Skewed Coil and WRF-MKH Method

2020 ◽  
Vol 25 (6) ◽  
pp. 2950-2960
Author(s):  
Weitao Wang ◽  
Jiwen Zhao ◽  
Juncai Song ◽  
Fei Dong ◽  
Kaifang Zong ◽  
...  
Keyword(s):  
Performance Improvement ◽  
Double Layer ◽  
Thrust Performance

scholarly journals Development of Non-Combustible Rocket Engine by Using Explosive Boiling of Liquid Nitrogen

2009 ◽  
Vol 7 (ists26) ◽  
pp. Ph_75-Ph_80
Author(s):  
Osamu KAWANAMI ◽  
Tomoya SUZUKI ◽  
Itsuro HONDA ◽  
Yousuke KAWASHIMA
Keyword(s):  
Liquid Nitrogen ◽  
Rocket Engine ◽  
Explosive Boiling

Measurement of Liquid Nitrogen in a Liquid Oxygen Feed Line During Rocket Engine Testing

2005 ◽  
Author(s):  
Vidhu Tiwari ◽  
Rajamohan Kalluru ◽  
Fang-Yu Yueh ◽  
Jagdish Singh
Keyword(s):  
Liquid Nitrogen ◽  
Rocket Engine ◽  
Liquid Oxygen ◽  
Feed Line ◽  
Engine Testing
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