Development of a Liquid Oxygen / Liquid Methane Rocket Engine Injector

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.

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Cold Helium Pressurization for Liquid Oxygen / Liquid Methane Propulsion Systems: Fully-Integrated Initial Hot-Fire Test Results

52nd AIAA/SAE/ASEE Joint Propulsion Conference ◽

10.2514/6.2016-4682 ◽

2016 ◽

Cited By ~ 3

Author(s):

Robert L. Morehead ◽

Matthew J. Atwell ◽

John C. Melcher ◽

Eric A. Hurlbert

Keyword(s):

Fire Test ◽

Liquid Oxygen ◽

Test Results ◽

Propulsion Systems ◽

Fully Integrated ◽

Liquid Methane

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Infrared radiation characteristics of liquid oxygen/kerosene rocket engine plume with different number of nozzles

Spectroscopy Letters ◽

10.1080/00387010.2018.1510840 ◽

2019 ◽

Vol 52 (3-4) ◽

pp. 159-167

Author(s):

Hong-Hua Cai ◽

Wan-Sheng Nie ◽

Ling-Yu Su ◽

Tian-yi Shi ◽

Kang-Kang Guo

Keyword(s):

Infrared Radiation ◽

Rocket Engine ◽

Liquid Oxygen ◽

Radiation Characteristics

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Practical uses of liquid methane in rocket engine applications

Acta Astronautica ◽

10.1016/j.actaastro.2009.01.052 ◽

2009 ◽

Vol 65 (5-6) ◽

pp. 696-705 ◽

Cited By ~ 35

Author(s):

Todd Neill ◽

Donald Judd ◽

Eric Veith ◽

Donald Rousar

Keyword(s):

Rocket Engine ◽

Liquid Methane

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