Liquid Oxygen Rotating Friction Ignition Testing of Aluminum and Titanium with Monel® and Inconel® for Rocket Engine Propulsion System Contamination Investigatio

2010 ◽  
pp. 204-204-15
Author(s):  
Stephen F. Peralta ◽  
Keisa R. Rosales ◽  
Joel M. Stoltzfus
Keyword(s):  
Rocket Engine ◽  
Propulsion System ◽  
Liquid Oxygen

Liquid Oxygen Rotating Friction Ignition Testing of Aluminum and Titanium with Monel® and Inconel® for Rocket Engine Propulsion System Contamination Investigation

2009 ◽  
Vol 6 (10) ◽  
pp. 102342 ◽  
Author(s):  
Stephen F. Peralta ◽  
Keisa R. Rosales ◽  
Joel M. Stoltzfus ◽  
H. Barthelemy ◽  
S. W. Dean
Keyword(s):  
Rocket Engine ◽  
Propulsion System ◽  
Liquid Oxygen

Some Problems Arising from the Use of Hydrogen-Fuelled Propulsion Systems

1964 ◽  
Vol 68 (647) ◽  
pp. 765-772 ◽  
Author(s):  
L. E. Maher
Keyword(s):  
Rocket Engine ◽  
Liquid Hydrogen ◽  
Propulsion System ◽  
Liquid Oxygen ◽  
Propulsion Systems ◽  
Vehicle Performance ◽  
Third Stage ◽  
Upper Stage ◽  
Chemical Propulsion ◽  
Rocket Technology

SummaryIt is now generally recognised that liquid hydrogen offers a considerable increase in vehicle performance over the more conventional fuels, despite its relatively low density.A design study on an upper stage, which uses a liquid hydrogen/ liquid oxygen chemical propulsion system, revealed a number of problem areas which extend beyond the current levels of experience and knowledge in rocket technology existing in the U.K. This study was made on the third stage of a communication satellite launching vehicle, and a number of the problems high-lighted during the course of the investigation, covering both the propulsion system and the structure, are described and discussed in terms of their importance and their effects on the launcher system. Solutions are suggested where possible—although, lacking practical confirmation, these must be tentative in the circumstances.While no fundamental difficulties are anticipated in the development of a rocket engine using hydrogen, it is essential to accumulate some background of data and experience to ensure that early policy and designs are sound; the importance of beginning practical work as soon as possible is emphasised.

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.

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

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

Development of a Regeneratively Cooled Low Pressure Liquid Oxygen and Liquid Methane Rocket Engine

2018 ◽  
Author(s):  
Ethan Sichler ◽  
Eric Gonzalez ◽  
Jesus D. Montes ◽  
Richard Picard ◽  
Frank O. Chandler
Keyword(s):  
Rocket Engine ◽  
Low Pressure ◽  
Liquid Oxygen ◽  
Liquid Methane
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