The development of small liquid oxygen and liquid hydrogen turbopumps of a LE-5 rocket engine

Author(s):  
K. KAMIJO ◽  
E. SOGAME ◽  
A. OKAYASU
1964 ◽  
Vol 68 (647) ◽  
pp. 765-772 ◽  
Author(s):  
L. E. Maher

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.


The liquefaction of helium by Kammerlingh Onnes has led in the past thirty years to discoveries of the greatest importance to the study of the solid state. In spite of this, very few laboratories are now equipped with the apparatus necessary for the production of liquid helium. It is therefore very desirable that the complicated technique necessary for its production should be simplified to allow of its more extensive use. In this paper we shall describe a more efficient liquefier, based on an adiabatic principle, which we hope will considerably simplify the production of liquid helium for scientific work. At present two principal methods are used for the cooling and liquefying of gases. The first method is based on cooling produced by adiabatic expansion where the expanding gas is cooled by doing external work. This phenomenon was observed by Clèment and Desormes in 1819 when they discovered the cooling of a gas in a container when its pressure was reduced by letting out some of the gas through a tap. It can be shown that on expanding, the gas remaining in the container has done work in communicating kinetic energy to the escaped gas, and therefore has been cooled adiabatically. Olszewski in 1895 applied this method to the liquefaction of hydrogen; he compressed the gas to 190 atmospheres and pre-cooled it with liquid oxygen boiling at reduced pressure (-211°C); on releasing the pressure, he observed a fog of liquid hydrogen drops. From this experiment he was able to determine the critical data for hydrogen. This method has also been used recently by Simon for liquefying helium. Simon took advantage of the fact that at very low temperatures the thermal capacity of the container is so small that it practically absorbs no cold from the liquefied helium. The limitations of this method are that it can only conveniently be applied for obtaining small amounts of liquid helium; it is not suited for a continuous output of helium, and also there is necessarily a loss of cold due to the gas which leaves the container. The method is also complicated by the fact that high pressures are required, and that pre-cooling with liquid hydrogen boiling at reduced pressure is necessary.


Author(s):  
M. L. Tupper ◽  
A. L. Pulley ◽  
E. F. Johnson ◽  
N. A. Munshi ◽  
P. E. Fabian ◽  
...  

Author(s):  
Hang Gi Lee ◽  
Ju Hyun Shin ◽  
Suk Hwan Yoon ◽  
Dae Jin Kim ◽  
Jun Hwan Bae ◽  
...  

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.


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

1904 ◽  
Vol 72 (477-486) ◽  
pp. 386-391 ◽  

The vapour pressures of liquid oxygen and liquid hydrogen on the scales of the constant-volume hydrogen and helium thermometers has recently been determined by one of us in conjunction with Dr. A. Jaquerod and Mr. G. Senter, and it has been found that two scales of temperature differ by amounts which increase as the temperature falls.


In the paper by K. F. Bonhoeffer and P. Harteck published in 1929, on para-hydrogen, no mention is made of the refractive index of the new modification, and, so far as we can find, no experiments on this subject have hitherto been published. It may, therefore, be presumed that, on the hypothesis which led to the discovery of the para-form, no change of index was expected; and, on any theory, it seemed probable that the change would be very small. It appeared worth while, however, to make use of a Jamin interferometer already set up for other purposes to test this point experimentally and the following paper records the result of the investigation. Para-hydrogen was prepared by adsorbing ordinary hydrogen, purified by previous adsorption in palladium, in charcoal at the temperature of liquid oxygen (—183°C.). After 1 1/2 to 2 hours the gas was allowed to warm up, and should then consist of approximately 50 per cent, ortho- and 50 per cent, para-hydrogen. In order to test whether this wTas actually so Schleiermacher’s method of measuring the thermal conductivities of the two forms, as described in Bonhoeffer and Harteck’s paper, was followed. In their case a Wollaston wire (0.01 mm. diameter) was stretched in a narrow cylindrical tube immersed in liquid hydrogen, and the change in the resistance of the wire, which was electrically heated to 200° absolute, was observed when para- was substituted for ordinary hydrogen at the same pressure (40 mm.). In these circumstances the resistance varied between 111.85 ohms for ordinary hydrogen to 106.25 for hydrogen containing 99.7 per cent, para-hydrogen.


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