Abstract
The energy efficiency of new technical developments is a critical issue. It should be noted that today the focus in this issue has seen a major shift to the maximum use of renewable energy sources. The purpose of this research is to reduce the weight of helium heat exchangers of the fuel tank pressurisation systems in modern rocket propulsion systems that use fuel components like liquid oxygen and kerosene-type fuel. This is the first time that the question has been raised about the possibility and advisability of increasing the temperature of helium at the heat exchanger inlet without the use of additional resources. The paper addresses the use of the waste (“low-potential”) heat and ”industrial wastes” present in propulsion systems. Basic laws of complex heat exchange and the retrospective review of applicable heat exchanger structures are applied as a research methodology. Two sources of low-potential heat are identified that have been previously used in the rocket engine building in an inconsistent and piecemeal manner to obtain and heat the pressurisation working fluid. These are the rammedair pressurisation during the motion of the rocket carrier in the atmosphere, and the tank pressurisation as a result of boiling of the top layer of oxidiser which is on the saturation line. This is the first time that the advisability has been substantiated of increasing the temperature of the working fluid at the heat exchanger inlet, first of all due to the use of the low-potential heat. This is also the first time that unemployed sources of low-potential heat and “industrial wastes” are found in modern deep throttling propulsion systems. These are the high-boiling-point fuel in the tank, behind the highpressure pump, at the exit of the combustion chamber cooling duct, and also the fuel tank structures, and the engine plume. A possibility is proved, and an advisability demonstrated of their implementation to increase the efficiency of pressurisation system heat exchangers. This is the first time that the methodology of combustion chamber cooling analysis has been proposed to be adopted for the heating of heat exchanger by the engine plume. This is the first time that a classification of waste heat sources has been developed which can be used to increase the pressurisation working fluid temperature. The identified reserves help to increase the efficiency of the helium heat exchangers of the tank pressurisation systems in the propulsion systems
Highlights
Heat exchangers have been long and widely used in the technological processes in the mining, oil refining, automotive, aeronautical, petrochemical, chemical, nuclear, aerospace industries, in the agricultural sector, energy industry, public services
It should be noted that today the focus in this issue has seen a major shift to the maximum use of renewable energy sources
The purpose of this research is to reduce the weight of helium heat exchangers of the fuel tank pressurisation systems in modern rocket propulsion systems that use fuel components like liquid oxygen and kerosene-type fuel
Summary
Heat exchangers have been long and widely used in the technological processes in the mining, oil refining, automotive, aeronautical, petrochemical, chemical, nuclear, aerospace industries, in the agricultural sector, energy industry, public services. – reduce the use of hydrocarbon fuel combustion products as a coolant in heat exchangers This is the first time that the issue has been addressed of finding and substantiating reasonable ways to employ the waste low-potential heat and the “industrial wastes” that are present in the rocket carrier (RC), foremost for increasing the heat exchanger inlet temperature of helium. The objectives of the research are to: – identify drawbacks of applicable heat exchangers of the fuel tank pressurisation systems in modern rocket propulsion systems on the basis of critical retrospective review of their structures, configurations of modern rocket engines, and achievements of heat engineering; – audit possible unemployed heat energy sources on board of RC that designers have previously missed; – substantiate most promised and technologically simple ways to use low potential heat for the improvement of heat exchanger characteristics, using the example of rocket propulsion systems; – classify the sources of low potential heat and “industrial wastes” identified on board of and near to RC. A notable example is the heat exchanger [4] of the RD-107 engine of the Soyuz-2 rocket carrier stage 1 (Fig. 2)
Sign-in/Register to view highlights & summary Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
