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Journal articles on the topic 'Turbopump units'

Author: Grafiati

Published: 28 May 2022

Last updated: 30 July 2025

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1

Ivanov, Y. N., O. P. Badun, S. A. Deshevykh, and L. F. Ivchenco. "Turbopump Units of Rocket Engines Developed by DO-4." Kosmičeskaâ tehnika. Raketnoe vooruženie 2018, no. 2 (2018): 25–33. http://dx.doi.org/10.33136/stma2018.02.025.

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2

Kochetkov, Yury, and Adelia Burova. "Gas-dynamic reasons for vibrations origination in turbopump units." Vestnik Moskovskogo aviatsionnogo instituta 28, no. 3 (2021): 54–62. http://dx.doi.org/10.34759/vst-2021-2-54-62.

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3

Eresko, S. P., E. V. Kukushkin, and A. A. Orlov. "Planning experimental studies of sealing units of a turbopump assembly." Systems. Methods. Technologies, no. 3(43) (2019): 7–13. http://dx.doi.org/10.18324/2077-5415-2019-3-7-13.

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4

Kulyk, A. V. "Technology development of packing rings production to butt-end packing of turbopump units." Kosmìčna nauka ì tehnologìâ 8, no. 1s (2002): 118–22. http://dx.doi.org/10.15407/knit2002.01s.118.

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5

Шашко, Юрій Анатолійович, Олексій Володимирович Кулик, Роман Федосійович Максимчук та Анатолій Федорович Санін. "Вибір оптимальних методів чистової обробки лопаток закритих моноколіс турбонасосних агрегатів, отриманих адитивним методом прямого лазерного спікання порошку". Aerospace technic and technology, № 4 (27 серпня 2021): 53–62. http://dx.doi.org/10.32620/aktt.2021.4.08.

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The creation of complex structural elements of aircraft using is promising and is widely used since such elements have several structural and technological advantages over the manufacture of parts using classical technologies. However, it requires the solution of several scientific and technical problems to obtain products of high accuracy and roughness, the development of a technological process, the development of processing modes, and sometimes the development of a new design of products. For the development of technologies in modern rocketry, improving the quality and accuracy of the produ

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6

Zuev, A. A., A. A. Arngold, V. P. Nazarov, V. N. Mehtieva, and E. V. Khodenkova. "Calculation of initial dynamically unstabilized sections in the elements of liquid rocket engines turbopump units." Journal of Physics: Conference Series 1889, no. 2 (2021): 022066. http://dx.doi.org/10.1088/1742-6596/1889/2/022066.

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7

Dotsenko, V., та Yu Koveza. "ВИКОРИСТАННЯ ПІДШИПНИКІВ КОВЗАННЯ У АВІАЦІЙНІЙ ТА КОСМІЧНОЇ ТЕХНІЦІ". Open Information and Computer Integrated Technologies, № 96 (23 лютого 2023): 24–33. http://dx.doi.org/10.32620/oikit.2022.96.02.

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Examples and prospects of various types of sliding bearings applications in power elements of aircraft engines and in turbopump units (TPU) of liquid propellant rocket engines (LPRE) are discussed in this article.In the second half of the last century, piston aircraft engines were replaced by turboprop (TPE) and turbojet (TJE) engines. Almost all leading manufacturers of these motors use rolling bearings as rotor supports for the main power units. The use of sliding bearings is extremely rare and is the exception rather than the rule. These exceptions include the company Pratt & Whitney, w

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8

Zuev, Alexander, Anna Arngol’d, and Vladimir Nazarov. "Sections of dynamically non-stabilized flows in characteristic channels of the air-gas channels of liquid rocket engines turbopump units." Vestnik Moskovskogo aviatsionnogo instituta 27, no. 3 (2020): 167–85. http://dx.doi.org/10.34759/vst-2020-3-167-185.

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9

Belyakov, Vladislav A., Dmitry O. Vasilevsky, Daniil V. Maslov, Artemy A. Kilyashov, and Roman V. Romashko. "Verification of thermodynamic parameters of a mixture of generator gas on oxygen-hydrogen fuel with an excess of one of the fuel components." Siberian Aerospace Journal 25, no. 1 (2024): 56–67. http://dx.doi.org/10.31772/2712-8970-2024-25-1-56-67.

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Liquid gas generators (LGG) are additional firing units in the power system of liquid rocket engines (LPRE). The LGG ensure the operation of the power units of the turbopump unit (TPU) of the engine by feeding combustion products (CP) to the turbine drive. The main criteria for the efficiency of the generator gas is the complex (RT)gg and the thermodynamic properties of the mixture, depending on temperature, pressure, the degree of excess of the oxidizer and the enthalpy of the fuel, attributed to the conditions of supply to the nozzles of the GG. Changing the parameters of the generator gas l

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10

Neporozhniy, Gennady, Alina Savchenko, and Oleksandr Pivovarov. "GRAPHIC SUPPORT FOR THE OPERATION OF AIRCRAFT POWER UNITS." Science-based technologies 61, no. 1 (2024): 59–75. http://dx.doi.org/10.18372/2310-5461.61.18516.

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The main task of operators is to maintain the airworthiness of aircraft by implementing the technologies outlined in the sets of documents attached to standard products.Engines, the main source of energy for flight, usually work in conjunction with many systems, each of which, in turn, is accompanied by instructions and manuals to ensure operability. In accordance with accepted practice, most of the disaggregated information is provided in text form. These forces you to remember the necessary data or constantly search for it in dozens of updated and replaced pages of the provided technologies,

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11

Prokopenko, Denis. "Analysis of noise sources in the cabin of a passenger aircraft and methods for combating them." E3S Web of Conferences 583 (2024): 03023. http://dx.doi.org/10.1051/e3sconf/202458303023.

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This paper examined the problem of noise in the aircraft cabin and ways to solve it. Through observations, the following causes of noise were identified: the power plant (acoustic and mechanical vibrations, turbulent boundary layer and others), the location of the engine relative to the airframe, the noise of the propeller (if it is a propeller power plant), the propeller of the power plant itself, the air conditioning system, and so on the same operating device in the cabin. There is a comprehensive way to solve the problem of noise in the aircraft cabin: for aircraft with turbojet engines, m

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12

Nerubasskyi, Vadym, та Denys Lavreniuk. "Питання вибору і кваліфікації засобів розробки програмного забезпечення для електронних систем автоматичного керування авіаційних двигунів". Aerospace technic and technology, № 4sup2 (22 серпня 2022): 80–85. http://dx.doi.org/10.32620/aktt.2022.4sup2.12.

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The introductory part of the article provides information that Element JSC is one of the leading enterprises in Ukraine in the scientific and technical direction "Electronic systems for measuring, parameters monitoring and controlling aircraft engines". Because of cooperation with Ivchenko-Progress SE and Motor Sich JSC, Element JSC has manufactured more than 250 EEC units of the RDC-450M family for various modifications of the AI-450 Turboshaft/Turboprop engines. The software of these EEC units is certified according to the DO-178B/ED-12B. The software of subsequent EEC units under developmen

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13

Panting, J. R., and K. R. Pullen. "Thermodynamic studies of a novel aeroengine concept." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 214, no. 2 (2000): 71–83. http://dx.doi.org/10.1243/0954410001531827.

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The purpose of the work described is to indicate the potential of a high-speed, spark ignition compound-turbocharged engine as an alternative to the gas turbine powered turboprop. Using relatively simple thermal cycle models, it is possible to show that such a compound-turbocharged engine should be capable of achieving very high thermal efficiency levels. A more sophisticated model of this engine type confirms these findings. It proves more difficult to estimate the power-weight ratio, but the specific power output of such an engine, measured in units of kW/1, is shown to be very high. In addi

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14

CHIESA, Sergio, Marco FIORITI, and Roberta FUSARO. "POSSIBLE HYBRID PROPULSION CONFIGURATION FOR TRANSPORT JET AIRCRAFT." Aviation 20, no. 3 (2016): 145–54. http://dx.doi.org/10.3846/16487788.2016.1200849.

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This research is aimed at studying the possible advantages of installing, for a hybrid propulsion aircraft, electric motors and related propellers into the dedicated supplementary nacelles. This innovative solution is different from the configuration, already studied for a regional turboprop (Chiesa et al.2013), in which the electric motors are in the same nacelles of the internal combustion engines. As it has been expected, it offers the advantages of avoiding mechanical links between the two units and, more importantly, can also be applied to jet aircraft. In fact, the main contribution of e

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15

Лось, Александр Васильевич, Владимир Федорович Шмырев та Виктор Иванович Рябков. "ДОСТИЖЕНИЕ ПРЕИМУЩЕСТВА Ан-188 СРЕДИ ОПЕРАТИВНО–ТАКТИЧЕСКИХ ВОЕННО-ТРАНСПОРТНЫХ САМОЛЕТОВ". Aerospace technic and technology, № 8 (31 серпня 2020): 5–11. http://dx.doi.org/10.32620/aktt.2020.8.01.

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In the "Antonov" Company, a unique medium-sized tactical military transport aircraft An-12 and An-70 have been created. Based on the Аn-12 basic version, several modifications have been developed, which operate in many countries around the world.To replace this aircraft has been created the An-70 with a higher capacity and hourly capacity, which on some key parameters outperforms the competition-analogs: American C-130J-30, West-European A400M, and Japanese C-2.However, the range with the maximum capacity is worse for Аn-77 compared to the A400M, but cruising speed and combat readiness – for C

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16

Smolentsev, Evgeniy, Kirill Milinchuk, and Vasily Gritsyuk. "TECHNOLOGICAL EQUIPMENT OF ELECTROEROSION TREATMENT FOR OBTAINING COMPLEX PROFILE HOLES IN THE HOUSINGS OF TURBOPUMP UNITS." Voronezh Scientific-Technical Bulletin, December 10, 2022, 11–17. http://dx.doi.org/10.34220/2311-8873-2022-11-17.

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The article discusses the design and purpose of a turbopump unit, in particular the pump housing of a turbopump unit of a liquid rocket engine. A device and a tool for obtaining complex profile holes in the housings of turbopump units are presented. The features of the design of techno-logical equipment for electrical discharge machining are considered. The proposed progressive design of the device and tool made it possible to process the parts of the turbopump unit of a liquid rocket engine with special holes.

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17

Verbovyi, A., V. Khomenko, C. Neamtu, et al. "Parameter Identification of Nonlinear Bearing Stiffness for Turbopump Units of Liquid Rocket Engines Considering Initial Gaps and Axial Preloading." Journal of Engineering Sciences 8, no. 2 (2021). http://dx.doi.org/10.21272/jes.2021.8(2).d2.

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This article is devoted to developing a mathematical model of nonlinear bearing supports for turbopump units of liquid rocket engines considering initial gaps and axial preloading. In addition to the radial stiffness of the bearing support, this model also considers the stiffness of the bearing cage, the rotational speed of the rotor, axial preloading of the rotor (due to which the inner cage shifts relative to the outer, changing the radial stiffness of the support), as well as radial gaps between contact elements of the bearings. This model makes it possible to calculate the stiffness of the

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18

Brikner, Natalya A., William G. Gardner, and Jonathan M. Protz. "Investigation of Heat Transfer and Scale Effects on the Performance of a Giffard Injector-Pumped Microrocket." Journal of Thermal Science and Engineering Applications 3, no. 4 (2011). http://dx.doi.org/10.1115/1.4005074.

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A novel approach to propellant pressurization for microscale rocket engines is introduced. The Giffard injector is shown to be a viable alternative to turbomachinery for pressurizing the liquid propellants on board a microrocket, offering a design free of moving parts. Extending the authors’ previous work, the engine performance is computed for several fuel/oxidizer combinations. A large-scope study of the heat transfer throughout the regenerative cooling engine cycle examines the effects of combustion chamber pressure and engine size on performance. A boiler is designed that facilitates the h

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19

Yi, Howon, Kyuman Kim, Hyunsung Jung, and Keun Ryu. "Dynamic Response of a Rotor Supported On Hybrid Bearings in Air, Water, and Liquid Nitrogen: Measurements and Comparisons to Predictions." Journal of Engineering for Gas Turbines and Power, September 13, 2024, 1–50. http://dx.doi.org/10.1115/1.4066539.

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Abstract Modern liquid rocket engine turbopumps implement hybrid bearings, which combine hydrostatic and hydrodynamic fluid film principles, in compact and lightweight units known for their superior reusability, durability, and reliability. This study aims to provide extensive and reliable test data for the purpose of anchoring and benchmarking predictive tools for these bearings. This paper provides comprehensive dynamic response measurements of a rotor weighing 10.40 kg and approximately 60 mm in diameter at the bearing locations. The bearings are tested with air, water, and liquid nitrogen,

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