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Relevant bibliographies by topics / Turbopump units

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Academic literature on the topic 'Turbopump units'

Author: Grafiati

Published: 28 May 2022

Last updated: 30 July 2025

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Journal articles on the topic "Turbopump units"

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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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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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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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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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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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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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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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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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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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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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Dissertations / Theses on the topic "Turbopump units"

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Горовий, С. О. "Динамічна стійкість робочого органа турбонасосного агрегату пластової рідини". Thesis, Вид-во СумДУ, 2002. http://essuir.sumdu.edu.ua/handle/123456789/21157.

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Павленко, Іван Володимирович, Иван Владимирович Павленко, Ivan Volodymyrovych Pavlenko та ін. "Визначення радіальної та осьової жорсткості підшипникових опор турбонасосних агрегатів". Thesis, Сумський державний університет, 2018. http://essuir.sumdu.edu.ua/handle/123456789/67573.

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Масалітін, І. О. "Комп'ютерний аналіз ротородинамічних характеристик лабіринтних і демпферних ущільнень". Thesis, Сумський державний університет, 2015. http://essuir.sumdu.edu.ua/handle/123456789/39755.

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В даний час все частіше застосовуються ротори, що швидко обертаються з кутовою швидкістю в кілька десятків і сотень тисяч обертів за хвилину. Газотурбінні двигуни з високою питомою потужністю, компресори та гідронасоси з великим напором, центрифуги, - це далеко не повний перелік машин, в яких основним шляхом технічного прогресу є збільшення частоти обертання їх головного робочого органу - ротора. З цієї причини, насамперед для турбонасосних агрегатів рідинних ракетних двигунів, розробляються так звані гнучкі ротори, швидкість обертання яких вище першої або навіть другої власної частоти

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Neklapil, Libor. "Návrh souosého vysokootáčkového reduktoru." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2008. http://www.nusl.cz/ntk/nusl-228136.

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The thesis deal with design of coaxial high-speed gear box for small-scale turboshaft engines. At the beginning a study of problems was performed and for design concept was elected version of single-shaft turbo-engine with electric generator. Kinematic diagram, type of gear design, material and lubrication method was designed. Further was solved proposal of basic gearing parameters, choice of the number of tooth and basic proposal calculations were performed. Was performed check calculation of gearing, calculation of bearings durability and was processed design documentation in required range.

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Books on the topic "Turbopump units"

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National Aeronautics and Space Administration (NASA) Staff. Liquid Hydrogen Turbopump ALS Advanced Development Program. Volume 1: Hot Fire Unit. Independently Published, 2018.

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Book chapters on the topic "Turbopump units"

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Pavlenko, Ivan, Vitalii Ivanov, Ivan Kuric, Oleksandr Gusak, and Oleksandr Liaposhchenko. "Ensuring Vibration Reliability of Turbopump Units Using Artificial Neural Networks." In Lecture Notes in Mechanical Engineering. Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-18715-6_14.

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Conference papers on the topic "Turbopump units"

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Demjanenko, Yury, Anatoli Dmitrenko, and Valery Pershin. "Experience of Developing Liquid Propulsion Rocket Engine Assembly Feed Systems Using Boost Turbopump Units." In 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-5072.

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Pai, Shantaram S., and David S. Riha. "Model Verification and Validation Concepts for a Probabilistic Fracture Assessment Model to Predict Cracking of Knife Edge Seals in the Space Shuttle Main Engine High Pressure Oxidizer." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-70132.

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Physics-based models are routinely used to predict the performance of engineered systems to make decisions such as when to retire system components, how to extend the life of an aging system, or if a new design will be safe or available. Model verification and validation (V&V) is a process to establish credibility in model predictions. Ideally, carefully controlled validation experiments will be designed and performed to validate models or submodels. In reality, time and cost constraints limit experiments and even model development. This paper describes elements of model V&V during the

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Kosykh, Dmytro. "REVIEW OF THE APPLICATION OF AN AUTOMATIC UNLOADING DEVICE IN THE TURBOPUMP UNITS FOR STAGE COMBUSTION LIQUID ROCKET ENGINES WITH THRUST UP TO 10 TONS." In XXVІІ International youth scientific and practical conference «Human and Space». О.М. Makarov National youth aerospace education center, 2025. https://doi.org/10.62717/2221-4550-2025-1-030.

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Osborn, Douglas M., Kyle Ross, Jeff Cardoni, et al. "Terry Turbopump Expanded Operating Band." In ASME/NRC 2017 13th Pump and Valve Symposium. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/pvs2017-3508.

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The Terry turbine is a small, single-stage, compound-velocity impulse turbine originally designed and manufactured by the Terry Steam Turbine Company purchased by Ingersoll-Rand in 1974. Terry turbines are currently manufactured and marketed by Dresser-Rand. Terry turbines were principally designed for waste-steam applications. Terry turbopumps are ubiquitous to the US nuclear fleet as a steam driven turbopump in either the reactor core isolation cooling system (RCIC) and high pressure coolant injection systems for boiling water reactors (BWRs) or in the auxiliary feedwater system (AFW) system

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Everaldo de Barros, Daniel Fraga Sias, Carlos dAndrade Souto, and Daniel Soares de Almeida. "DYNAMIC ANALYSIS OF A LIQUID ROCKET TURBOPUMP UNIT." In 23rd ABCM International Congress of Mechanical Engineering. ABCM Brazilian Society of Mechanical Sciences and Engineering, 2015. http://dx.doi.org/10.20906/cps/cob-2015-1034.

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Stewart, J. D. "Operation of the CT7 Turboprop Engine as an Auxiliary Power Unit (APU)." In ASME 1986 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1986. http://dx.doi.org/10.1115/86-gt-28.

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In response to the need of the new generation of commuter airliners, General Electric has developed the CT7 Turboprop engine so that it may be used as an Auxiliary Power Unit (APU) in addition to its normal mission as a prime propulsion unit. The General Electric CT7 Turboprop is a 1700 shaft horsepower class engine (Figure 1) developed for the new generation of 30+ passenger commuter and executive aircraft(1). Beyond this, the CT7 engine now offers the airlines a self-contained APU system to provide bleed air for the Environmental Control System (ECS) and electrical power for the aircraft dur

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Gurov, V. "Operational reliability of turbopump - key unit of the liquid rocket engines." In 37th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-3395.

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Zubanov, Vasilii, Andrei Volkov, Valeriy Matveev, Grigorii Popov, and Oleg Baturin. "Optimization of Fuel Two-Stage Screw Centrifugal Pump of Rocket Powerful Turbopump Unit." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76400.

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The article describes a refining method for a fuel pump of rocket powerful turbo-pump unit by the joint usage of mathematical optimization software IOSO, meshing complex NUMECA and CFD complex ANSYS CFX. The optimization software was used for automatic change of the geometry of low-pressure impeller, transition duct and high-pressure impeller to find the optimal design. It was mandatory to keep the original variant of the remaining parts of the pump. For this reason, only geometrical parameters of the blades were varied without changing the contours of the pump meridional flow part. The invest

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Maeding, C., L. Souverein, D. Hummel, S. Koenigbauer, A. Wagner, and J. Alting. "A preliminary design study for an expander liquid oxygen turbopump." In Progress in Propulsion Physics – Volume 11. EDP Sciences, 2019. http://dx.doi.org/10.1051/eucass/201911571.

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In the recent years, Airbus DS GmbH started a turbopump initiative to buildup fundamental capabilities in analyzing and designing turbomachinery within a German national funded program “TARES.” Turbomachinery is widely used in different rocket propulsion systems and include such parts as pumps and turbines. Turbines are used for generating power required by pumps in order to feed the propellants to the thrust chamber. The paper is dedicated to present an overview about currently ongoing conceptual design activities of turbomachinery covering the main design phases like TPA (TurboPump Assembly)

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Yoon, S. H., S. M. Jeon, and J. Kim. "Transient Thermal and Structural Analysis of the Liquid Rocket Turbopump Turbine." In ASME 2005 Summer Heat Transfer Conference collocated with the ASME 2005 Pacific Rim Technical Conference and Exhibition on Integration and Packaging of MEMS, NEMS, and Electronic Systems. ASMEDC, 2005. http://dx.doi.org/10.1115/ht2005-72070.

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A turbopump unit is a key component of the liquid rocket engine assembly. Generally operated by an impulse-type turbine with supersonic hot gas for a gas generator cycle engine, it pressurizes liquid oxygen and fuel to attain high specific impulse. The turbine is exposed to hot gas while rotating at a high speed and experiences severe thermal and mechanical loads during the operation. Its structural integrity must be assured through thermal and structural analyses of the turbine. To investigate non-steady heat transfer characteristics from the hot gas to the turbine blade, the heat transfer of

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