Search Results for “Golovin D. Y.” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 02 Apr 2024 10:53:04 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “Golovin D. Y.” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 10.2.2018 Calculation of Gas Flow in High-Altitude Engine Nozzle and Experience of Using Water-Cooled Nozzle Head during Tests https://journal.yuzhnoye.com/content_2018_2-en/annot_10_2_2018-en/ Thu, 07 Sep 2023 11:29:45 +0000 https://journal.yuzhnoye.com/?page_id=30766
The gas dynamic analysis of the nozzle with water-cooled extension showed the importance of using the turbulent flow model k-ω SST for the flows with internal separation of boundary layer and with flow separation at nozzle section. A one-equation turbulence model for aerodynamic flows: Technical Report. Performance Analysis of Secondary Gas Injection into a Conical Rocket Nozzle. A., Adler D., Bar-Yoseph P. Östlund J., Damgaard T., Frey M. Golovin V.S., Kolchugin B.A., Labuntsov D.A. 2nd edition stereotyped. Heat-Mass Exchange and Friction in Turbulent Boundary Layer. More Citation Formats Harvard Chicago IEEE AIP ДСТУ 8302:2015 ДСТУ ГОСТ 7.1:2006 (ВАК) ISO 690:2010 BibTeX Keywords cloud Your browser doesn't support the HTML5 CANVAS tag.
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10. Calculation of Gas Flow in High-Altitude Engine Nozzle and Experience of Using Water-Cooled Nozzle Head during Tests

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 83-93

DOI: https://doi.org/10.33136/stma2018.02.083

Language: Russian

Annotation: At Yuzhnoye State Design Office, the Cyclone-4 launch vehicle 3rd stage engine has been developed and is under testing. For adjustment of the engine and test bench systems, in the first firing tests the radiation-cooled nozzle extension was replaced with a steel water-cooled one. It was planned to start the engine with water-cooled nozzle extension without vacuumizing and without gad dynamic pipe, which conditioned operation with flow separation at the output edge of water-cooled nozzle extension. Therefore, the calculation of flow in the nozzle with water-cooled extension, flow separation place, and thermal load on watercooled nozzle extension during operation in ground conditions is an important task. Selection of turbulent flow model has a noticeable impact on prediction of flow characteristics. The gas dynamic analysis of the nozzle with water-cooled extension showed the importance of using the turbulent flow model k-ω SST for the flows with internal separation of boundary layer and with flow separation at nozzle section. The use the flow model k-ω SST for calculation of nozzle with flow separation or with internal transitional layer allows adequately describing the flow pattern, though, as the comparison with experimental data showed, this model predicts later flow separation from the wall than that obtained in the tests. The calculation allows obtaining a temperature profile of the wall and providing the recommendations for selection of pressure measurement place in the nozzle extension for the purpose of reducing sensors indication error. With consideration for the special nature of the nozzle extension wall temperature field, the cooling mode was selected. The tests of RD861K engine nozzle with water-cooled extension allow speaking about its successful use as a required element for testing engine start and operation in ground conditions without additional test bench equipment.

Key words: turbulent flow, flow separation, cooling, technological extension

Bibliography:
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2. Mezhevov A. V., Skoromnov V. I., Kozlov A. V. et al. Introduction of Radiation Cooling Nozzle Head of Made of Carbon-Carbon Composite Material on DM-SL Upper Stage 11D58M Main Engine. News of Samara Aerospace University. No. 2 (10). 2006. P. 260-264.
3. Fluent. Software Package, Ver. 6.2.16, Fluent Inc., Lebanon, NH, 2004.
4. Wilcox D. C. Turbulence Modeling for CFD. DCW Industries, Inc. La Canada, California, 1998. 460 р.
5. Andersen D., Tannehill J., Platcher R. Computational Hydromechanics and Heat Exchange: in 2 volumes М., 1990. 384 p.
6. Rodriguez C. G., Culter, A. D. Numerical Analysis of the SCHOLAR Supersonic Combustor, NASA-CR-2003-212689. 2003. 36 р.
7. Rajasekaran A., Babu V. Numerical Simulation of Three-dimensional Reacting Flow in a Model Supersonic Combustor. Journal of Propulsion and Power. Vol. 22. No. 4. 2006. Р. 820-827. https://doi.org/10.2514/1.14952
8. Spalart P., Allmaras S. A one-equation turbulence model for aerodynamic flows: Technical Report. American Institute of Aero-nautics and Astronautics. AIAA-92-0439. 1992. Р. 5-21. https://doi.org/10.2514/6.1992-439
9. Launder B. E., Spalding D. B. Lectures in Mathematical Models of Turbulence. London, 1972. Р. 157-162.
10. Rajasekaran A., Babu V. Numerical Simulation of Three-dimensional Reacting Flow in a Model Supersonic Combustor. Journal of Propulsion and Power. Vol. 22. No. 4. 2006. Р. 820-827. https://doi.org/10.2514/1.14952
11. Ten-See Wang. Multidimensional Unstructured Grid Liquid Rocket-Engine Nozzle Performance and Heat Transfer Analysis. Journal of Propulsion and Power. Vol. 22. No. 1. 2006. 21 р. https://doi.org/10.2514/1.14699
12. Hyun Ko, Woong-Sup Yoon. Performance Analysis of Secondary Gas Injection into a Conical Rocket Nozzle. Journal of Propulsion and Power. Vol. 18, No. 3. 2002. Р. 585-591. https://doi.org/10.2514/2.5972
13. Wilson E. A., Adler D., Bar-Yoseph P. Thrust-Vectoring Nozzle Performance Mode-ling. Journal of Propulsion and Power. Vol. 19, No. 1. 2003. Р. 39-47. https://doi.org/10.2514/2.6100
14. Gross A., Weiland C. Numerical Simulation of Hot Gas Nozzle Flows. Journal of Propulsion and Power. Vol. 20, No. 5. 2004. Р. 879-891. https://doi.org/10.2514/1.5001
15. Gross A., Weiland C. Numerical Simulation of Separated Cold Gas Nozzle Flows. Journal of Propulsion and Power. Vol. 20, No. 3. 2004. Р. 509-519. https://doi.org/10.2514/1.2714
16. Deck S., Guillen P. Numerical Simulation of Side Loads in an Ideal Truncated Nozzle. Journal of Propulsion and Power. Vol. 18, No. 2. 2002. Р. 261-269. https://doi.org/10.2514/2.5965
17. Östlund J., Damgaard T., Frey M. Side-Load Phenomena in Highly Overexpanded Rocket Nozzle. Journal of Propulsion and Power. Vol. 20, No. 4. 2004. Р. 695-704. https://doi.org/10.2514/1.3059
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21. Kutateladze S. S., Leontyev A. I. Heat-Mass Exchange and Friction in Turbulent Boundary Layer. М., 1972. 341 p.
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10.2.2018 Calculation of Gas Flow in High-Altitude Engine Nozzle and Experience of Using Water-Cooled Nozzle Head during Tests
10.2.2018 Calculation of Gas Flow in High-Altitude Engine Nozzle and Experience of Using Water-Cooled Nozzle Head during Tests
10.2.2018 Calculation of Gas Flow in High-Altitude Engine Nozzle and Experience of Using Water-Cooled Nozzle Head during Tests

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9.2.2017 Peculiarities of Development of Cryogenic Propulsion System Circulating Cooling System https://journal.yuzhnoye.com/content_2017_2/annot_9_2_2017-en/ Wed, 09 Aug 2023 11:22:39 +0000 https://journal.yuzhnoye.com/?page_id=29767
Peculiarities of Development of Cryogenic Propulsion System Circulating Cooling System Authors: Golovin D. Peculiarities of Development of Cryogenic Propulsion System Circulating Cooling System Автори: Golovin D. Peculiarities of Development of Cryogenic Propulsion System Circulating Cooling System Автори: Golovin D. Peculiarities of Development of Cryogenic Propulsion System Circulating Cooling System Автори: Golovin D. Peculiarities of Development of Cryogenic Propulsion System Circulating Cooling System Автори: Golovin D.
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9. Peculiarities of Development of Cryogenic Propulsion System Circulating Cooling System

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (2); 49-52

Language: Russian

Annotation: The paper describes the experiments of cryogenic engine unit circulatory cooling system, considers the developed technique of circulation parameters evaluation and gives the comparison of calculated and experimental data on this system.

Key words:

Bibliography:
1. Evaluation of Parameters of Liquid Oxygen Circulation in Cryogenic LRPS Cooling System: Technical Note 22.8234.123 ST. Yuzhnoye SDO.
2. Kutepov A. M., Sterman L. S., Styushin N. G. Hydrodynamics and Heat Exchange at Vapor Formation. М., 1986.
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9.2.2017 Peculiarities of Development of Cryogenic Propulsion System Circulating Cooling System
9.2.2017 Peculiarities of Development of Cryogenic Propulsion System Circulating Cooling System
9.2.2017 Peculiarities of Development of Cryogenic Propulsion System Circulating Cooling System
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7.2.2017 Features of Pneumatic Hydraulic Feeding System with the Use of Oxygen-Methane Cryogenic Propellants https://journal.yuzhnoye.com/content_2017_2/annot_7_2_2017-en/ Tue, 08 Aug 2023 12:43:00 +0000 https://journal.yuzhnoye.com/?page_id=29758
, Golovin D. Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine Page: Kosm. 2017 (2); 35-40 Language: Russian Annotation: The paper presents the results of comparative investigation into characteristics of methane, kerosene and hydrogen in pair with oxygen. The optimal parameters are considered of pneumohydraulic supply system, including the designs of tanks, pressurization system and engine supply lines cooling system. Key words: Bibliography: 1. System, Sensitivity Studies of a LOX/Methane Expander Cycle Upper Stage Engine. Kyoung-Ho Kim, Dae-Sung Ju. Evaluation of Parameters of Liquid Oxygen Circulation in Cryogenic LRPS Colling System: Technical Note 22.8234.123 ST / Yuzhnoye SDO. Pneumohydraulic Systems. А., Golovin D. А., Golovin D. А., Golovin D. А., Golovin D. А., Golovin D. А., Golovin D.
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7. Features of Pneumatic Hydraulic Feeding System with the Use of Oxygen-Methane Cryogenic Propellants

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (2); 35-40

Language: Russian

Annotation: The paper presents the results of comparative investigation into characteristics of methane, kerosene and hydrogen in pair with oxygen. The peculiarities of each of these components are shown. The optimal parameters are considered of pneumohydraulic supply system, including the designs of tanks, pressurization system and engine supply lines cooling system.

Key words:

Bibliography:
1. Tamura H., Ono F., Kumakawa A. LOX/Methane Staged Combustion Rocket Investigation. AIAA 87-1856.
2. Crocker A., Perry S. System, Sensitivity Studies of a LOX/Methane Expander Cycle Upper Stage Engine. AIAA 98-3674.
3. Kyoung-Ho Kim, Dae-Sung Ju. Development of “Chase-10” liquid rocket engine having 10tf thrust using LOX & LNG (Methane). AIAA-2006-4907. 2014.
4. Evaluation of Parameters of Liquid Oxygen Circulation in Cryogenic LRPS Colling System: Technical Note 22.8234.123 ST / Yuzhnoye SDO. 2014.
5. Belyayev N. M. Pneumohydraulic Systems. Calculation and Designing. М., 1988. 42 p.
6. Pavlyuk Y. S. Ballistic Designing of Rockets: Tutorial for universities. Chelyabinsk, 1996. 92 p.
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7.2.2017 Features of Pneumatic Hydraulic Feeding System with the Use of Oxygen-Methane Cryogenic Propellants
7.2.2017 Features of Pneumatic Hydraulic Feeding System with the Use of Oxygen-Methane Cryogenic Propellants
7.2.2017 Features of Pneumatic Hydraulic Feeding System with the Use of Oxygen-Methane Cryogenic Propellants
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