METHODS FOR COOLING THE HOT ZONE OF HEAT ENGINES AND TECHNOLOGICAL TECHNIQUES FOR IMPLEMENTING THE METHODS

2020 ◽  
pp. 10-14
Author(s):  
E. V. Panichev ◽  
V. P. Smolentsev ◽  
A. V. Shchednov
Keyword(s):  
Combustion Chamber ◽  
Protective Coatings ◽  
Rocket Engines ◽  
Internal Cooling ◽  
Fuel Component ◽  
Cooling Systems ◽  
Cooling Medium ◽  
Aerospace Technology ◽  
Liquid Rocket ◽  
Hot Zone

Various types of hot zone cooling systems for liquid rocket engines are considered. The analysis of systems for external and internal cooling of the hot zone of the combustion chamber and the jet co-PLA is performed. The area of primary use of external and internal impact of components on the combustion chamber and the jet nozzle of a temporary product with a high thermal load on the material is given. Recommendations on the choice of technological methods for processing heat-protective coatings were developed, where the advantages of combined electroabrasive treatment were revealed. In this case, the possibility of finishing the transition sections of the path from areas that are difficult to access for the tool, which have coatings with ceramic granules that have been used in the latest products of aerospace technology, is shown. The mechanism of heat transfer by the cooling medium from the areas of the greatest heating, as a rule, to the flow of the liquid fuel component of the fuel is shown. Examples of implementation of modern cooling systems on typical designs of combustion chambers of modern rocket engines are considered. It is shown that the cooling efficiency will be higher the more belts of the cooling medium curtain are located along the length of the combustion chamber. At the same time, it should be taken into account that the use of an excessively large number of belts means a significant complication of the camera design, its manufacturing technology, and an increase in the cost of the product.

Investigation of the Properties of Heat-Protective Coatings to Improve the Performance of Products

2021 ◽  
Vol 1037 ◽  
pp. 516-521
Author(s):  
Vladislav Smolentsev ◽  
Nikolay Nenahov ◽  
Natalia Potashnikova
Keyword(s):  
Combustion Chamber ◽  
Protective Coatings ◽  
Rocket Engine ◽  
Multilayer Coating ◽  
Surface Preparation ◽  
Rocket Engines ◽  
Initial Surface ◽  
Technological Parameters ◽  
Materials Used ◽  
Liquid Rocket

The heat-loaded part of the combustion chamber of a liquid rocket engine are Considered. The proposed coating has several layers: an internal metal coating that contacts the part or substrate, and an external coating made of a mixture of ceramic granules and metal powder. At the same time, to obtain the initial surface for coating with the required surface layer roughness, it is proposed to use the method of sand blasting. The article analyzes possible mechanisms of material formation for "base-coating" transition zones, as well as the influence of their chemical composition on the adhesive strength of layers.. The choice of brand and combination of materials used for coating is justified. Technological modes that have been tested in production conditions when applying heat-resistant coatings to parts of modern rocket engines are proposed. The influence of technological parameters of the initial surface preparation process and the geometry of the resulting micro-relief of the substrate on the adhesion characteristics of a multilayer coating made of heat-protective materials operating in the high-temperature zone of the combustion chamber of liquid rocket engines is revealed.

Innovative methods for obtaining artificial roughness on the surfaces of heat-loaded parts of the liquid rocket engine combustion chambers

2020 ◽  
Author(s):  
A.Yu. Ryazantsev ◽  
S.S. Yukhnevich ◽  
A.A. Shirokozhukhova
Keyword(s):  
Combustion Chamber ◽  
Rocket Engine ◽  
Empirical Studies ◽  
Aerospace Industry ◽  
Rocket Engines ◽  
Artificial Roughness ◽  
Special Equipment ◽  
Liquid Rocket Engines ◽  
Engine Combustion ◽  
Liquid Rocket

The paper shows the applications of combined processing in the manufacture of parts and assembly units of liquid rocket engines in the aerospace industry. The most effective methods of obtaining artificial roughness on the surfaces of special equipment products are considered. Empirical studies of changes in the physical and mechanical properties of the material are performed using various methods of combined processing. Qualitative and quantitative relationships between the hydraulic characteristics of the rocket engine combustion chamber manufactured using the combined method, and the quality of the surface layer of the product are described and formalized. The analysis of modern processing methods is performed, and the latest methods for obtaining artificial roughness on the surfaces of rocket engine parts are presented. The relevance and need for the use of high-end technology in obtaining surface layers of products included in the structure of the combustion chamber of liquid rocket engines are proved. The results obtained allow significant expanding the technological capabilities of production, as well as appreciable improving the technical characteristics of special equipment products in the aerospace industry.

Technology for fi nishing combined processing of mineral-ceramic coatings

2020 ◽  
pp. 318-323
Author(s):  
E.V. Panichev ◽  
V.P. Smolentsev ◽  
V.V. Ivanov
Keyword(s):  
Surface Layer ◽  
Protective Coatings ◽  
Combustion Products ◽  
Ceramic Coatings ◽  
Fuel Combustion ◽  
Rocket Engines ◽  
Combustion Chambers ◽  
Temperature Combustion ◽  
Liquid Rocket ◽  
Processing Zone

Technological methods for manufacturing of cooling elements of modern rocket engines are considered, they are developed taking into account the possibility of reusable use. Significant increase in the thermal load on the walls of combustion chambers of liquid rocket engines required the creation of new ways to protect the surface layer of the hot zone from the effects of the flame in the fuel combustion zone. The possibilities for using of plasma application of metal-ceramic heat-protective coatings for these purposes, which have good erosion resistance and high thermal resistance in conditions of intense exposure to high-temperature combustion products, are revealed. The analysis of the effect of the quality of the coatings surface layer on the performance characteristics of the product is presented. The need for local finishing of the applied coatings is justified, including in the transition areas of the combustion chambers and the jet nozzle, which have limited tool access to the processing zone. The most effective method is the combined alignment of the microprofile with the imposition of electric field. But for its implementation, set of studies is needed to study the mechanism of allowance removing, and to adjust the technological modes. The task of minimizing allowances for finishing combined processing is solved, which allowed to align the thickness of the heat-protective coating along the length of the fuel combustion path, including the cleaning sections, to increase the number of trouble-free engine starts by 1.5...2.0 times and ensure reusable use of product.

scholarly journals Toxic effect of 2,2’-bis(bicyclo[2.2.1] heptane) on bacterial cells

2020 ◽  
Author(s):  
A. G. Kessenikh ◽  
L. S. Yaguzhinsky ◽  
M. V. Bermeshev ◽  
V. G. Pevgov ◽  
V. O. Samoilov ◽  
...  
Keyword(s):  
Rocket Engines ◽  
Oxygen Species ◽  
Bacterial Cells ◽  
Mechanism Of Formation ◽  
Fuel Component ◽  
E Coli ◽  
Liquid Rocket Engines ◽  
Lux Biosensor ◽  
Liquid Rocket ◽  
Oxidative Effect

ABSTRACTHere we present the study of the genotoxic effect of a 2,2’-bis(bicyclo[2.2.1]heptane) (BBH), which is promising as a fuel component for liquid rocket engines. The use of Escherichia coli lux-biosensors showed that in addition to DNA damage causing SOS-response, there is also an oxidative effect on cells. The greatest toxicity is determined by the mechanism of formation of superoxide anion radical and is detected by the lux biosensor E. coli pSoxS-lux, in which the genes of bacterial luciferases are transcriptionally crosslinked with the promoter of the soxS gene. It is assumed that the oxidation of BBH leads to the formation of reactive oxygen species, which should give the main contribution to the toxicity of this substance.

EVALUATION OF SMD EFFECTS ON CHARACTERISTIC LENGTHS OF LIQUID ROCKET ENGINES USING ETHANOL/LOX AND RP-1/LOX

2020 ◽  
Author(s):  
Maurício Sá Gontijo ◽  
Gustavo Alexandre Achilles Fischer ◽  
FERNANDO DE SOUZA COSTA
Keyword(s):  
Rocket Engines ◽  
Liquid Rocket Engines ◽  
Liquid Rocket

SIMULATION OF THE CURRENT-VOLTAGE CHARACTERISTICS OF SOLAR BATTERIES WITH CONSIDERING DECREASE OF LIGHTING DUE TO THE INFLUENCE OF JETS OF THE ELECTRIC PROPULSION

2019 ◽  
pp. 56-64
Author(s):  
Ya.N. MIGUNOV ◽  
V.V. ONUFRIEV
Keyword(s):  
Solar Cells ◽  
Temperature Gradient ◽  
Electric Propulsion ◽  
Protective Coatings ◽  
Rocket Engine ◽  
Solar Array ◽  
Rocket Engines ◽  
Lighting Conditions ◽  
Main Equation ◽  
Voltage Current Characteristic

A model for calculating the voltage-current characteristic of a solar array in the presence of a temperature gradient by its photovoltaic converters and their variable illumination due to possible pollution under the action of space factors, including operation of electric rocket engines, is described. The model is based on the main equation of a solar cell. In this case both a one-dimensional and a two-dimensional temperature gradients are taken into account. The principles of constructing a model are given, and the initial data selection is made. To simulate the lighting conditions of the solar array such a concept as effective illumination is used, i.e. the density of the radiation flux which falls on photovoltaic converters passing through the protective coatings. The features of simulation of the temperature distribution in the solar array and the effective illumination of its surface in cases of parallel, serial and mixed switching of solar cells are described. The calculation procedures and examples of solar cells are given. The construction of the model in universal mathematical package Mathcad is described. Some simulation results are discussed. Key words: solar array, mathematical simulation, illumination, temperature gradient, electric rocket engine, spacecraft, Mathcad.

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