THERMOPHYSICAL CHARACTERISTICS AND THERMOEROSION RESISTANCE OF CERAMIC MATERIAL BASED ON BORON CARBIDE
A study of the thermophysical characteristics, heat resistance, and thermal erosion resistance of high-temperature structural ceramics (SC), which was developed at NTUU "I. Sikorsky Kyiv Polytechnic Institute" under the supervision of Corresponding Member of the National Academy of Science...
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| Format: | Article |
| Language: | English |
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National Aerospace University «Kharkiv Aviation Institute»
2020-08-01
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| Series: | Авіаційно-космічна техніка та технологія |
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| Online Access: | http://nti.khai.edu/ojs/index.php/aktt/article/view/1206 |
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| author | Юрий Игоревич Евдокименко Ирина Александровна Гусарова Геннадий Александрович Фролов Вячеслав Михайлович Кисель Сергей Васильевич Бучаков |
| author_facet | Юрий Игоревич Евдокименко Ирина Александровна Гусарова Геннадий Александрович Фролов Вячеслав Михайлович Кисель Сергей Васильевич Бучаков |
| author_sort | Юрий Игоревич Евдокименко |
| collection | DOAJ |
| description | A study of the thermophysical characteristics, heat resistance, and thermal erosion resistance of high-temperature structural ceramics (SC), which was developed at NTUU "I. Sikorsky Kyiv Polytechnic Institute" under the supervision of Corresponding Member of the National Academy of Sciences of Ukraine, Professor P. I. Loboda was made. This high-temperature structural ceramics is intended for use in aerospace engineering, in particular - for the manufacture of aerodynamic surfaces of reusable hypersonic aircraft and heat-stressed elements of the gas-dynamic paths of their engines. The samples of B4C-SiC-B6Si ceramics of two compositions (No. 1 and No. 2) were studied, which differ in the mass content of the initial components. Temperature dependences of the specific heat and thermal conductivity of the spacecraft, radiation coefficient, heat resistance in an oxidizing environment, and the thermal erosion resistance in supersonic flow of combustion products of an air-kerosene fuel mixture were determined. The temperature dependence of the specific heat was determined using an IT-c-400 instrument (in the range of 40 °C - 440 °C) and by the calculation of the temperature dependences of the specific heat capacity of the system components following the Reno rule (up to 2100 °C). The temperature dependence of the thermal conductivity coefficient of the SC of composition No. 1 was determined by solving the inverse heat conduction problem on a computer model based on experimental data. Temperature fields and heat fluxes were obtained under conditions of one-sided heat-ing with a reducing flame of a propane-oxygen welding burner. The thermal conductivity coefficient of SC composition No. 1 increases from 11 W/(m×K) at 20 °С to 25 W/(m×K) at 1400 °С. Its radiation coefficient in the temperature range 1000 °С - 1400 °С is ε = 0.96 ± 0.02. Heat resistance of SC of both compositions in the oxidizing flame of an oxygen welding burner at a surface temperature of 1400 °C has demonstrated that after two hours of heating, the average values of mass ablation for the two tested samples of compositions №1 and № 2 respectively 2.1% and 1.4% (a sample thickness of 4 mm). Tests in the supersonic flow of combustion products at the same surface temperature confirm the high resistance of the material to thermoerosion in the oxidizing medium. The change in the morphology of the heated surface of the sample after six five-minute heating cycles was manifested only by an increase in its roughness without visible oxidation. High thermal conductivity, heat and thermoerosion resistance, radiation coefficient of the studied SC at a temperature of 1400 °C in combination with low density (2.7 g / cm3) make this high-temperature structural material of aerospace technology promising for use. |
| first_indexed | 2024-03-12T07:06:14Z |
| format | Article |
| id | doaj.art-7c01ee0c1ca84abfb9bf25f902566009 |
| institution | Directory Open Access Journal |
| issn | 1727-7337 2663-2217 |
| language | English |
| last_indexed | 2024-03-12T07:06:14Z |
| publishDate | 2020-08-01 |
| publisher | National Aerospace University «Kharkiv Aviation Institute» |
| record_format | Article |
| series | Авіаційно-космічна техніка та технологія |
| spelling | doaj.art-7c01ee0c1ca84abfb9bf25f9025660092023-09-02T23:25:47ZengNational Aerospace University «Kharkiv Aviation Institute»Авіаційно-космічна техніка та технологія1727-73372663-22172020-08-010813614510.32620/aktt.2020.8.181225THERMOPHYSICAL CHARACTERISTICS AND THERMOEROSION RESISTANCE OF CERAMIC MATERIAL BASED ON BORON CARBIDEЮрий Игоревич Евдокименко0Ирина Александровна Гусарова1Геннадий Александрович Фролов2Вячеслав Михайлович Кисель3Сергей Васильевич Бучаков4Институт проблем материаловедения им. И.Н. Францевича НАН Украины, КиевГосударственное предприятие КБ «Южное», ДнепрИнститут проблем материаловедения им. И. Н. Францевича НАН Украины, КиевИнститут проблем материаловедения им. И. Н. Францевича НАН Украины, КиевИнститут проблем материаловедения им. И. Н. Францевича НАН Украины, КиевA study of the thermophysical characteristics, heat resistance, and thermal erosion resistance of high-temperature structural ceramics (SC), which was developed at NTUU "I. Sikorsky Kyiv Polytechnic Institute" under the supervision of Corresponding Member of the National Academy of Sciences of Ukraine, Professor P. I. Loboda was made. This high-temperature structural ceramics is intended for use in aerospace engineering, in particular - for the manufacture of aerodynamic surfaces of reusable hypersonic aircraft and heat-stressed elements of the gas-dynamic paths of their engines. The samples of B4C-SiC-B6Si ceramics of two compositions (No. 1 and No. 2) were studied, which differ in the mass content of the initial components. Temperature dependences of the specific heat and thermal conductivity of the spacecraft, radiation coefficient, heat resistance in an oxidizing environment, and the thermal erosion resistance in supersonic flow of combustion products of an air-kerosene fuel mixture were determined. The temperature dependence of the specific heat was determined using an IT-c-400 instrument (in the range of 40 °C - 440 °C) and by the calculation of the temperature dependences of the specific heat capacity of the system components following the Reno rule (up to 2100 °C). The temperature dependence of the thermal conductivity coefficient of the SC of composition No. 1 was determined by solving the inverse heat conduction problem on a computer model based on experimental data. Temperature fields and heat fluxes were obtained under conditions of one-sided heat-ing with a reducing flame of a propane-oxygen welding burner. The thermal conductivity coefficient of SC composition No. 1 increases from 11 W/(m×K) at 20 °С to 25 W/(m×K) at 1400 °С. Its radiation coefficient in the temperature range 1000 °С - 1400 °С is ε = 0.96 ± 0.02. Heat resistance of SC of both compositions in the oxidizing flame of an oxygen welding burner at a surface temperature of 1400 °C has demonstrated that after two hours of heating, the average values of mass ablation for the two tested samples of compositions №1 and № 2 respectively 2.1% and 1.4% (a sample thickness of 4 mm). Tests in the supersonic flow of combustion products at the same surface temperature confirm the high resistance of the material to thermoerosion in the oxidizing medium. The change in the morphology of the heated surface of the sample after six five-minute heating cycles was manifested only by an increase in its roughness without visible oxidation. High thermal conductivity, heat and thermoerosion resistance, radiation coefficient of the studied SC at a temperature of 1400 °C in combination with low density (2.7 g / cm3) make this high-temperature structural material of aerospace technology promising for use.http://nti.khai.edu/ojs/index.php/aktt/article/view/1206конструкционная керамикасистема b4c-sic-b6siтеплофизические характеристикивысокотемпературные испытанияжаростойкостьстойкость к термоэрозионному воздействию |
| spellingShingle | Юрий Игоревич Евдокименко Ирина Александровна Гусарова Геннадий Александрович Фролов Вячеслав Михайлович Кисель Сергей Васильевич Бучаков THERMOPHYSICAL CHARACTERISTICS AND THERMOEROSION RESISTANCE OF CERAMIC MATERIAL BASED ON BORON CARBIDE Авіаційно-космічна техніка та технологія конструкционная керамика система b4c-sic-b6si теплофизические характеристики высокотемпературные испытания жаростойкость стойкость к термоэрозионному воздействию |
| title | THERMOPHYSICAL CHARACTERISTICS AND THERMOEROSION RESISTANCE OF CERAMIC MATERIAL BASED ON BORON CARBIDE |
| title_full | THERMOPHYSICAL CHARACTERISTICS AND THERMOEROSION RESISTANCE OF CERAMIC MATERIAL BASED ON BORON CARBIDE |
| title_fullStr | THERMOPHYSICAL CHARACTERISTICS AND THERMOEROSION RESISTANCE OF CERAMIC MATERIAL BASED ON BORON CARBIDE |
| title_full_unstemmed | THERMOPHYSICAL CHARACTERISTICS AND THERMOEROSION RESISTANCE OF CERAMIC MATERIAL BASED ON BORON CARBIDE |
| title_short | THERMOPHYSICAL CHARACTERISTICS AND THERMOEROSION RESISTANCE OF CERAMIC MATERIAL BASED ON BORON CARBIDE |
| title_sort | thermophysical characteristics and thermoerosion resistance of ceramic material based on boron carbide |
| topic | конструкционная керамика система b4c-sic-b6si теплофизические характеристики высокотемпературные испытания жаростойкость стойкость к термоэрозионному воздействию |
| url | http://nti.khai.edu/ojs/index.php/aktt/article/view/1206 |
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