Influence of temperature drop on the pressure rise in the fan circuit of the gas turbine engine turbo-fan attachment
The subject of this study is the working process in a turbofan attachment of a gas turbine engine. The object of study is the fan part of the impeller of a turbofan attachment. The aim of this study was to evaluate the effect of temperature difference in a two-tier impeller on the degree of pressure...
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| Format: | Article |
| Language: | English |
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National Aerospace University «Kharkiv Aviation Institute»
2023-08-01
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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/2071 |
| _version_ | 1827861089781547008 |
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| author | Roman Maiboroda |
| author_facet | Roman Maiboroda |
| author_sort | Roman Maiboroda |
| collection | DOAJ |
| description | The subject of this study is the working process in a turbofan attachment of a gas turbine engine. The object of study is the fan part of the impeller of a turbofan attachment. The aim of this study was to evaluate the effect of temperature difference in a two-tier impeller on the degree of pressure increase in the fan part of a two-tier impeller of a turbofan attachment of a three-circuit engine. To achieve this goal, the following tasks were solved: to simulate the flow in a turbofan attachment; to calculate the dependence of the degree of pressure increase in the fan part of the impeller of the turbofan attachment on the Mach number for the operating mode at altitudes of 0 km, 9 km and 11 km; to evaluate the temperature difference in the two-tier impeller of the turbofan attachment. The study was carried out by the method of numerical experiment. Results: The dependence of the degree of pressure increase of the fan circuit of the turbofan attachment on the Mach number at the inlet is obtained, taking into account the effect of hot gases of the turbine circuit of the turbofan attachment. It is shown that the flow of hot gases affects the degree of pressure increase in the fan circuit. The presence of the turbine part of the two-tier impeller leads to a slight deterioration in the characteristics of the fan part. The degree of pressure increase is reduced by 0.2 ... 4.8 %. The greatest influence is manifested in the operating mode H = 11 km. Visualization of the flow velocity field in the fan part of the turbofan unit showed that during the operation of the turbine circuit, the nature of the leakage in the fan part changes by approximately 50% of the blade height. An increase in temperature contributes to the intensification of the energy of the boundary layer around the lower part of the blade of the fan circuit, which has a positive effect on the reduction of zero velocity zones during the flow. Scientific novelty and practical significance: new data were obtained on the effect of temperature difference in a two-tier impeller on the degree of pressure increase in the fan part of a two-tier impeller of a turbofan attachment of a three-circuit engine. The results obtained can be used to optimize the turbofan attachment of a gas turbine engine. |
| first_indexed | 2024-03-12T13:32:06Z |
| format | Article |
| id | doaj.art-1d55f2aac807469696726b94cf06d9d1 |
| institution | Directory Open Access Journal |
| issn | 1727-7337 2663-2217 |
| language | English |
| last_indexed | 2024-03-12T13:32:06Z |
| publishDate | 2023-08-01 |
| publisher | National Aerospace University «Kharkiv Aviation Institute» |
| record_format | Article |
| series | Авіаційно-космічна техніка та технологія |
| spelling | doaj.art-1d55f2aac807469696726b94cf06d9d12023-08-24T07:58:40ZengNational Aerospace University «Kharkiv Aviation Institute»Авіаційно-космічна техніка та технологія1727-73372663-22172023-08-0104sup2707510.32620/aktt.2023.4sup2.091963Influence of temperature drop on the pressure rise in the fan circuit of the gas turbine engine turbo-fan attachmentRoman Maiboroda0National Aviation University, KyivThe subject of this study is the working process in a turbofan attachment of a gas turbine engine. The object of study is the fan part of the impeller of a turbofan attachment. The aim of this study was to evaluate the effect of temperature difference in a two-tier impeller on the degree of pressure increase in the fan part of a two-tier impeller of a turbofan attachment of a three-circuit engine. To achieve this goal, the following tasks were solved: to simulate the flow in a turbofan attachment; to calculate the dependence of the degree of pressure increase in the fan part of the impeller of the turbofan attachment on the Mach number for the operating mode at altitudes of 0 km, 9 km and 11 km; to evaluate the temperature difference in the two-tier impeller of the turbofan attachment. The study was carried out by the method of numerical experiment. Results: The dependence of the degree of pressure increase of the fan circuit of the turbofan attachment on the Mach number at the inlet is obtained, taking into account the effect of hot gases of the turbine circuit of the turbofan attachment. It is shown that the flow of hot gases affects the degree of pressure increase in the fan circuit. The presence of the turbine part of the two-tier impeller leads to a slight deterioration in the characteristics of the fan part. The degree of pressure increase is reduced by 0.2 ... 4.8 %. The greatest influence is manifested in the operating mode H = 11 km. Visualization of the flow velocity field in the fan part of the turbofan unit showed that during the operation of the turbine circuit, the nature of the leakage in the fan part changes by approximately 50% of the blade height. An increase in temperature contributes to the intensification of the energy of the boundary layer around the lower part of the blade of the fan circuit, which has a positive effect on the reduction of zero velocity zones during the flow. Scientific novelty and practical significance: new data were obtained on the effect of temperature difference in a two-tier impeller on the degree of pressure increase in the fan part of a two-tier impeller of a turbofan attachment of a three-circuit engine. The results obtained can be used to optimize the turbofan attachment of a gas turbine engine.http://nti.khai.edu/ojs/index.php/aktt/article/view/2071триконтурний двигунтурбовентиляторна приставкаступінь підвищення тискумоделюваннятемпературний впливвентиляторний контурдвоярусне робоче колесочисельний експеримент |
| spellingShingle | Roman Maiboroda Influence of temperature drop on the pressure rise in the fan circuit of the gas turbine engine turbo-fan attachment Авіаційно-космічна техніка та технологія триконтурний двигун турбовентиляторна приставка ступінь підвищення тиску моделювання температурний вплив вентиляторний контур двоярусне робоче колесо чисельний експеримент |
| title | Influence of temperature drop on the pressure rise in the fan circuit of the gas turbine engine turbo-fan attachment |
| title_full | Influence of temperature drop on the pressure rise in the fan circuit of the gas turbine engine turbo-fan attachment |
| title_fullStr | Influence of temperature drop on the pressure rise in the fan circuit of the gas turbine engine turbo-fan attachment |
| title_full_unstemmed | Influence of temperature drop on the pressure rise in the fan circuit of the gas turbine engine turbo-fan attachment |
| title_short | Influence of temperature drop on the pressure rise in the fan circuit of the gas turbine engine turbo-fan attachment |
| title_sort | influence of temperature drop on the pressure rise in the fan circuit of the gas turbine engine turbo fan attachment |
| topic | триконтурний двигун турбовентиляторна приставка ступінь підвищення тиску моделювання температурний вплив вентиляторний контур двоярусне робоче колесо чисельний експеримент |
| url | http://nti.khai.edu/ojs/index.php/aktt/article/view/2071 |
| work_keys_str_mv | AT romanmaiboroda influenceoftemperaturedroponthepressureriseinthefancircuitofthegasturbineengineturbofanattachment |