NAU Harvester System
PROFILE RESISTANCE OF A GAS-TURBINE ENGINE NACELLE WITH A TURBOFAN ATTACHMENT
Наукові журнали Національного Авіаційного Університету
View Archive Info| Field | Value | |
| Title |
PROFILE RESISTANCE OF A GAS-TURBINE ENGINE NACELLE WITH A TURBOFAN ATTACHMENT
ПРОФІЛЬНИЙ ОПІР МОТОГОНДОЛИ ГАЗОТУРБІННОГО ДВИГУ-НА З ТУРБОВЕНТИЛЯТОРНОЮ ПРИСТАВКОЮ |
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| Creator |
Терещенко, Юрій Юрійович
Терещенко, Юрій Матвійович Дорошенко, Катерина Вікторівна Усенко, В’ячеслав Юрійович |
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| Subject |
boundary layer; profile resistance; nacelle; turbofan attachment; numerical experiment
— пограничний шар; профільний опір; мотогондола; турбовентиляторна приставка; чисельний експеримент — |
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| Description |
Aerodynamic coordination of the aircraft and the gas turbine engine is one of the most important problems that arise when designing subsonic passenger aircraft. Providing competitive engines requires the development of new engine design schemes. One of these promising schemes is a gas turbine engine with a rear-mounted turbofan attachment. Theoretical calculations show that it has high efficiency and efficiency compared with modern bypass engines of varying of bypass. However, the question of studying the profile resistance of the engine nacelle of a gas turbine engine with a rear-mounted turbofan attachment has not yet been studied. When a real gas is wrapped around the engine nacelle, flow always sticks to the walls. The presence of the resistance of the engine nacelle causes energy losses in the boundary layer, which causes a decrease in the air flow rate at the inlet to the gas turbine engine with a turbofan attachment. This fact affects the reduction of reactive thrust in the fan circuit. The numerical experiment makes it possible to study the resistance of the engine nacelle of a gas turbine engine with a turbofan attachment under various external conditions and flight speeds. To calculate the flow, the averaged Navier – Stokes equations are used, which are closed by the Menter SST turbulent viscosity model. A series of calculations was made of the flow the engine nacelle with a rear-mounted turbofan attachment with Mach numbers M = 0.3 ... 0.8. The paper assesses the effect of flow parameters on the outer surface of the engine nacelle on the formation of the boundary layer in front of the turbofan attachment of a gas turbine engine when viscous air flows the engine nacelle. The results showed that there is a need to take into account the thickness of the displacement when calculating the air flow in the fan circuit of a gas turbine engine with a rear-mounted turbofan attachment.
Проведено оцінку впливу параметрів течії на зовнішній поверхні мотогондоли на формування пограничного шару перед турбовентиляторною приставкою газотурбінного двигуна при обтіканні мотогондоли в’язким потоком. |
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| Publisher |
National Aviation University
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| Contributor |
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| Date |
2018-12-31
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| Type |
—
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| Format |
application/pdf
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| Identifier |
http://jrnl.nau.edu.ua/index.php/PTZ/article/view/13329
10.18372/0370-2197.4(81).13329 |
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| Source |
Проблеми тертя та зношування; № 4(81) (2018); 64-71
Problems of Friction and Wear; № 4(81) (2018); 64-71 Проблемы трения и изнашивания; № 4(81) (2018); 64-71 |
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| Language |
uk
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