Estimation of the aerodynamic characteristics of a stepped nacelle for the aircraft powerplant

Tereshchenko, Yuriy; Sklyarov, Alexander; Дорошенко, Екатерина Викторовна; Humeniuk, Pavlo

doi:10.15587/1729-4061.2019.183403

Cited by 2 publications

(3 citation statements)

References 9 publications

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“…На сьогоднішній день, нажаль, досліджень характеристик двигунів з турбовентиляторною приставкою досить обмежена кількість [1][2][3][4][5]. Питання впливу мотогондоли на течію у вентиляторі турбовентиляторної приставки було досліджено в роботі [1] тільки аналітичним шляхом. В роботі [2] авторами  Р. В. Майборода, 2023 було проведено модельний експеримент, який виявив суттєвий вплив примежового шару на мотогондолі на течію у вентиляторі турбовентиляторної приставки, але головним недоліком цього експерименту є те що, він проводився на моделях, які в 10-20 разів менше, ніж реальний двигун.…”

Section: вступunclassified

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Аналіз Впливу Мотогондоли На Силу Тяги Вентиляторного Контуру Турбовентиляторної Приставки

Maiboroda

2023

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The subject of this study is the interaction between the engine nacelle of a three-circuit turbojet engine and a turbofan attachment. The object of this research is a model of a cylindrical engine nacelle and a fan part of the impeller of a turbofan attachment. The aim of this study was to evaluate the influence of the engine nacelle on the thrust force of the fan circuit of a three-circuit turbojet engine, taking into account the influence of the operation of the turbofan attachment. Tasks: to simulate the flow around the engine nacelle with a turbofan attachment and without a turbofan attachment; calculate the thrust force of the turbofan attachment. The studies were carried out using the method of numerical experiment. The system of Navier-Stokes equations was closed by the turbulent viscosity model SST Gamma Theta Transitional No. 4. The results of the study showed that the reactive thrust of the fan circuit of the turbofan attachment increases by 0.87-6.15% when operating at an altitude of 0 km, 9 km, 11 km and the range of Mach numbers at the input from 0.2 to 0.5. When flowing around the engine nacelle without taking into account the influence of the turbofan attachment, it is characteristic that the velocity field at the inlet is uniform, except for the zone with a boundary layer near the surface of the engine nacelle. However, during operation of the turbofan attachment, the flow pattern changes radically and the thickness of the boundary layer decreases, and the flow in front of the fan is uneven. A characteristic feature of the turbofan attachment, which is associated with the heating of the intermediate housing between the turbine and fan housings, has a positive effect on reducing the thickness of the boundary layer, wall heating contributes to an increase in the stagnant flow velocity due to viscous forces. The presence of a boundary layer on the engine nacelle does not adversely affect the flow in the fan circuit of the turbofan attachment, and the fan of the turbofan attachment does not adversely affect the engine gas generator. The scientific novelty and practical significance of this work lies in obtaining new data on the effect of the engine nacelle on the thrust force of the fan circuit of a three-circuit turbojet engine, taking into account the influence of the operation of the turbofan attachment. The results obtained can be used to optimize the turbofan attachment of a three-circuit turbojet engine.

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Section: вступunclassified

Аналіз Впливу Мотогондоли На Силу Тяги Вентиляторного Контуру Турбовентиляторної Приставки

Maiboroda

2023

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“…При проектуванні літака найважливішими завданнями є вибір типу двигуна, параметрів його робочого процесу, габаритів, які визначаються, як правило, за необхідною тягоозброєністю, а також схеми компонування СУ та її розташування на ЛА, які оцінюються насамперед перевагами, отриманими від їх взаємної інтеграції [1].…”

Section: вступunclassified

Закони Керування Авіаційним Газотурбінним Двигуном З Турбовентиляторною Приставкою

Tovkach

2023

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The main aspects of the general task of integrating an aviation engine (AE) with a turbofan additional unit (TAU) of a multi-mode aircraft are the selection of the scheme and design parameters of the AE with the TAU (including parameters of the work process), as well as methods and means of automatic control of the AE with the TAU for better matching its characteristics with certain flight modes. These two tasks are closely interrelated: on the one hand, when determining the appearance of the aircraft and its power plant (PP), it is necessary to consider what means will ensure the adaptation of its characteristics to the variable flight mode, and on the other hand, the purpose of the aircraft, its parameters and parameters of the PP, and the flight modes mostly determine the choice of control laws. The subject of the research is the formation of the laws of control of the aviation gas turbine engine with TAU. The goal is to improve the dynamic characteristics of the aviation gas turbine engine by applying adaptive control of the gas turbine engine with the use of wireless information exchange technologies. Objectives: to generalize the concept of adaptive control at the stage of determining the appearance of an engine with TAU; to determine the methods of regulating the GTE with TAU and their influence on the speed characteristics; to describe the process of formation of the laws governing AE with TAU; to investigate thermal processes in order to find functional dependencies in the optimal control of gas turbines with TAU. Research methods: system analysis, mathematical and computer modeling were used in the formation of control laws; the methods of philosophical knowledge were used to build an approach to the design of adaptive control systems of gas turbines with TAU. The theory of aircraft engines, the theory of differential equations, difference grids, and numerical methods were used to optimize the control of gas turbines with TAU. Results: methods of regulating the GTE with TAU and their influence on the speed characteristics of the aviation engine; formulas for researching the thermal processes of the working blades of the GTE with TAU in order to form the influence of the regulator on the executive mechanisms. Scientific and practical novelty: formation of a paradigm for the development of models of adaptive control of GTE with TAU, considering different flight modes of the aircraft and engine operation modes. The selection of control laws using multi-parameter optimization methods for finding the relationship between structural and component schemes of the gas generator and turbofan additional unit. The character of the engine thrust change depending on the input temperature is shown, which in turn, will allow to increase the efficiency of the fan and obtain a thrust reserve. The research directions of the temperature field and stress field were formed.

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Estimation of the aerodynamic characteristics of a stepped nacelle for the aircraft powerplant

Cited by 2 publications

References 9 publications

Аналіз Впливу Мотогондоли На Силу Тяги Вентиляторного Контуру Турбовентиляторної Приставки

Аналіз Впливу Мотогондоли На Силу Тяги Вентиляторного Контуру Турбовентиляторної Приставки

Закони Керування Авіаційним Газотурбінним Двигуном З Турбовентиляторною Приставкою

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