Кафедра авіаційних двигунів (НОВА)
Permanent URI for this communityhttp://er.nau.edu.ua/handle/NAU/56735
News
Відповідальний за розділ: Якушенко Олександр Сергійович, доцент кафедри авіаційних двигунів. E-mail: oleksandr.yakushenko@npp.nau.edu.ua
Browse
Browsing Кафедра авіаційних двигунів (НОВА) by Title
Now showing 1 - 20 of 97
- Results Per Page
- Sort Options
Item A study of the energy balance of main gas pipeline operating modes on its efficiency(Національний авіаційний університет, 2022-10-07) Kapitanchuk, Kostiantyn; Andriyishyn, Mykhailo; Pikul, Marina; Otroshchenko, Volodymyr; Капітанчук, Костянтин Іванович; Андріїшин, Михайло Петрович; Пікуль, Марина Олександрівна; Отрощенко, Володимир ВіталійовичA study of the efficiency of the main gas pipeline «Soyuz» in different modes with the corresponding daily productivity and the effect of compressor stations shutdowns were conducted. The dependence of specific energy of fuel gas on the energy of transported natural gas at the exit from the main gas pipeline and its productivity was obtainedItem Aeroacoustic characteristics оf the axial compressor stage with tandem impeller(Naukovyi Visnyk Natsionalnoho Hirnychoho Universytetu, 2019) Dогоshепkо, Е.V.; Теrеshсhепkо, Yu. М.; Тегеshсhепkо, Yu.Yu.; Kushchinskiy, А. О.Рurpоsе. Comparative evaluation of aeroacoustic characteristics of the axial соmрrеssоr stages with а single and equivalent tandem impeller. Methodolory. The rеsеагсh was реrfоrmеd using the пumегiсаl ехреrimепt. The flow рагаmеtеrs in the stage of the axial соmрrеssоr wеrе calculated by solving the. non-stationary system of Navier - Stokes equations. The equations were closed bу the model of tuгbulеnt viscosity SST. The stage of the соmрrеssоr consisted of inlet guide vanes, the impeller and the guide vanes. The imреllег of the modified axial соmрrеssоr stage is designed as an equivalent tandem rоw. Acoustic sоurсеs of the axial соmрrеssог stage were calculated using the Ffowcs Williams - Hawkings equation. Findings. The гesults of а соmрагаtive eva]uation of the aeroacoustic characteristics of the axial соmрrеssог stages with а singlе and equivalent dоublе-гоw imреllеr аге оbtаinеd. The use of а tandem rоw instead of an equivalent single гоw in the impelle of the axial соmрrеssог slage makes it possible to increase the рrеssurе гаtiо bу 1-I5 % . In the design mode, the pressure ratio is inсгеsеd bу 8.5 %. А stage with а tandem impeller has grеаtеr acoustic efficiency than а соmрrеssоr stage with а single impeller. The obtained гesults dеmопstгаtе а significant decrease in the acoustic рrеssurе of the dipole sоurсе. In the design mode, the acoustic ргеssurе of the dipole sоurсе decreases bу mоrе than 70 %, the acoustic рrеssurе of the quadrupole sоurсе dесгеаsеs bу mоrе than 10 %. Originality. Fоr the first time the results of а comprehensive study of the aerodynamic and acoustic characteristics of the axial соmрrеssоr stage wеrе obtained. The results allow estimating the efficiency of application of tandem rоw in the impeller of the low loaded subsonic stage of the ахiаl соmрrеssоr. Practical value. The received recommendations can bе used while designing imреllеr machines with а low lечеl of acoustic emissionItem Automation control system of technical condition of gas turbine engine compressor(2019-08) Kulyk, M.S.; Kozlov, V.V.; Volianska, L.G.The article is devoted to one of the approaches to the construction of an automated system for solving the problems of diagnostics and monitoring of the flow duct of aircraft gas turbine engines and gas turbine plants. Timely detection of faults and subsequent monitoring of their development in operation are possible thanks to automated systems for assessing the technical condition of engines. This is particularly relevant in operating conditions as the knowledge of the technical condition of the engine is necessary for any engine maintenance system allows to choose the content and timing of maintenance, repair of the flow duct of gas turbine engines and gas turbine plants, as well as commissioning. The engineering technique, which can be applied at the performance of maintenance and stages of tests and debugging of aircraft engines, is considered. The automated system imple-ments a method of measuring the airflow through the compressor and a technique for assessing the technical condition of the compressor by the relative change in airflow. To determine the airflow rate through the gas turbine engine, it is sufficient to measure only static pressure values in the flow part. The static pressure receivers are not located in the flow part and do not obscure it, and thus do not affect the compressor gas-dynamic stability margin. The inspection area is selected for measuring in the flow duct of the air intake. Static pressure in the maximum and minimum cross-sections of the chosen area is measured; the maximum cross-section area of the flow duct, the total temperature of the airflow is measured outside the air intake. To determine the airflow rate, the functional dependence of the airflow rate on the static pressure is used. The algorithm for monitoring and diagnosing the operating condition of the engine is based on a comparison of the actual values of air flow rate with the airflow rate determined during the control tests or when using a mathematical model adapted for this gas turbine engine. The positive effect of the using of the proposed automated control system of the technical condition is that the airflow rate measured under operating conditions will significantly increase the objectivity of the control of the operation and technical condition of the gas turbine engine.Item Aналіз впливу зупинки лінійної компресорної станції на номінальну продуктивність магістрального газопроводу(Національний авіаційний університет, 2023-05-11) Андріїшин, Михайло Петрович; Капітанчук, Костянтин Іванович; Отрощенко, Володимир Віталійович; Пікуль, Марина Олександрівна; Andriyishyn, Мuhаilo; Kapitanchuk, Kostiantyn; Otroshchenko, Volodymyr; Pikul, MarinaПроведено розрахунки впливу зупинки лінійної компресорної станції на номінальну продуктивність магістрального газопроводу. Найбільший вплив на зміну продуктивності впливають зупинки компресорних станцій на початку газопроводу. Чим більш віддалена зупинка КС від початку газопроводу, тим менший її вплив на зміну продуктивності.Item CALCULATION OF SOUND POWER LEVEL OF TANDEM AXIAL FAN(Eastern-European Jornal of Enterprise Technologies, 2017) Doroshenko, E.; Tereshchenko, Yu.; Lastivka, I.; Tereshchenko, Yu.Представлено результати чисельного моделюван- ня течії в осьовому вентиляторі. Проведено тесто- вий розрахунок рівня звукової потужності вентиля- тора. Результати чисельного моделювання показали гарну збіжність. Визначено рівень звукової потуж- ності для перших двох гармонік геометрично екві- валентного дворядного вентилятора. Результати розрахунків показали, що застосування дворядного вентилятора дає можливість зменшити загальний рівень звукової потужності на 6.8…7.4 дБ / A numerical simulation of the flow in axial fans with single and tandem geometrically equivalent blade rows was carried out. During the research, the sound power level of the fans was calculated. The acoustic characteristics of the single fan obtained in the numerical experiment were compared with the results of the physical experiment. The divergence between the results of the physical and numerical experiments on the sound power level for the first harmonic is 0.08 %, for the second harmonic – 0.35 %. In order to reduce the acoustic emission, a 3D model of the axial fan with the geometrically equivalent tandem row was constructed. The results showed that at the fan rotation frequency of 900 rpm, the sound power level on the first two harmonics is reduced by more than 7 dB. Also, the change in the total sound power level for axial single and tandem fans in the rotation frequency range of 900 to 1,500 rpm was investigated. The fan with the geometrically equivalent tandem blade row has the total sound power level by 6.9...7.4 dB lower than the single fan. The use of the tandem axial fan allows improving acoustic characteristicsItem Database structure for aircraft fleet reliability management(Національний авіаційний університет, 2022-09-30) Yakushenko, O.; Popov, O.; Simakhina, N.Analysis of data necessary for the operation of an aviation equipment reliability monitoring system at an airline level was carried out. The PostgreSQL system was used as the basis for the database. The structure of the database and the diagram of tables interaction in it was shownItem Design оf Aviation Machines. Aircraft and Rocket Engines(НАУ, 2018) Гвоздецький, Іван Іванович; Волянська, Лариса Георгіївна; Йовенко, Сергій Іванович; Акмалдінова, Олександра Миколаївна; Морозов, Лев Миколайович; Карпенко, Маргарита ВеніаміновнаThe manual includes theoretical base of aircraft and rocket engines working processes, brief information on different types of gas turbine engines structure and turboprop ТВ3-117-ВМА-СБМ engine construction and systems description. The book is intended for students of Specialties 134 “Aviation and Space Rocket Technology” and 272 “Aviation Transport”.Item DEVELOPMENT OF A METHOD FOR OPTIMIZING THE STRUCTURE OF STATIC NEURAL NETWORKS INTENDED FOR CATEGORIZING TECHNICAL STATE OF GAS- TURBINE ENGINES(Eastern-European Journal of Enterprise Technologies, 2020-12-18) Yakushenko, O.; Popov, O.; Mirzoyev, A.; Chumak, O.; Okhmakevych, V.A process of creating a static neural network intended for diagnosing bypass gas turbine aircraft engines by a method of cat- egorizing the technical state of the engine flow path was considered. Diagnostics depth was “to the structural assembly”. A variant of diagnosing single faults of the flow path was considered. The following tasks were set: ‒ select the best neuron activation functions in the network layers; ‒ determine the number of layers; ‒ determine the optimal number of neurons in layers; ‒ determine the optimal size of the training set. The problem was solved taking into account the influence of parameter measurement errors. The method of structure optimization implies training the network of the selected configuration using a training data set. The training was periodically interrupted to analyze the results of the network operation according to the criterion characterizing the quality of classification of the engine technical state. The assessment was performed with training and control sets. The network that pro- vides the best value of the classification quality parameter assessed by the test set was selected as the final network. The PS-90A turbojet engine was selected as the object of diag- nostics. Diagnostics was carried out on takeoff mode and during the initial climb. Primary optimization was carried out according to the data with no measurement errors. It was shown that a two-layer net- work with the use of neurons having a hyperbolic tangent function in both layers is sufficient to solve the problem. The size of the first network layer was finally optimized according to the data contain- ing measurement errors. A two-layer network with eight neurons in the first layer was obtained. The share of erroneous diagnoses measured 14.5 %.Item Development of data obtaining method for neuron networks learning to gas turbine engines, gas compress units diagnosing(Eastern-European Journal of Enterprise Technologies, 2018-12) Кулик, М. С.; Абдуллаєв, П. Ш.; Якушенко, О. С.; Попов, О. В.; Мірзоєв, А. Дж.; Чумак, О. І.; Охмакевич, В. М.The application of neural networks is one of promising ways to improve efficiency when diagnosing aviation gas turbine engines and gas pumping units. In order to start functioning of such network, it should be trained first using the pre-defined training sets. These data should fully characterize work of the object in a wide range of operating modes and at various technical states of the diagnosticated assemblies. In addition, it is necessary to have a similar data set to monitor quality of the neural network learning. To train the network to recognize faults of one type, a set of 20‒200 or more training examples is required. Obtaining such information in operation or in full-scale tests is a rather long or costly process. A method for acquisition of training and control data sets was proposed. The sets are intended to train static neural networks recognizing single and multiple faults of the elements of air-gas channels of gas turbine engines and gas pumping units. The method enables obtaining sets of working process parameters describing operation of objects at various technical states of an air-gas channel, effect of measurement errors and object functioning in a wide range of modes and external conditions. Composition of the pumped gas is additionally taken into account for gas pumping units. To obtain the required parameters, a mathematical model of the working process of the object of the second level of complexity was used. The sets characterize work of operable objects and objects with significant malfunctions in spools of compressors and turbines and in a combustion chamber and for the case of a gas pumping unit, in its supercharger. Two variants of formation of sets were considered: using the measured parameters of the working process; deviations of the measured parameters from their reference values and the parameters used as regime parameters in the mathematical model of the working process. For the second variant, check of expediency of including the regime parameters in the sets was made. It has been shown that regime parameters can be excluded from data sets in some cases.Item Diagnostics of gas pumping units: Method Guide to Calculation and Graphic Work(National Aviation University, 2024) Yakushenko, O.; Andriets, O.; Gvozdetskyi, I.; Якушенко, О.; Андрієць, О.; Гвоздецький, І.The method guide contains methodical recommendations for calculation and graphic work on the academic discipline “Diagnostics of gas pumping units”. Intended for higher education seekers of specialty 142 "Power Machinery", that study in English according to the Educational Professional Program “Gas Turbine Plants and Compressor stations”Item Gas turbine engines diagnosing using the methods of pattern recognition(Авиационно–космическая техника и технология. Харьков., 2017-09) Dmitriev, S.; Popov, O.; Yakushenko, O.; Potapov, V.; Pashchuk, O.The paper is dedicated to the relevant problem that pertains to gas turbine engines diagnosing. The issue con- sidered in the paper is how to diagnose gas turbine engines using the methods of pattern recognition: in par- ticular the method of “binary tree” and the “nearest neighbor” method. In computer science, a binary tree is a tree data structure in which each node has at most two children, which are referred to as the left child and the right child. A recursive definition using just set theory notions is that a (non-empty) binary tree is a triple (L, S, R), where L and R are binary trees or the empty set and S is a singleton set. Some authors allow the binary tree to be the empty set as well. I n computing, binary trees are seldom used solely for their struc- ture. Much more typical is to define a labeling function on the nodes, which associates some value to each node. Nearest neighbor search (NNS), as a form of proximity search, is the optimization problem of finding the point in a given set that is closest (or most similar) to a given point. Closeness is typically expressed in terms of a dissimilarity function: the less similar thItem Gas turbine plant of simple cycle with development of vibration monitoring systems(Національний авіаційний університет, 2020-06) Akwan, OmarAim: to develop an efficient and accurate vibration monitoring system and chose and mount vibration sensors for the designed GTP to ensure accurate reading of vibration values Gas turbine plants operation parameters are affected by the design of the GTP and the ambient conditions temperature and pressure, a thermodynamic calculation were done on the designed GTP to calculate the change in temperature and pressure through different sections of the designed GTP. Based on the thermodynamic calculations a gasdynamic calculation were done to determine the optimal diametrical sizes on each section of GTP, and to calculate the compression work distribution between LPC and HPC and to determine the number on stages for each of LPC, HPC, LPT, HPT and PT. A strength calculation were done on GTP elements to determine the tension stresses from the centrifugal forces and the bending stress from gaseous and centrifugal forces the first strength calculations were done on turbine rotor blade on four cross sections on root 25%, 50% and 75% of the blade length, the second strength calculations were done on the turbine disc. As any rotary machine faults in any of the GTP elements can happen but with a good system for monitoring the health of the GTP parts the faults can be either predicted or prevented before happening this system is Vibration Monitoring system this part is focused on better understanding of vibration Monitoring and the development of the system itself. Vibration sensors were chosen taking into account the vibration limits of the GTP elements and the purpose of the sensor with working limits of the sensor itself.Item Information support of aftersale support of aircraft gas turbine engines in real operation(2019-04-23) Popov, O. V.; Yakushenko, O. S.; Popov, D. V.; Kolomiiets, Z. I.The questions of information systems for assessing the technical condition of aircraft engines in the system of maintaining the flight worthiness of aircraft are considered. The main tasks of monitoring the technical condition of engines during their maintenance and the overall structure of control and diagnosis of engines during operation stage have been proposedItem Method of formulating input parameters of neural network for diagnosing gas-turbine engines(Aviation. Taylor&Francis, 2013-05) Kulyk, Mykola; Dmitriev, Sergiy; Yakushenko, Oleksandr; Popov, OleksandrA method of obtaining test and training data sets has been developed. 弻ese sets are intended for train- ing a static neural network to recognise individual and double defects in the air-gas path units of a gas-turbine engine. 弻ese data are obtained by using operational process parameters of the air-gas path of a bypass turbofan engine. 弻e method allows sets that can project some changes in the technical conditions of a gas-turbine engine to be received, taking into account errors that occur in the measurement of the gas-dynamic parameters of the air-gas path. 弻e op- eration of the engine in a wide range of modes should also be taken into accountItem Methods of fuel efficiency increase for gas turbine plants at base of conversion aircraft engines(Національний авіаційний унівенситет, 2020-03-01) Фахар, МохаммадObject of research — Gas turbine plant with increased thermal efficiency based on converted aero engine. Subject of investigation — methods to increase the thermal efficiency of mobile gas turbine plant. Aim of diploma work — is to study the possibility of increasing the fuel efficiency of a converted aviation gas turbine engine when it is used as a drive for mobile electrical power plants.Item Modeling of hydrates forming process during natural gas drying when using 3S Separator at fueling stations systems(National Aviation University, 2020-09-22) Капітанчук, Костянтин Іванович; Андріїшин, Михайло Петрович; Андріїшин, Назар Михайлович; Kapitanchuk, Kostiantyn; Капитанчук, Константин ИвановичProposal of installation to dry natural gas with combined low-temperature separator with double fitting 3S separator and pressure stabilizer. The installations have to provide conditions for full natural gas drying from moisture by crystallizing hydrates in separation chamber. The issues concerning the first stage of modeling of 3S natural gas drying separator at natural gas transportation and sale facilities are considered, namely by creating of separator model with software in Python 2.7 language and Matplotlib and NumPy libraries to determine the main characteristics of the separator. Provided geometry modeling method of separator nozzle and twister and grid model of separator chamber with gas predetermined parameters of natural gas flow. Combination of k– and k–w turbulence models was used to describe the flow of natural gas in separator. Mathematical model is constructed in such way that is gets advantages of both turbulence models. Border layer calculated via SST-model. Thermodynamic parameters of natural gas flow across separator chamber that are required for hydrates molecules forming are analyzedItem RESEARCH INTO AERO ACOUSTIC CHARACTERISTICS OF TWO-ROW IMPELLERS OF THE AXIAL COMPRESSOR(Eastern-European Journal of Enterprise Technologies ISSN 1729-3774, 2018) Doroshenko, Ekaterina; Tereshchenko, Yuriy; Lastivka, Ivan; Kudzinovs'ka, InnaПредставлено порівняльну оцінку напір них характеристик і рівня втрат повного тиску дозвукових робочих коліс осьового ком пресора з однорядними і еквівалентними дво рядними лопатковими вінцями. Отримано аероакустичні характеристики дозвукових дворядних робочих коліс. Рівень звукового тиску дозвукових дворядних робочих коліс нижче, ніж рівень звукового тиску одноряд них робочих коліс на 0,5…3,2 дБ при густо ті лопаткових вінців на середньому радіусі 1…2,5 Представлена сравнительная оценка на порных характеристик и уровня потерь полного давления дозвуковых рабочих колес осевого компрессора с однорядными и экви валентными двухрядными лопаточными венцами. Получены аэроакустичнеские ха рактеристики дозвуковых двухрядных рабо чих колес. Уровень звукового давления дозву ковых двухрядных рабочих колес ниже, чем уровень звукового давления однорядных рабо чих колес на 0,5…3,2 дБ при густоте лопа точных венцов на среднем радиусе 1…2,5 We have conducted numerical simulation of current in the axial impellers with a single-row and a two-row geometrically equivalent blade crowns with a density of blade crowns over average radius of 1...2.5. The pressure characteristics of impellers obtained at q(λ)=0.45…0.8 show that using the two-row impellers can improve the pressure of a stage over the entire range of operation. Under the flow-around modes that correspond to the maximum pressure, the degree of pressure rise increases by 10.5 %. The research results showed that the two-row impellers demonstrate the higher level of losses compared with the level of losses in the equivalent single-row impellers. We have obtained results of research into aero acoustic characteristics of subsonic two-row impellers of the axial compressor. The research results showed that the use of two-row blade crowns in the impeller makes it possible to reduce the level of acoustic pressure in the range of operation q(λ)=0.45…0.8 by 0.5 dB to 3.2 dB at a density of blade crowns over average radius of 1...2.5. The replacement of a single-row blade crown in the impeller of a stage of the axial compressor with the equivalent two-row blade crown could ensure the enhancement of aerodynamic loading on the stage and reduce acoustic emission of the compressor.Item Thermocyclic fatigue and destruction of high pressure turbine blades in their critical sections(Elsevier, 2022) Кulyk, Mykola; Koveshnikov, Mykola; Petruk, Yana; Petruk, Bohdan; Yakushenko, OleksandrIn the article the critical sections and points at the leading edges of the airfoils of high-pressure turbines were reasonably defined for experimental studies of thermocyclic durability. Experimental studies of thermocyclic durability were performed for the samples of heatproof alloys for the cyclic change parameters in extreme temperatures and thermomechanical stresses that exert at the starting and running down of aircraft gas turbine engines and ground gas turbine power plants. The influence of protective coatings on thermocyclic durability of alloys and parts is mentioned in the article. The article describes the methods of determination the thermal stress in the blades. It is emphasized that extreme thermal stresses of compression in the edges of nozzle vanes and stretch on the pressure side of the airfoil occur on the operating mode "starting", and the cracks are revealed mainly on the mode "shutdown". In the intermediate stages of the flight cycle the do not exceed of the yield strength of the blade material and do not significantly affect there lative thermocycle durability of heatproof alloys. The destruction of the blades of high-pressure turbines in their cross sections along the airfoil shroud platform, in the zone of maximum temperature sand in the root sections explained from the position of the three– and multi component approachItem Автомобільні газонаповнювальні компресорні станції. Частина 1. Історія, сучасність, перспективи розвитку(Державний університет інфраструктури та технологій, 2020-12-20) Кулик, Микола Сергійович; Орлов, Ігор Олегович; Капітанчук, Костянтин Іванович; Волянська, Лариса Георгієвна; Kapitanchuk, KostiantynПідручник «Автомобільні газонаповнювальні компресорні станції»: складається з двох частин, а саме: частина 1 «Історія, сучасність, перспективи розвитку» та частина 2 «Конструкція, експлуатація». Містить основні аспекти розв’язання проблеми використання стисненого природного газу як моторне паливо для автомобільного та внутрішнього згоряння двигунів. Розглянуто принципові технологічні схеми сучасних і перспективних автомобільних газонаповнювальних компресорних станцій (АГНКС) гаражного типу. Детально проаналізовано основні технологічні процеси, що відбуваються на АГНКС. Розглянуто конструкцію основного устаткування АГНКС. Призначений для фахівців нафтогазової галузі, студентів вищих навчальних закладів, що навчаються за спеціальністю «Енергетичне машинобудування», а також може бути корисним працівникам науково-дослідних, проектно-конструкторських та інших організацій, що займаються проектуванням і експлуатацією АГНКСItem Автомобільні газонаповнювальні компресорні станції. Частина 2. Конструкція, експлуатація(Державний університет інфраструктури та технологій, 2020-12-20) Кулик, Микола Сергійович; Орлов, Ігор Олегович; Капітанчук, Костянтин Іванович; Волянська, Лариса Георгієвна; Kapitanchuk, KostiantynПідручник «Автомобільні газонаповнювальні компресорні станції»: складається з двох частин, а саме: частина 1 «Історія, сучасність, перспективи розвитку» та частина 2 «Конструкція, експлуатація». Містить основні аспекти розв’язання проблеми використання стисненого природного газу як моторне паливо для автомобільного та внутрішнього згоряння двигунів. Розглянуто принципові технологічні схеми сучасних і перспективних втомобільних газонаповнювальних компресорних станцій (АГНКС) гаражного типу. Детально проаналізовано основні технологічні процеси, що відбуваються на АГНКС. Розглянуто конструкцію основного устаткування АГНКС. Призначений для фахівців нафтогазової галузі. студентів вищих навчальних закладів, що навчаються за спеціальністю «Енергетичне машинобудування», а також може бути корисним працівникам науково-дослідних, проектно-конструкторських та інших організацій, що займаються проектуванням і експлуатацією АГНКС.