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Статті в журналах з теми "Thermogasdynamic compression"
1
Kobalava, H., and D. Konovalov. "Numerical simulation of the regime and geometric characteristics influence on the pressure loss of a low-flow aerothermopressor." Refrigeration Engineering and Technology 55, no. 2 (April 30, 2019): 66–76. http://dx.doi.org/10.15673/ret.v55i2.1355.
Повний текст джерелаАнотація:
In this paper, a study of gasdynamic processes that occur in a low-flow aerothermopressor has been done. The aerothermopressor is a two-phase jet apparatus for contact cooling, in which, due to the removal of heat from the air flow, the air pressure is increased (thermogasdynamic compression) and its cooling is taken place. Highly effective operation of the aerothermopressor is influenced by primarily the flow part design and the water injected method in the apparatus. Constructive factors that influence energy costs to overcome friction losses and local resistances on the convergent-divergent sections of the aerothermopressor are exerted a significant impact on the working processes in the apparatus. In this paper, a study of a number of typical low-flow aerothermopressor models has been conducted by using computer CFD modeling. Determination of the main parameters of the air flow (total pressure, dynamic pressure, velocity, temperature, etc.) has been carried out for a number of taper angles of a confuser a and a diffuser b, as well as for a number of values of the relative air velocity in the working chamber M = 0.4-0.8. Comparison of the obtained data with experimental data has been carried out. The deviation of the calculated values of local resistances coefficients in the confuser and in the diffuser from those obtained by computer CFD modeling does not exceed 7–10%. The recommended angles were determined: confuser convergent angle – 30° and diffuser divergent angle – 6°, corresponding to the minimum pressure loss is 1.0 – 9.5 %, and therefore also to the maximum pressure increase as a result of the thermogasdynamic compression that occurs during injection and evaporation of liquid in the working chamber. Thus, analytical dependences are obtained for determining the local resistance coefficients for the confuser (nozzle) and the diffuser, which can be recommended to use in the design methodology for low-flow aerothermopressors.
2
Коновалов, Дмитро Вікторович, та Галина Олександрівна Кобалава. "ПРОМІЖНЕ ОХОЛОДЖЕННЯ ЦИКЛОВОГО ПОВІТРЯ В ГАЗОТУРБІННИХ УСТАНОВКАХ АЕРОТЕРМОПРЕСОРАМИ". Aerospace technic and technology, № 1 (25 лютого 2018): 29–36. http://dx.doi.org/10.32620/aktt.2018.1.02.
Повний текст джерелаАнотація:
Existing technologies to improve the fuel and energy efficiency of gas turbine plants due to intercooling of the cycle air are analyzed. One of the promising ways for increasing the efficiency of such technologies is using thermogasdynamic compression in the heat recovery processes of secondary energy resources. A feature of this process is the pressure rate increase due to the instant evaporation of a finely dispersed liquid is injected into the air stream which accelerated to the speed of sound. When the pressure of the boiling liquid is increased, the power consumption for compressing the working fluid (cyclic air) is reduced, the efficiency is increased and the consumption of the fuel and energy resources of the gas turbine plant is reduced.The advantages of cooling technology with an aerothermopressor are outlined in the article. The aerothermopressor is a multifunctional jet apparatus, whose work consists in injecting water into the stream of cyclic air when it is compressed in the gas turbine plant compressor. If this apparatus is used for cooling of cycle air, it will be compensate for aerodynamic losses along the air path and it will reduce compression work in the compressor, increase the consumption of the working fluid and, as a result, increase the gas turbine plant power. The basic schemes of the aerothermopressor installation between the stages of low and high pressure compressors are considered. Theoretical thermodynamic cycles of such gas turbine plants are presented and the advantage of using a contact cooler for intercooling of the cyclic air in comparison with surface air coolers for intercooling is defined in this paper.The proposed cooling technology makes it possible using low-potential heat of secondary energy resources of gas turbine plants (heat of cyclic air), the utilization of which by traditional methods is problematic because the temperature of waste heat sources is low.The tasks are determined, the solution of which will ensure the possibility of rational organization of cooling processes in the aerothermopressor, which in turn will allow achieving optimal parameters for increasing the efficiency of the gas turbine plant and reducing the specific fuel consumption in relation to the variable climatic conditions of operation
3
Коновалов, Дмитро Вікторович, та Галина Олександрівна Кобалава. "ЧИСЕЛЬНЕ МОДЕЛЮВАННЯ ПРОТОЧНОЇ ЧАСТИНИ МАЛОВИТРАТНОГО АЕРОТЕРМОПРЕСОРА ДЛЯ ПРОМІЖНОГО ОХОЛОДЖЕННЯ ЦИКЛОВОГО ПОВІТРЯ ГАЗОТУРБІННОГО ДВИГУНА". Aerospace technic and technology, № 4 (31 серпня 2019): 31–38. http://dx.doi.org/10.32620/aktt.2019.4.06.
Повний текст джерелаАнотація:
A cyclic air intercooling application in the compression process in the compressor has a positive effect on the resource of the gas turbine plant (GTP) and on increasing its capacity without reducing the service life. The most promising method of cooling the cyclic air of the GTP, namely contact cooling by using an aerothermopressor, was analyzed in the paper. This heat exchanger is a two-phase jet apparatus in which, due to the removal of heat from the airflow, the air pressure is increased and its cooling occurs. The main problem in the development of the aerothermopressor is to determine the geometric characteristics of the apparatus flow part and the fluid injection system, which allow its effective application for increasing pressure and fluid spraying fine. An analysis was made of the apparatus models operation by using CFD simulation in the ANSYS Fluent software package to determine the aerothermopressor main characteristics of the cyclic air cooling system of the GTP. The calculation method was determined, the turbulence model was selected, the calculation was carried out taking into account the convergence of the results, and the output data were processed and visualized in the CFD-Post in the form of graphs and fields. Based on this, the aerothermopressor design was developed for a WR-21 gas turbine produced by Rolls Royce. At the first stage of the study, a “dry” aerothermopressor was modeled (without water injection into the evaporation chamber). It was found that the decrease in airflow pressure due to friction losses was about 5%. At the second stage of the study, a simulation of the aerothermopressor with water injection into the flow part (at the inlet to the evaporation chamber) was carried out. As a result of thermogasdynamic compression, the increase in the total air pressure at the outlet of the aerothermopressor was 3.1%, and the temperature of the cooled air was decreased by 280 degrees. To ensure effective air compression in the gas turbine compressor, incomplete evaporation of water in the aerothermopressor was considered. It made it possible to obtain finer water spraying at the diffuser outlet, while the average diameter of the water droplet decreased to 2.5 μm.
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Коновалов, Дмитро Вікторович. "АНАЛІЗ ЕФЕКТИВНОСТІ ТЕПЛОВИКОРИСТОВУЮЧОЇ ТЕРМОПРЕСОРНО-ЕЖЕКТОРНОЇ ХОЛОДИЛЬНОЇ МАШИНИ". Aerospace technic and technology, № 8 (31 серпня 2019): 59–67. http://dx.doi.org/10.32620/aktt.2019.8.09.
Повний текст джерелаАнотація:
One of the ways to increase the energy efficiency of ejector refrigerating machines is to use of thermopressor technologies, which are based on to use of the process of thermogasdynamic compression. This process consists in contact cooling and at the same time increasing the gas or steam pressure. The thermopressor application in the ejector refrigerating machines cycle installed at the outlet of the ejector, allows, by increasing the pressure during vapour contact cooling to a saturation tempera-ture, to increase the ejection coefficient U and, accordingly, the thermal coefficient z. A number of refrigerants were chosen for analysis of cycle of ejector refrigerating machines, among which those traditionally is used for ejector refrigerating ma-chines, and a number of other refrigerants that can be used in ejector refrigerating machines based on the possibility of using the thermopressor. It is possible to in-crease the ejector refrigerating machines efficiency by using the thermopressor while ensuring a greater temperature difference. With the temperature difference 60–100 oC, the relative pressure increase is mostly positive. The following refrigerants have the most significance: R717, R134a, R227ea, R1234ze(E), R1234yf. Analysis of the ejector refrigerating machines scheme by using the thermopressor shows that the greatest efficiency at the highest possible boiling points in the generator tg is the refrigerants: R142b, R600, R1233zd(Е), R245fa.
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Коновалов, Дмитро Вікторович, Роман Миколайович Радченко, Сергій Георгійович Фордуй, Віктор Павлович Халдобін, Олексій Олегович Зєліков та Олександр Анатолійович Різун. "ВДОСКОНАЛЕННЯ ТЕПЛОВИКОРИСТОВУЮЧИХ ЕЖЕКТОРНИХ ХОЛОДИЛЬНИХ МАШИН ЗАСТОСУВАННЯМ АЕРОТЕРМОПРЕСОРНИХ ТЕХНОЛОГІЙ". Aerospace technic and technology, № 1 (26 лютого 2021): 60–66. http://dx.doi.org/10.32620/aktt.2021.1.06.
Повний текст джерелаАнотація:
The paper shows and analyzes circuit solutions for improving the existing schemes of ejector heat-using refrigeration machines, which are used as part of cogeneration plants. One of the promising areas is the use of an aerothermopressor, which implements the effect of thermogasdynamic compression, which is to increase the pressure while reducing the temperature in the evaporation of liquid, which injected into the flow of vapor moving at speed near the sound. To analyze the efficiency of ejector refrigeration machines, the developed calculation model was used, which takes into account the use of an aerothermopressor in the cycles of refrigeration machines with the features of the calculations of cycles and circuits. To select and determine possible circuit solutions, the efficiency of an aerothermopressor for different refrigerants was evaluated and a comparative analysis of the characteristic parameters of the efficiency of an aerothermopressor in the range of cooling temperature differences is 20–100 oC was made. It is possible to increase the efficiency of ejector heat-using refrigeration machines when using an aerothermopressor by providing a temperature difference of 60–100 oC. The analysis showed that the most important are: R717, R134a, R227ea, R1234ze (E), R1234yf (2–4%). It is possible to provide a higher thermal coefficient for ejector heat-using refrigeration machines by using an aerothermopressor in the circuit using the circulation of liquid refrigerant. The corresponding increase in the thermal coefficient is 1.5–2.0%. The use of an aerothermopressor in the scheme with heat recovery allows removing additional overheating of vapor before suctioning into the ejector with a corresponding increase in the thermal coefficient by 4-8%. The analysis shows that the total increase in the thermal coefficient due to the combined use of an aerothermopressor, heat recovery, and recirculation is 10–15% at a base value of 0.30–0.40.
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Кобалава, Галина Олександрівна. "ВИЗНАЧЕННЯ КОНСТРУКТИВНИХ ПАРАМЕТРІВ ПРОТОЧНОЇ ЧАСТИНИ АЕРОТЕРМОПРЕСОРА СИСТЕМИ ОХОЛОДЖЕННЯ ЦИКЛОВОГО ПОВІТРЯ МІКРОТУРБІН". Aerospace technic and technology, № 2 (22 квітня 2019): 44–50. http://dx.doi.org/10.32620/aktt.2019.2.05.
Повний текст джерелаАнотація:
Among modern jet technologies, one of the promising research areas is a study of gas-dynamic processes in the aerothermopressor. This jet apparatus is a device for contact cooling (the heat from the air flow is consumed for the instantaneous evaporation of water droplets), in which there is a thermogasdynamic compression effect, and that is, the air pressure increase is taken place. A significant influence on the working processes in the aerothermopressor is exercised by design factors. The influence of these factors on energy costs to overcome the friction losses and local resistances on the convergent-divergent sections of the apparatus was investigated. Relevant in the aerothermopressors development is to determinate of rational parameters of the workflow organization with the corresponding development of the flow part design. At the same time, it is necessary to have an opportunity for analytical determination of pressure losses in the confuser and diffuser of the aerothermopressor. A research of typical models of the aerothermopressor for a number of taper angles of a confuser a (convergent angle a = 30; 35; 40; 45; 50 °) and diffuser b (divergent angle b = 6; 8; 10; 12 °), for a number of air velocity values in the working chamber M = 0.4-0.8 has been carried out. The obtained calculated data (results of computer CFD-simulation) and experimental data have been compared. The error of the values for the coefficients of local resistances in the confuser and diffuser does not exceed 7-10%. It was established that the value of the local resistance coefficient depends only on the geometrical parameters (the angle of tapering and the diameters ratio of the input and output D1/D2), that is, the air flow character in the aerothermopressor corresponds to the self-similar mode. The recommended angles were determined: confuser convergent angle a = 30 ° and diffuser divergent angle b = 6 °, corresponding to the minimum pressure loss DPloss = 1.0–9.5 %. The empirical equations were defined for determining the local resistance coefficients of the confuser and diffuser, which can be recommended for use in the design of low-flow aerothermopressor for microturbines
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Boyko, Ludmila, Vadym Datsenko, Aleksandr Dyomin, and Nataliya Pizhankova. "Devising a method for calculating the turboshaft gas turbine engine performance involving a blade-by-blade description of the multi-stage compressor in a two-dimensional setting." Eastern-European Journal of Enterprise Technologies 4, no. 8(112) (August 31, 2021): 59–66. http://dx.doi.org/10.15587/1729-4061.2021.238538.
Повний текст джерелаАнотація:
The design and adjustment of modern gas turbine engines significantly rely on the use of numerical research methods. This paper reports a method devised for calculating the thermogasdynamic parameters and characteristics of a turboshaft gas turbine engine. The special feature of a given method is a two-dimensional blade-by-blade description of the compressor in the engine system. Underlying the calculation method is a nonlinear mathematical model that makes it possible to describe the established processes occurring in individual nodes and in the engine in general. To build a mathematical model, a modular principle was chosen, involving the construction of a system of interrelated and coordinated models of nodes and their elements. The approach used in modeling a two-dimensional flow in the compressor makes it possible to estimate by calculation a significant number of parameters that characterize its operation. With the help of the reported method, it is possible to estimate the effect of changing the geometric parameters of the compressor height on the characteristics of the engine. To take into consideration the influence of variable modes of air intake or overflow in various cross-sections along the compressor tract, to determine the effect of the input radial unevenness on the parameters of the compressor and engine in general. To verify the method described, the calculation of thermogasdynamic parameters and throttle characteristics of a single-stage turboshaft gas turbine engine with a 12-stage axial compressor was performed. Comparison of the calculation results with experimental data showed satisfactory convergence. Thus, the standard deviation of the calculation results from the experimental data is 0.45 % for the compressor characteristics, 0.4 % for power, and 0.15 % for specific fuel consumption. Development and improvement of methods for calculating the parameters and characteristics of gas turbine engines make it possible to improve the quality of design and competitiveness of locally-made aircraft engines.
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Blinov, V. L., and G. A. Deryabin. "Technical Condition Estimation of the Gas Turbine Axial Compressor." IOP Conference Series: Earth and Environmental Science 990, no. 1 (February 1, 2022): 012037. http://dx.doi.org/10.1088/1755-1315/990/1/012037.
Повний текст джерелаАнотація:
Abstract The paper describes an approach for determining the technical state of an axial compressor as part of a gas turbine unit, based on thermogasdynamic parameters that are measured at the operating facility. As a criterion for the technical condition, it is proposed to use the ratio of the actual efficiency of an axial compressor to the reference efficiency in such modes. To do this, it is enough to know the temperatures and pressures of the air at the inlet and outlet of the axial compressor. A method for selecting such modes is described and some features of filtering the operating parameters of a gas turbine plant are noted. In the proposed approach, the choice of modes for analyzing the technical state of an axial compressor is carried out according to the value of the effective power of the gas turbine unit. Some results of determining the criterion of the technical condition of an axial compressor for a gas turbine unit, which drives a centrifugal compressor of natural gas, are presented. Based on the analysis of the degradation of the technical condition criterion, it is possible to determine its predicted value. The results of the work can be used to create automated systems for assessing and predicting the technical condition of drive gas turbine units at their facilities. The application of the obtained results of the work expands the possibilities of servicing gas turbine plants according to the actual state. The proposed approach can be adapted and applied for gas turbine plants for various purposes, as well as for their individual units.
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Shabarov, Alexander B., Alexander M. Moiseev, Mikhail S. Belov, and Andrey A. Achimov. "INFORMATION SYSTEM OF THE TEST BENCH FOR DRIVING GAS TURBINE ENGINES." Tyumen State University Herald. Physical and Mathematical Modeling. Oil, Gas, Energy 6, no. 4 (2020): 28–47. http://dx.doi.org/10.21684/2411-7978-2020-6-4-28-47.
Повний текст джерелаАнотація:
This article studies the problem of determining the technical condition of drive and energetic gas turbine engines (GTE) during acceptance tests that have been repaired at a specialized enterprise. The following descriptions are given: of the bench for testing drive and energetic gas turbine engines; of the bench systems for monitoring and measurement, methods for conducting acceptance tests; of the evaluation the quality of the repaired engine based on its thermogasdynamics parameters; of the processing of measurement results obtained during acceptance tests. The materials of the system of differential (subassembly) diagnostics of GTE are generalized. The authors have considered the features of diagnostics of transient modes of GTE. The authors suggest the transition from the engine node to its elements as one of the ways to further improve the differential diagnostics, which has required developing the technique and system of pressure and temperature measurement at inlet and outlet of stage axial compressor. An algorithm for differential (element-by-element) engine diagnostics is described using the example of an axial compressor stage.
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Бойко, Людмила Георгиевна, Олег Владимирович Кислов та Наталия Владимировна Пижанкова. "МЕТОД РАСЧЕТА ТЕРМОГАЗОДИНАМИЧЕСКИХ ПАРАМЕТРОВ ТУРБОВАЛЬНОГО ГТД НА ОСНОВЕ ПОВЕНЦОВОГО ОПИСАНИЯ ЛОПАТОЧНЫХ МАШИН. ЧАСТЬ 1. ОСНОВНЫЕ УРАВНЕНИЯ". Aerospace technic and technology, № 1 (25 лютого 2018): 48–58. http://dx.doi.org/10.32620/aktt.2018.1.05.
Повний текст джерелаАнотація:
Gas turbine engines processes mathematic simulations are widely used in different steps of its living cycle. All engine simulations may be divided into different difficulty levels: higher simulation level allows doing a more precise description of physical processes in main units of gas turbine engines and their elements. It gives the opportunity for getting better arrangement of calculation results and experimental data, reduce the quality of factors, which are traditionally used in determine engine operational characteristics with 1-level models.The purpose of the article is to describe the thermogasdynamic parameters and maintenance perfomances calculation method, which based on second level mathematic simulation. Its main feature is blade-to-blade turbomachines description (multistage compressor and multistage cooling gas turbine), which allows to take into account blade and flow path geometrical parameters. Their changing during the gas turbine engine design and development processes influence its performances: thrust, fuel consumption, efficiency as functions of values of flow rate, rotational speed, engine entrance conditions and so on. All these dependences could be defined by using proposed calculation method.In distinction from methods which are noted, this method allows to concede compressor or turbine incidence angles, drag values, pressure ratio, surge margin in design and off-design engine regimes. The opportunity to take into account by-passing and air bleeding from compressor blade channels and their engine parameters influence is very important also.The article includes calculation method main points, block-scheme, equations system, which gives the opportunity of alignment the engine units and their elements in wide range of state working regimes. Set of equations consists of flow rate balance equations through the stages of multistage compressor and turbine, combustion chamber and connected channels. Also system includes power balance equations, by-passing, air bleeding from compressor stages channels, its admission into the cooling turbine stages and accounts their thermodynamic parameters. Compressors and turbines maps parameters are calculated with main turbomachinery theory lows and semi-empirical dependences.This article is the first in series of articles, which considers this problem
Дисертації з теми "Thermogasdynamic compression"
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Сорін, В. Д. "Вихровий компресор для наддуву повітря в топку згорання на ТЕЦ". Master's thesis, Сумський державний університет, 2021. https://essuir.sumdu.edu.ua/handle/123456789/86615.
Повний текст джерелаАнотація:
У роботі виконано розрахунок одноступеневого вихрового компресора та визначено діаметр робочого колеса. З метою зменшення габаритних розмірів виконано розрахунок двоступеневого вихрового компресора з різними діаметрами робочих коліс першого та другого ступенів. Виконано аналіз отриманих результатів та вибрано оптимальну конструкцію для пропонованих вихідних даних. У розділі охорони праці виконано аналіз шкідливих та небезпечних факторів при експлуатації вихрових компресорів та виконано розрахунок шумоглушника.В работе выполнен расчет одноступенчатого вихревого компрессора и определен диаметр рабочего колеса. С целью уменьшения габаритных размеров выполнен расчет двухступенчатого вихревого компрессора с разными диаметрами рабочих колес первой и второй ступеней. Выполнен анализ полученных результатов и выбрана оптимальная конструкция для предлагаемых исходных данных. В разделе охраны труда выполнен анализ вредных и опасных факторов при эксплуатации вихревых компрессоров и расчет шумоглушителя.
In this work, the calculation of a single-stage vortex compressor is carried out and the diameter of the impeller is determined. In order to reduce the overall dimensions, a calculation was made for a two-stage vortex compressor with different diameters of the impellers of the first and second stages. The analysis of the obtained results is carried out and the optimal design for the proposed initial data is selected. In the labor protection section, the analysis of harmful and hazardous factors during the operation of vortex compressors and the calculation of the silencer are carried out.
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Konovalov, Dmytro, Eugeniy Trushliakov, Mykola Radchenko, Halina Kobalava, and Vitaliy Maksymov. "Research of the Aerothermopressor Cooling System of Charge Air of a Marine Internal Combustion Engine Under Variable Climatic Conditions of Operation." Thesis, 2020. https://doi.org/10.1007/978-3-030-40724-7_53.
Повний текст джерелаАнотація:
Research of the Aerothermopressor Cooling System of Charge Air of a Marine Internal Combustion Engine Under Variable Climatic Conditions of Operation / D. Konovalov, E. Trushliakov, M. Radchenko, H. Kobalava, V. Maksymov // Grabchenko’s Intern. Conf. on Advanced Manufacturing Processes. – Odessa, 2020. – P. 520–529.Abstract. Principle of charge air cooling of the internal combustion engine with an aerothermopressor is proposed. It is implemented on the transport ship regular line. Arising thermogasdynamic compression allows increasing the air pressure. The aerothermopressor application in the charge air cooling systems makes it possible to reduce the power consumed by compressors, Nc by 3–10 %, thereby the engine power is increased by 1–3 % and the specific fuel consumption is decreased by 2–4 %. It is established that in case of increasing the ambient air temperature tamb at the turbocharger input the effect from the aerothermopressor used for cooling of the charge air is increased: the turbocharger power reduction DNC is increased with a corresponding increase in engine power and a decrease in specific fuel consumption. The relative (related to air flow) water mass flow is determined, which has to be injected at completely evaporated in a thermal overpressure: 0.02–0.05 (2–5 %).
Тези доповідей конференцій з теми "Thermogasdynamic compression"
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Baturin, Oleg, Andrei Tkachenko, Ilia Krupenich, Grigorii Popov, and Eugene Goryachkin. "Identifying the Approach to Significantly Improve the Performance of NK-36ST Gas Turbine Power Plant." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-64836.
Повний текст джерелаАнотація:
Collaboration between the Samara National Research University [1] and the JSC “KUZNETSOV” [2] included the research efforts in the field of increasing the performance of NK-36ST [3] gas turbine power plant intended for use as a driving unit of a gas compression station. The requirements included 3% increase in engine efficiency while keeping the maximum number of engine parts unchanged. First, the thermogasdynamic simulator of the NK-36ST gas turbine power plant was developed and verified using the results of experimental investigations. The impact of various parameters of the engine upon its efficiency was thoroughly investigated and the approach to modernization preserving most of the engine parts was suggested. This approach included increasing the values of work process parameters, the hydraulic efficiency of turbomachinery and reducing the cooling air consumption. Second, the analysis of the working process of turbomachinery was carried out. The air-gas channel in a meridional section was kept unchanged for the first iteration, thus keeping the parts of the initial engine unchanged, except for the blades and vanes of turbomachinery. For this variant, the parameters of compressors (head ratio and flow ratio) changed to more favorable values, supposedly providing 1–2% higher efficiency. Unfortunately, for this variant and the given restrictions the points, corresponding to the parameters of turbines moved at the Smith diagram to the unfavorable areas, thus making the increase in turbine efficiency very unlikely. The analysis had shown that to provide more convenient values of turbine parameters the blades should be shortened, and this decrease in blade length provides the possibility to increase the rotational speed of the rotor with the same strain levels of the blades and disks. As the result, the gas channel configuration and values of rotational speeds for the turbines providing the increase in their efficiency by 0.5%–1.0% were suggested. The suggested gas channel configuration preserves the same inner diameters thus keeping the disks layout the same. At the next stage, the shapes of the low-pressure turbine and compressor blades and the blades of free turbine were optimized using the Profiler program (developed at the Samara University), the NUMECA [4] system and the IOSO [5] optimization package, providing the 0.5%–1.0% increase in the efficiency in comparison to the initial variant. The results of the described research efforts provide the increase in engine efficiency of about 3% while providing the possibility to keep most of the rotor parts of the engine unchanged.
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Vinogradov, Alexandr S., and Renat R. Badykov. "Influence of Labyrinth Seal Leakage on the Turbine Support Cooling." In ASME 2014 Gas Turbine India Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gtindia2014-8172.
Повний текст джерелаАнотація:
This paper presents a study of the seal of supporting element in aviation engines with consideration of the mutual influence of its leakage on parameters of internal air system and engine oil system. A method of seal leakage calculation was developed. It connects engine thermogasdynamics calculation, airflow hydraulics calculation and structural analysis of deformed parts. The main sources of heat transferred to the supporting element were determined; their numerical values and percentages for the compressor and turbine were also determined. This paper provides options of cooling the turbine support for realization of this method. A way of cooling the support determines the quantity of heat supplied to the support. Thus, this article analyzes the sources of heat. Comparison the amount of heat from different sources also is carried out. The amount of heat is defined the temperature of the cooling air. The article provides a comparison of calculation results for different temperatures of the cooling air. After selecting the geometry of the seal system, and determining of the total amount of heat, single seal from the system was researched. The main purpose of the paper is to explain the design of a single seal as part of whole seal system, which is used to cool the support of the aircraft engine.