Investigation of the impact of tangenical shape of the axial compressor gas-dynamic stability stock and efficiency of stage

In this paper, a study is presented of the shape of the first stage of the axial compressor in the circumferential direction by varying the variables of the Bézier curve of the second order, which forms the midline of the shape. The design is related to the optimization of the profile of the blade of the fan together with the CFD analysis. The analysis of the results showed the expediency of applying the bulk to optimize the flowing of flow, increasing the efficiency and the margin of the gas-dynamic stability of the step.В данной работе представлено исследование формы навала лопаток первой ступени осевого компрессора в окружном направлении за счет варьирования переменных кривой Безье второго порядка, которая образует форму средней линии. Проектирование связано с оптимизацией профиля пера лопатки совместно с CFD анализом. Анализ результатов показал целесообразность применения навала для оптимизации течения потока, повышения эффективности и запаса газодинамической устойчивости ступени

Investigation of the influence of the displacement of the blade section in the axial direction on the gas dynamic stability reserve and the efficiently of the stage.

In this work optimization of a shape of a shovel of the first step of the axial compressor, by means of a sweep of a profile part is presented. Research of the flow in the stage were carried out in the program complex of computational gas dynamics. According to known geometric data, blade profiles and meridional contours are constructed. Recommendations of application of an axial pile for the first step are provided.В данной работе представлена оптимизация формы лопатки первой ступени осевого компрессора, при помощи осевого навала профильной части. Исследования течения в ступени осуществлялись в программном комплексе вычислительной газодинамики. По известным геометрическим данным построены профили лопаток, а также меридиональные обводы. Приведены рекомендации о применении осевого навала для первой ступени

Identification of corner separation modelling in axial compressor stage

The paper presents a study of corner separations in hub to blade region at various operation conditions towards compressor stall. It is known that for compressor flows with low or none separations computation fluid dynamics with RANS methods work quite well, however, for highly separated flows they are no longer entirely valid. Therefore, several criteria were applied for prediction and quantification of possible corner separation, and the main interest of this work is in predicting the separation just before it will actually happen by certain flow metrics, so these metrics can be further used as a 'pre-stall' criteria whilst the RANS CFD operating point still behave within its appropriate limits. Also the effect of shear lean is discussed in the presented context. © The Authors, published by EDP Sciences, 2020

The influence of lean blades of highly loaded axial compressor at its integral characteristics and the stock of gas-dynamic stability

В данной работе представлена модификация исходного осевого компрессора и новой 3D конструкции с использованием автоматизированного многокритериального оптимизационного процесса. Новые методологии проектирования, используемые для этого компрессора, основаны на автоматизированной оптимизации аэродинамического профиля в IOSО NM совместно с 3D-CFD анализом. Использован многоступенчатый CFD анализ для регулирования распределения нагрузки по ступеням и получения соответствующих свойств. CFD анализ успешно показал, что срывы в корневой части значительно снижены.This paper presents the modification of the current baseline axial flow compressor design and the development of a new 3D design using an automated multi-objective optimization process. The new design methodology used to this compressor design was based on an automated airfoil geometric optimization system in the IOSO NM combined with a 3D-CFD analysis. A multi-stage CFD analysis was used effectively in order to adjust a loading distribution along stages and to obtain a proper stage matching. CFD analysis showed that hub corner stall was successfully suppressed

Redesign of an axial compressor with mass flow reduction of 30%

In this paper redesign process of an axial compressor of a Gas Turbine for mechanical drive is discussed together with computational results and experimental data. The goal of the project was to reduce compressor mass flow by 30% and at the same time to increase compressor specific work by about 10%. This could not be achieved by conventional methods such as re-staggering of Inlet Guide Vanes. Throughflow and CFD calculations were performed for redesigned versions. As a result an updated compressor was produced for the real engine and achieved design objectives. This paper shows how the swept area distribution along the compressor affects stage loading distribution and surge limits. © 2019 WIT Press

Numerical Analysis of the Gas Dynamics of Axial Compressor on the Example of GTK-10-4

The purpose of this computational study was to study the physics of the process of flow and the formation of breakdown zones of a working fluid in an OC during CFD calculations. And also the analysis of the influence of boundary conditions, models of turbulence and the rotating root part in the directing apparatus (HA) on the flow structure and the coordination of the steps in the OK.Целью данного расчетного исследования являлось изучение физики процесса течения и образования срывных зон рабочего тела в ОК при CFD-расчете. А также анализ влияния граничных условий, моделей турбулентности и вращающейся корневой части в направляющем аппарате (НА) на структуру потока и согласование работы ступеней в ОК

Comparison of Experimental Data with the Results of Numerical Simulation of the Flow to the Stage of the Axial Compressor Received with Using k-e and SST Models of Turbulence

The numerical simulation of the flow in the Stage D compressor stage was verified as a result of an experimental study. For verification, the most widespread turbulence models, k-ε and SST, are used in engineering practice. Comparison of the data is performed both by integral characteristics and by the distribution of the total pressure, angles, axial velocity along the step height. As a result of the comparison, it is established that the integral flow parameters and πk have a high accuracy of coincidence with experiment. When comparing the height parameters, the greatest discrepancy is observed in the end regions.Проведена верификация численного моделирования течения в осевой компрессорной ступени Stage D по результатам экспериментального исследования. Для верификации использованы наиболее распространенные в инженерной практике модели турбулентности k-ε и SST. Сравнение данных выполнено как по интегральным характеристикам, так и по распределению полного давления, углов, осевой скорости по высоте ступени. В результате сравнения установлено, что интегральные параметры расхода и πк имеют высокую точность совпадения с экспериментом. При сравнении параметров по высоте наибольшее расхождение наблюдается в торцевых областях

Research of Influence of Border Conditions and Models of Turbulence on Structure of Flow and Harmonization Matching of Stages in AC GTK-10-4

The purpose of this computational study was to study the physics of the process of flow and the formation of breakdown zones of a working fluid in an AC during CFD calculations. And also the analysis of the influence of boundary conditions, models of turbulence and the rotating root part in the directing apparatus (HA) on the flow structure and the coordination of the steps in the AC.Целью данного расчетного исследования являлось изучение физики процесса течения и образования срывных зон рабочего тела в ОК при CFD-расчете. А также анализ влияния граничных условий, моделей турбулентности и вращающейся корневой части в направляющем аппарате (НА) на структуру потока и согласование работы ступеней в ОК