In this paper, a parametric study of Compressor Performances is performed by the streamline curvature method. Effects of three input parameters in the design process, e. g., number of blades, distribution of blade thickness, and blade sweep angels, on the main objective parameters in the aerodynamic design, e. g., velocity distribution, efficiency, and pressure ratio, are investigated in the parametric study. Initially, a certain two-stage axial Compressor is designed by the streamline curvature method. Validation of the results is confirmed by comparing the obtained results with the experimental ones. Regarding various values for the aforementioned input parameters, the first stage of the axial Compressor is redesigned, and the output parameter is established. Therefore, the sensitivity of the design results to each of the aforementioned parameters is recognized. Results show that increasing the blades sweep angle causes the flow behavior, such as efficiency and pressure ratio in the axial fan, to improve while reducing it provides a completely contrary result. Also, reducing the rotors blades number leads to an increase in the pressure ratio and efficiency while its increase causes a contrary result. It is concluded that a reduction in the number of the blades has a stronger effect on the Performance parameters than when it increases. The results also show that the effect of the thickness in the hub is greater than the thickness of the tip, and its increase leads to reduce both efficiency and pressure ratio.

Centrifugal Compressors play an essential role in oil, gas and petrochemical industries. Their extensive usage is due to their smooth operation and high reliability compared to other other Compressor types. One of the main characteristics of these turbomachines is their Performance curve, which is an important criterion for selecting the appropriate Compressor for a desired working condition. In the presented article, the effect of impeller’ s geometry on Performance curve and other Compressors characteristics is numerically investigated. The 3D CFD code is used to achieve the Performance curves that are dedicated to each geometrical configuration. The results indicate that some of the selected geometrical parameters have a significant effect on Performance curve margins. Increasing the shroud angle moves the surge point to the higher flow coefficients, while the pressure ratio remains constant and increasing the blade’ s trailing edge angle, leads to increase in pressure ratio.

Design models of multi-stage, axial flow Compressor are developed for gas turbine engines. Axial flow Compressor is one of the most important parts of gas turbine units.Therefore, its design and Performance prediction are very important. One-dimensional modeling is a simple, fast and accurate method for Performance prediction of any type of Compressors with different geometries. In this approach, inlet flow conditions and Compressor geometry are identified and by considering various Compressor losses, velocity triangles at rotor, and stator inlets and outlets are determined, and then Compressor Performance characteristics are predicted.Numerous models have been developed theoretically and experimentally for estimating various types of Compressor losses. In the present work, Performance characteristics of the axial-flow Compressor are predicted based on one-dimensional modeling approach. Firstly, the proposed algorithm for modeling and then the losses model for calculation of pressure loss coefficient in the blades cascade have been represented. In this study, models of Lieblein, Koch-Smith, Aungier, Hawell are implemented to consider the Compressor losses. Finally, the model results are compared with experimental data to validate the model.

Increasing the pressure in gas turbine cycle is done by Compressor which is one of the most important components of the Gas Turbines. Due to positive pressure gradient, the nature of the flow inside the Compressor is complicated and for this reason and because of the duty of the blade for transferring energy to the flow, precise design of the Compressor’s blades from the aerodynamic view of point is very important In this study, effects of changes the rotor blade stagger angle on a transonic axial Compressor Performance curves including efficiency and pressure ratio has been studied. To simulate the complicated three-dimensional flow field in axial Compressors, a numerical code is used to solve Reynolds Average Navier-Stokes (RANS) equations. comparison between numerical results and experimental data shows a good agreement. When numerical code are verified. Then the rotor blade twist changes on axial Compressor Performance have been studied. The results show that the rotor blades twist leads to decrease in Compressor efficiency and pressure ratio.

Flow capacity of a gas transmission pipeline is usually affected by different parameters. In this study several determining factor are selected for sensitivity analysis of flow capacity prediction in IGAT-IV. These parameters include; pipeline parameters, gas parameters, system parameters, heat transfer parameters, compression parameters and Compressor fuel consumption parameters.Detail calculation has been performed by developing a computer program by Microsoft Visual Basic.Moreover, a computer program for generating the Compressor Performance curve has been written by MATLAB. This curve has been used to design and optimize the Compressor stations. From the present investigation, it has concluded that AGA Fully Turbulent, Colebrook-White and Weymouth equations have the best prediction of flow rate in gas transmission pipelines.87.85 % flow changes due to 1% isentropic exponent change, which has a very large effect on the flow capacity.10% to 30% flow changes due to 1% suction compressibility factor and discharge compressibility factor change. They have large effect on the flow capacity.1% to 10% flow changes due to 1% Compressor horsepower, Compressor suction and discharge temperature and adiabatic efficiency change. They have medium effect on the flow capacity. The other parameters have not significant effect on the flow capacity.

Triple shaft gas turbines are the most gas Compressor driven in natural gas Compressor station in national Iranian Gas Company. In the recent study, exergy equilibrium formula of each components of gas Compressor station specified and several mathematical models made. The model predict different parameters based on environmental and operational conditions. Models made by multivariate linear regression and ANOVA technique that made high precision models. The models results show that how varying the environment and operational condition such Compressor inlet temperature, turbine inlet temperature and turbine pressure ratio affect exergy efficiency, fuel consumption, exergy destruction and specific fuel consumption. In this study effects of environmental and operational variables on this parameters and interaction of this variable on each other surveyed. Results showed that variation in each variables has no effect in slope of net output power variation due to change in other variables, whereas Compressor inlet temperature and pressure ratio in exergy efficiency model, turbine inlet temperature and pressure ratio in fuel consumption model and turbine and Compressor inlet temperature in specific fuel consumption model have interaction on their model's response

One of the factors that can cause a reduction in the efficiency and Performance of axial Compressors is the tip leakage flow of the Compressor blade. In the first, the Compressor's Performance curve is compared with experimental results obtained under the condition of no air injection, and a statistically significant agreement is observed. The present study investigates the impact of various parameters, including flow rate, diameter, angle, and injection location, on the Compressor's Performance curve and flow structure, taking into account the injection of air into a passage. The results indicate that the Compressor's stall margin and stable range extension are at their maximum values at a specific scale of each of the aforementioned parameters. Any deviation from this scale, either by reducing or increasing the injection parameters, leads to a reduction in the above characteristics. Although the presence of injection leads to an increase in the total pressure ratio in all injection states compared to the state without injection, the adiabatic efficiency at similar mass flow rates exhibits no significant change. The results also indicate that flow injection in the most suitable state increases the stall margin amount by 27% and the stable range extension of the Compressor by 192.

In this research, the aerodynamic design of a centrifugal Compressor is carried out using an inverse design method. At the first step of the aerodynamic design, the shape modification capability of Compressor meridional plane is generated by linking up the Ball-Spine inverse design algorithm as a shape modification algorithm and quasi 3D analysis code as a flow solver. Then, the meridional plane is modified by improving the hub and shroud pressure distribution and applying it to the inverse design code. At the second part of this research, by developing a novel design method on the blade to blade plane, and incorporating it into the quasi 3D flow solver, the 3D profiles of impellers will be obtained in order to reach the higher blade loading. Finally, to check the outcome of design process, the current and the modified impellers are analyzed using the full 3D flow solver, CFX. The results are the representatives of about 5 percent enhancement in Compressor total pressure ratio.

In the present study, an experimental method is proposed to study the influence of different slot widths, ‎positions and structures of the Compressor recirculation systems on the Compressor Performance. ‎Obtained results indicate that the Compressor flow range increases with the width of the recirculation slot ‎at the expense of a narrower high-efficiency operating region. It is found that when the slot width is set to ‎‎3 mm, the surge and choke margins are about 12% higher than that of the 2 mm slot. Moreover, it is ‎found that when the position of the recirculation slot falls in the middle area of the guide wheel and far ‎from the splitter blades, a larger surge margin can be achieved then it near the splitter blade. Adopting the ‎recirculation structure without intake retaining ring structure can effectively broaden the Compressor flow ‎range. Compared with a straight slot intake structure, the Compressor with an inclined slot intake structure ‎has a greater surge margin in the high-speed region, however, the high-efficiency range of the latter ‎scheme is smaller. Furthermore, the efficiency circle moves towards higher mass flow conditions. The ‎present parametric study is expected to provide a guideline to design recirculation devices‎‎.