Sharif Digital Repository

Axial compression systems are widely used in many aerodynamic applications. However, the operability of such systems is limited at low mass flow rates by fluid dynamic instabilities. These instabilities lead the compressor to rotating stall or surge. In some instances, a combination of rotating stall and surge, called modified surge, has also been observed. In this research Moore – Greitzer model that the principle of constant speed mode checks as a base case has been considered and the developed condition of this model in which the dynamic model of the shaft will also respect and shaft rotational speed as a basis for state shall consider, has been analyzed.
In this study the effect of... 

Axial compressors play an important role in industry and aerial and land-based engines. Hence their design and optimization is of great importance. Due to the high costs associated with design and manufacturing of axial compressors, developing a sophisticated, rapid, low-cost and reliable methods for machine performance prediction is imperative. In this study, an attempt was made at introducing such a method. In this method, isolated airfoils were built in two different scales based on medium radius cross section of stator and rotor blades of the axial compressor of Sharif University of Technology gas turbine laboratory. Using the existing wind tunnel set-up at the aforementioned laboratory,... 

Compressors are one of the most important components of gas turbines and turbomachinery processes. Thus some precise and quick tools are needed for design and analysis purposes. Despite of vast development of Computational Fluid Dynamics (CFD) tools, Through-Flow Streamline Curvature Methods (SCM) has retained their position. 2D and quasi-3D forms of SCM in combination with CFD results nowadays make more than 80% of turbomachinery design process of axial and radial compressors and turbines. In this thesis, the basics of developing a tool for axial-flow compressor analysis are introduced. As will be seen, this analysis tool can be used for design purposes too. The method that is chosen for... 

Axial compressor design is a very complex and expensive process. In general, for design and development of a new axial compressor, manufacturing companies usually intend to employ an existing and successful axial compressor as an starting point and modify and upgrade it. In this regard, dimensional scaling is a common method for derivative axial compressors. The goal of dimensional scaling is to get a different capacitywhile minimizing the development time and cost. In this thesis, theNASA eight stage transonic axial flow compressor is chosen as the base model for dimensional scaling to lower and upper size of its original dimension. The scaled compressor is analyzed with a quasi 2-D code.... 

Axial compressors are utilized to increase compressible flow pressure in an efficient manner where mass flow rate is high, such as aviation engines and power generation gas turbines. The flow is compressed within this machine through several stages. Each stage consists of a rotor blade row followed by a stator blade row. Energy transfer to the air is performed on the rotor by changing its velocity vector. Then, pressure is recovered from velocity by diffusion, meanwhile turning the flow direction through stator blades. These blades have been designed and optimized with various methods evolved with developing computational and manufacturing facilities. In this thesis the aerodynamic design of... 

Improving compressor performance and arriving at better conditions has always been considered by researchers and industrialists. However axial compressor design process is time consuming, very costly, and involves uncertainties and iterations such that sometimes the preset targets are not achieved. Therefore it is required to be able to perform preliminary design and specify the compressor geometry and blade specifications and predict the performance characteristics with a fast, cheap method with required accuracy suitable for this step before detailed design and manufacture. Also some design methods need a primary geometry that is generated by these methods.In this work, towards achieving... 

Overall performance improvement of gas turbine is available by modifying each component of cycle. The purpose of this research is to improve performance of a micro turbine with 200 KW power, by redesigning compressor set. Considerable increase in performance and stability occurs, by adding individual stage of axial compressor at the entry of centrifugal section. It should be noted that, this improvement occurs without a significant increase in size and without having to change the centrifugal compressor design.In this study, design of one stage axial compressor and three dimensional modeling is discussed after, modeling and preliminary design of centrifugal compressor. Then, after obtaining... 

With everyday increasing application of gas turbine in different industries, fast and accurate tools for design, analysis and performance estimation of gas turbines have found many proponent; Compressors, as one of the most important parts of gas turbines, are no exception to this ordinance. Although development of Computational Fluid Dynamics (CFD) method was a great aid to improve the accuracy of this tools, complexity and being time consume make them uncommon and unpopular during preliminary design and analysis process. So it could be imply that simple analysis methods, such as 1D, 2D and quasi-3D, are not only not abandoned, but also very practical and most applied in preliminary design,... 

Axial-flow compressor is one of the most basic components of gas turbine engines. Consequently, it is essential to design this machine appropriately. Full three dimensional analyses of axial-flow compressors is time consuming due to the flow field complexity, so a method with minimum running time and producing an acceptable design is required. One dimensional design method is a low cost procedure with acceptable results for preliminary stages of design. It receives inlet flow conditions, such as total pressure ratio, mass flow and rotational speed and designs a compressor which satisfies the desired input data. Too many efforts have been accomplished to predict energy losses, design... 

Improvement of axial flow compressor is usually goal of manufacturers of these equipments. Because basic role of it in gas turbine efficiency too many researchers have effort to know phenomenon and effect of them on axial flow compressor's revenue and optimization of them. In this project the aerodynamic of axial flow compressor studied and effect of important parameters such as diffusion factor coefficient, optimum incidence angel and Mach and Reynolds number determined from text and papers. Then obtained a model from experimental data to determine shock loss and extended algorithms to specify critical Mach number and chocking mass flow. With quotation Craig and Cox method we determined a... 

Nowadays, the axial transonic compressors are used widely in aircraft engines, oil and gas industry and etc. because of higher pressure ratio and more efficiency than the other compressors. The Major part of losses in transonic compressors is due to shock waves. In this study the idea of using Shock Control Bump as a passive flow control method has been used for weakening the shock waves. The Shock Control Bump is modeled with the Hicks-Henne function and added to the suction side of a section of the NASA rotor 67 blade. Validation of flow solver is done in both two and three dimensions. Single-point and multi-point optimizations are performed in the design condition and in two off-design... 

Streamline Curvature method is one of the most commonly used methods by industry for prediction of axial flow compressors. This method analyze axial compressor by solving radial equations in the meridional plane to locate streamlines and also by using empirical models to predict total pressure loss. Despite growth of CFD models, Streamline Curvature method has been considered as most practical method for compressor preliminary design and performance assessment because of it’s high speed and good precision. In the current work a C++ code (SLC) has been developed using streamline curvature for axial flow compressor performance analysis. This code receives compressor geometry, properties of... 

Transonic flow compressors are widely used today. In these systems, the occurrence of shock waves, interaction of the shock and the boundary layer, thickening of the boundary layer and separation are some challenges which can severely affect the aerodynamic performance. Here we use a numerical analysis and an optimization algorithm to optimize the aerodynamic shape of a transonic axial compressor blade section. The total pressure loss through a cascade of blade sections is selected as the cost function. A continuous adjoint optimization method is used along with a RANS solver to find the new blade section shape. Application of three different geometric modelling of a compressor blade section... 

The objective of the current work is to investigate the application of tandem blade rotor for possible improvements of a transonic fan. A near term application of tandem blade rotor could be either in the last stages of a high pressure compressor or in the fan section. The present research is motivated by evaluating the tandem configuration for transonic fan of high bypass ratio turbofan engines. The main idea is to achieve higher overall blade loading and at the same time lowering the flow separation tendency by shifting the boundary layer growth to the rear rotor. A computational fluid dynamics code, solving the Navier-Stokes equations based on a flexible multiple-block grid discretization... 

Improving the performance of compressors plays a key role in saving energy in industries. The presence of aleatory and epistemic uncertainties, such as dimensional, geometrical and environmental uncertainties, causes the tolerances that are within the allowed ranges in normal assembly conditions to violate the assembly requirements in operational conditions and cause a drop in compressor efficiency. In order to reach the dimensional and geometrical tolerances of the components of a compressor, especially in the design of the rotor and stator blades, that guarantees the optimal and stable performance while not increasi the production costs, there is a need for an optimal and robust tolerance...