An effective methodology for optimal design of axial turbine blades is presented. It has been used for achieving stage maximal efficiency meeting both stress-strain and vibration reliability requirements and taking into account technological limitations.
A new method for centrifugal and mixed-type compressors flow paths design based on a unique integrated conceptual design environment is presented in this article. At the heart of this new method is the translation of proven, integrated design environments that have been successfully used for axial turbomachinery for many years. This integrated environment is a seamless and swift processing scheme that incorporates stages aerodynamic analysis and preliminary design/sizing based on the one-dimensional method interactive spatial blade profiling, export of blade geometry to CAD and CFD tools, 3D stress and vibration analysis, and finally, flow modeling. The design process is demonstrated for a centrifugal compressor design utilizing AxSTREAM software.
In recent decade, industry had started to use intensively 3D simulation in turbine flow path and its components design. At the same time, this remains a very labor- and time-consumable process that sufficiently hampers its usage, whereas unidimensional and axisymmetric analyses are still widely used in the industry practice. A comparison of the data obtained from experiments conducted on a single stage air turbine test model with the results of 1D and 2D modeling and 3D simulation using a CFD solver was performed. The results were analyzed to validate a judgement of the authors that along with 3D CFD methods the low-fidelity models can be successfully used for turbine flow path optimization with the help of DoE methods. The forthcomings and advantages of different models are also discussed.
The use of S-CO2 as working fluid in a power cycle has been growing in recent years due to associated benefits such as highly compact power plant and high cycle thermal efficiencies for application including waste heat, solar thermal and nuclear power plants. Many authors have presented studies on S-CO2 cycle and its modifications and there also exists many patents which claim different embodiments of the S-CO2 cycle for different heat sources. Each author of the S-CO2 cycle embodiment uses some specific tool to analyze the cycle performance with assumed values of component efficiencies. In the S-CO2 cycle the ratio of turbine work to compressor work is relatively small and its variation may cause a significant influence on cycle performance estimation accuracy. Exact prediction of the S-CO2 cycle performance requires defining exact turbomachinery efficiency magnitudes. However, S-CO2 turbines and compressors are in development stage except for several low power scale prototypes and hence it is very difficult to make assumptions on efficiency and they need to be designed. To enable design of cycle from concept to detailed design of the turbomachinery, the authors in this work have developed a flexible design system which is starting from heat balance calculation, continues with sizing of turbomachinery flow path, through 1D/2D/3D aero and structural multidisciplinary optimization. Such a design process is iterative because a refinement of the turbomachinery efficiencies lead to change in cycle boundary conditions for turbomachinery design and the design needs to be refined by recalculation of the cycle. In the present work, four different embodiments of S-CO2 thermodynamic cycles were analyzed using assumed component efficiencies and based on the actual design of the turbomachinery components the cycle was recalculated and accurate performance of the cycle was predicted. It is observed that the turbine efficiency has significant influence on the overall cycle performance compared to the compressor efficiency.
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