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Performance Prediction of a S-CO2 Turbine

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Performance Prediction of a S-CO2 Turbine ( performance-prediction-s-co2-turbine )

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Appl. Sci. 2020, 10, 4999 14 of 21 The data obtained after the reconstruction of all the calculation examples were summarized. Then, the average relative error and maximum relative error of the temperature and pressure at the stator blade and rotor blade were obtained with the box chart, as shown in Figure 10. The results show that the average relative error of the field is less than 1.5%, and the error of the stator blade temperature and the rotor blade pressure is relatively small. The maximum relative error is less than 15%, and the prediction error of the stator blade pressure is small. The above description shows that the reconstructed field is in good agreement with the field calculated by CFD, and the reconstruction Appl. Sci. 2020, 10, x FOR PEER REVIEW 15 of 24 method is effective. (a) (b) FiguFreig1u0re. T10h.eTrhelaretilvateiveerreorro:r(:a()a)ththeeaaveragerellattiivveeeerrorro;r(;b()bt)htehmeamxiamxuimurmelarteivlaeteirvreore.rror. The pTrhedpircetdioicntiroensurelstus,lt3s,-D3-DCFCDFDrerseusultltssand errordiisstrtirbibuutiotinosnosfoCfaCseassAesaAndaBndarBe sahroewsnhoinwn in FigurFeisg1u1reasn1d11a2n,dre1s2p,ercetsipvecltyi.vIetlyc.aInt bcaenfobuenfdouthndattthaet cthloeucdlomudapmdaipstdribsturitbiountionf tohfethperepdriecdtioctniornesults results is basically the same as that of the CFD results, which is in good agreement. All kinds of key is basically the same as that of the CFD results, which is in good agreement. All kinds of key typical typical phenomena in turbine are captured and predicted, including: phenomena in turbine are captured and predicted, including: 1. 2. 3. 4. 1. Stagnation phenomenon of high temperature and high pressure in the S_LE. Stagnation phenomenon of high temperature and high pressure in the S_LE. 2. The local acceleration of S_LE due to the large curvature change results in a small area of low The local acceleration of S_LE due to the large curvature change results in a small area of low pressure and low temperature. 3p.ressTuhreetiapncdlelaorwantcemofpreortaotrubrlea.de is affected by the pressure difference between both rotor blade sides and the larger negative impact angle. This causes the working fluid in the tip clearance to The tip clearance of rotor blade is affected by the pressure difference between both rotor blade accelerate from the pressure side to the suction side. Therefore, the pressure and temperature sides and the larger negative impact angle. This causes the working fluid in the tip clearance to near the tip of the rotor blade will be relatively low. accelerate from the pressure side to the suction side. Therefore, the pressure and temperature 4. The flow separation due to deviation from the design condition. It is worth noting that the flow near the tip of the rotor blade will be relatively low. in these regions is very complex, so the corresponding prediction error will increase accordingly. The flow separation due to deviation from the design condition. It is worth noting that the flow However, the error is still small, completely within the acceptable range. in these regions is very complex, so the corresponding prediction error will increase accordingly. However, the error is still small, completely within the acceptable range. The computation costs of different methods are compared in Table 3. The evaluation time of the CFD solver is the average time to obtain the numerical result with design input. Since ResNet based surrogate models could amortize computational overhead per instance by predicting multiple instances in parallel, we measured the average time cost for batch size 32 running on a Nvidia Geforce-1080. It can be found that GPU accelerated ResNet model only needs 0.04 s to obtain a prediction result. Compared with the conventional CFD method, our method can quickly predict the physical field on the blade surface and the aerodynamic performance of the turbine. It can greatly reduce the design cycle of the turbine. In addition, the off-design performance of the turbine unit can be mastered in real time in the actual operation of the system, so as to adjust and control the system in time and realize the rapid response of the system.

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