Generation of 3D Turbine Blades for Automotive ORC

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Generation of 3D Turbine Blades for Automotive ORC ( generation-3d-turbine-blades-automotive-orc )

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Mathematics 2020, 9, 50 10 of 30 Table 3. Definitions of blade thickness coefficients. Shroud Hub C=− B Mathematics 2020, 8, x FOR PEER REVIEW F=−2θ4 + 1 cotβ5h +cotβ4 m3 m2 r5h rr D = cotβ5h B= 1 cotβ4 −cotβ5s E= 3θ4 − 1 2cotβ5h +cotβ4 m2 r4 r5s m2 m4 r5h rr 4 4􏱅􏱆 A = cotβ5s 􏱅r5s􏱆 􏱅r5h􏱆 2m4 4 4 10 of 34 Mathematics 2020, 8, x FOR PEER REVIEW Figure 7. Meridional profiles of the turbine blade. Figure 7. Meridional profiles of the turbine blade. 11 of 34 In the current study, the blade is not radially fibred. The blade distribution of blade angles is determined by the numerical integration of Equations (15) and (16), where 𝑚 is the meridional distance along the 𝑍−𝑅 contour, Figure 7. The coefficients 𝐴 to 𝐹 are summarized in Table 3. Equation (15) is the blade camber-line along the shroud contour, whereas Equation (16) is the camber- line along the hub contour. The distribution of the blade angle is shown in Figure 8. 𝜃(𝑚)=𝐴𝑚+𝐵𝑚2 +𝐶𝑚4 (15) 𝜃(𝑚)=𝐷𝑚+𝐸𝑚2 +𝐹𝑚4 (16) Table 3. Definitions of blade thickness coefficients. Shroud 𝐴 = 𝑐𝑜𝑡𝛽5𝑠 Hub 𝐷 = 𝑐𝑜𝑡𝛽5h 𝑟5𝑠 𝐵= 1 [𝑐𝑜𝑡𝛽4−𝑐𝑜𝑡𝛽5𝑠] 𝐸=3𝜃4− 1 [2𝑐𝑜𝑡𝛽5h+𝑐𝑜𝑡𝛽4] 𝑚2 𝑟 𝑟 𝑚2 𝑚 𝑟 𝑟 445𝑠 445h𝑟 𝐶=− 𝐵 𝐹=−2𝜃4+1[𝑐𝑜𝑡𝛽5h+𝑐𝑜𝑡𝛽4] 2𝑚 𝑚3𝑚2𝑟𝑟 4 445h𝑟 Figure 8. DistributioFnigoufrreo8t.oDr bisltardibeuatinognleosf.rotor blade angles. BladethicknBelsasdiestdhisictrkibnuestesdisindtihstrreieburetgedionins,tnharmeelrye,glieoandsin,gn-aemdgel,y,mleraidionnga-eldpgroef,ilme,earnidional trailing edgep.rAofis lwe,ilalnbde tsrhaoiwlinglaetdegr,eb. lAadsewroilol tbies stheowlocnaltaiotenr,wbhlaerdeesrtoreostsiisstthe lhoicgahteiostn. Twhheerreefosrter,ess is the highest. Therefore, this region must be the thickest to improve the weight distribution this region must be the thickest to improve the weight distribution of the blade. To obtain thick root, of the blade. To obtain thick root, the blade is tapered from hub to tip. Thicknesses at inlet the blade is tapered from hub to tip. Thicknesses at inlet and exit of the leading edge and trailing and exit of the leading edge and trailing edge, Figure 9, are calculated using Equations (17)– edge, Figure 9, are calculated using Equations (17)–(20) [27,58]. 𝑡5𝑡 and 𝑡5h are the tip and hub exit (20) [27,58]. t and t are the tip and hub exit thicknesses and obtained from the mean-line thicknesses and obtained5ftrom th5eh mean-line model [31]. In the current study, the blade thickness at the hub (𝐿𝐸h) is obtained using Equation (20) to keep thicker root. Figure 9 also presents the developed 3D rotor blade. 𝑇𝐸𝑡= 𝑡5𝑡 (17) 𝑐𝑜𝑠𝛽5𝑡 𝑟5h

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