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Mathematics 2020, 9, 50 Mathematics 2020, 8, x FOR PEER REVIEW Mathematics 2020, 8, x FOR PEER REVIEW 17 of 30 18 of 34 Figure 18 depicts the contours of the total pressure and temperature through the turbine depicts the contoTuhresroefstuhletstointatlhpisressescutiroenaanrdetbeamsepderoantutrheethbroouungdharthyectounrdbitnioensstapgresaetnatsepdainoTfa5b0l%e 1. . Figure 18 6.1.2. Results atTDhesirgensuPltosinint this section are based on the boundary conditions presented in Table 1. The results in this section are based on the boundary conditions presented in Table 1. Figure 18 stage at a span of 50%. From the inlet of the stator to the exit of the rotor, the pressure Fromtheindleptiocftsththeesctaotnotroutorsthoeftehxeittotfatlhperersostuore,tahnedptreemsspuereatduerceretharsoeusgfrhotmhe9t0u0rbkiPnaetsota1g3e0aktPaas,panof50%. decreases from 900 kPa to 130 kPa, while the temperature decreases from 471 K to 448 K. while the teFmropmertahtuerienldeetcorfeathsessftraotomr t4o71thKe teoxi4t4o8fKth.eTrhoetopr,etshseurperedsrsouprethdreocurgehastehsefrtoumrbi9n0e0sktaPgaeto 130 kPa, The pressure drop through the turbine stage satisfies the expansion requirement of the satisfies thewehxipleanthsieontemreqpueriraetumrendteocfrtehaesedsefsriogmn p4o7i1ntK. to 448 K. The pressure drop through the turbine stage design point. 18 of 34 6.1.2. Results at Design Point Figure 17. Comparison between numerical results and experimental results. Figure 17. Comparison between numerical results and experimental results. Figure 17. Comparison between numerical results and experimental results. 6.1.2. Results at Design Point satisfies the expansion requirement of the design point. Figure 18. Pressure (a) and temperature (b) distributions at design point (N = 40,000 rpm, PR = 6.9). Figure 18. Pressure (a) and temperature (b) distributions at design point (N = 40,000 rpm, PR = 6.9). Figure 18. PHreoswsuervee(ra,)tahnedhtiegmhp-pereastusurere(br)adtiostreibsutlitosnisnaht idgehsiMgnapchointu(mNb=e4r0v,0a0lu0 erps mat, tPhRe =st6a.9to).r exit However,thehigahn-dprheisgshurleoaradtinogreosnutlthseintuhribgihneMbalachdensu,mrebsuerltvinagluienshaitgthersftraitcotrioenxiltoasnsedshaingdh,therefore, loading on the tHurobwineelvoebwrl,aetrdhesffi,hcrigieeshnu-cplytri,enasgsusinhreohwriagnthioienrFefrsigiuculttirsoenisn1lho9isagsnhedsMa2na0c.dhH, tnohuwemreevbfeoer,evt,halilosuwhesiegrahtevtfhfaiecluisetnaoctfyoMr, aeasxciht annudmhbiegrh shown in Fliogaudriensg1o9niastnhedex2ptu0er.cbtHeindoewobewlvaiednreg,st,thoriestshuhelitgsihnugdvdianleunheiegoxhfpeMarnfasrcihoctninoounfmlfloboseswresiasatentxdhp,isetchaterredeaf.owrMei,nalcgohwtoneurthmeefbfiecrieinscayl,saos influenced by the operating mass flow rate of the working fluid and the throat opening sudden expsahnoswionionfFfliogwureast t1h9isaanrdea2.0M. Hacohwneuvmerb, ethriishailgsohivnafluenocfedMbaychthneuompbeerartisngexmpaescstefdloowwing to the of the stator vanes. The pressure drop across the stator vanes is used to accelerate the rate of the swuodrdkeingexflpuaidnsaionndotfheflothwroaattthopiseanrienag. oMfatchhe nstuamtobrevrainseasl.soThineflpurensscuedrebdyrothpeaocproersasttinhge mass flow organic fluid as it moves towards the circumferential direction. However, the pressure loss stator vanersaitseuosfedthteowacocreklienrgatefluthide oarngdanthiceftlhuridoaatsoipt emnoinvgesotfotwhaersdtsatohrevcairnceusm. Tfehrenptriaelssduirecdtiroonp. across the across the stator vane is significantly high and results in shock waves. Through the rotor However, tshteatporevsasnueres ilsosusseadcrtossactchelesrtateorthveaonregiasnsicigfnluifiidcaanstliyt mhiogvhesantodwraersduslttshiencsirhcoucmk fweraevnetisa. l direction. blades, the values of Mach number are below unity. Figure 19 also shows the location of ThroughthHeorwoteovrebr,lathdesp,rtehsesuvraeluloessoafcMroasschthneusmtabtoervaraenebeisloswignuinfictya.ntFliyguhrigeh19anadlsroesuhlotwsisntshheockwaves. the shock waves, where a violent change in the pressure gradient occurred in the throat locationofTtherosuhgohckthweavroetso,rwbhleardeesa,vtihoelevnatlucheasnogfeMinacthenpurmesbseureargerabdeileonwtoucncuitryr.eFdiginurtehe19tharolsaotshowsthe area. It is worth mentioning that the modelling approach accounting for the high Mach area.Itiswloocratthiomneonftihoenisnhgoctkhawtatvhes,mwohderlleinagvaioplpenrotacchhanagcecoiunntthinegprfeosrsuthreghriagdhieMntacohccnuurrmedbeirnthethroat number values is presented in [31]. values is praersean.teItdiisnw[3o1r]t.h mentioning that the modelling approach accounting for the high Mach number values is presented in [31].PDF Image | Generation of 3D Turbine Blades for Automotive ORC
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