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tpeta n/(n-1) l turbine (dp/p) l combust To5 To5 To1=Toa Poa = Po1 Po2 Po3 Po4 Po5 To2 To3 To4 To6 To7 Po6 Po7 Po7/Pc8 Po7/Pa Po2/Pc9 Po2/Pa T8 C8 P8 Rho8 A8/m8 T9 C9 P9 rho9 A9/m9 Specific Thrust, ST Thrust f/a mfuel TSFC TSFC' ST | core m 0.9 4.4400 0.065 1027 C 1300 K 236.550 K 0.263 Bar 0.434 Bar 1.085 Bar 4.995 Bar 4.671 Bar 277.31 K 370.93 K 602.39 K 1097.38 K 872.68 K 2.199 Bar 0.795 Bar 1.8530 4.1100 1.8930 2.2440 748.02 535.02 381 Turbine polytropic efficiency Turbine polytropic factor, k/[(k-1)Ctpeta] Combustor fractional pressure drop High pressure turbine inlet temperature To5(K)=To5(C)+273 Toa=Ta+Ca^2/(2CCpa*1000) Po1 = Poa = PaC(Toa/Ta)^3.5 Po2=FPRCPo1 Po3=(LPCPR)Po2 Po4=Po3(HPCPR) Po5=Po4C[1 - (dp/p)] | combust To2=To1CFPR^[(n-1)/n] I comp To3=To2C(LPCPR)^[(n-1)/n] | comp To4=To3CHPCPR^[(n-1)/n] | comp To6=To5-(Cpa/Cpg)C(To4-To3) To7=To6-(Cpa/Cpg)[(B+1)(To2-To1)+(To3-To2)] Po6=Po5C(To6/To5)^[n/(n-1)] | turbine Po7=Po6C(To7/To6)^[n/{n-1)] | turbine Crit. press. ratio: Po7/Pc8=[(4/3+1)/2]^4 Core flow is choked Crit. Press. ratio: Po2/Pc9=[(7/5+1)/2]^3.5 Bypass flow is choked IF (Po7/Pc8) < (Po7/Pa) THEN T8=2CTo7/(4/3+1) ELSE T8=To7/(Po7/Pa)^0.25 IF (Po7/Pc8)<(Po7/Pa) THEN C8=(287CT8C4/3)^0.5 ELSE C8 = [(To7-T8)C2000CCpg)]^0.5 IF Pc8>Pa THEN P8=Po7/(Po7/Pc8) ELSE P8=Pa Rho8=100CP8/(0.287*T8) A8/m8 = 1 / (C8CRho8) IF Pc9>Pa THEN T9=2To2/(7/5+1) ELSE T9=To2/(Po2/Pa)^(1/3.5) IF Pc9>Pa THEN C9=(287CT8C7/5)^0.5 ELSE C=[(To2-T9)C2000CCpa]^0.5 IF Pc9>Pa THEN P9=Po2/(Po2/Pc9) ELSE P9=Pa Rho9=100CP9/(0.287CT9) A9/m9=1 / (C9CRho9) ST = C8+C9CB-CaC(B+1)+[(P8-Pa)C(A8/m8) +(P9-Pa)C(A9/m9)CB]C10^5/(B+1) Total engine thrust= mair(specific thrust) f/a=Cpg(To5-To4)/HV Fuel flow rate=mairC(f/a)/(B+1) TSFC=(f/a)/[spec. thrust)(B+1)] TSFC'=3600CTSFC ST based on m8 = (B+1)CST K m/s 0.429 Bar 0.200 kg/m^3 0.0094 m^2-s/kg 231.09 K 304.72 m/s 0.229 Bar 0.346 kg/m^3 0.009 m^2-s/kg 242.9 N-s/kg 24294.4 N 0.0186 0.466 kg/s 0.000019 kg/N-s 0.069 kg/N-hr 971.8 N-s/kg The specific thrust is presented in two forms, one based on the total mass flow rate to the engine and the other based on the mass flow rate to the core engine. The former, ST, allows easy comparison with engines of comparable frontal area, while the latter, ST | core m, is useful in showing the thrust increase due to addingPDF Image | Advanced Systems Steam Power Plant
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