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66 Integrated system design Table 4-1: Specifications of the Rolls-Royce Trent 1000 engine and airliner Boeing 787 Rolls-Royce Trent 1000 [51] Dry weight Fan air mass flow Rotational speed kg 5409.0 kg/s 1089.0 - 1211.0 RPM 13500.0 (high pressure turbine) kN 283.6 (take off, S/L), 65.4 mg/Ns 13.787 (take off), 14.325 (cruise) — 10.4 - 11.0 (take off), 10.7 (cruise) — 47.7 (take off), 50.0 (climb) kJ/kg 42800.0 Thrust∗ (ISA) Specific fuel consumption (ISA) By pass ratio Overall pressure ratio Boeing 787 [71] Cruise speed Take off speed [72] Maximum certified altitude Number of engines Other information Fuel lower heating value [9] ∗ Cruise conditions, 10670 m, Trent 900, at 0.85M m/s 0.85M m/s 84.89 m 13135.0 — 2 In order to establish a common frame for the comparison between the s-CO2 Brayton system and the Trent engine, it is necessary to study the thermodynamic behavior of the latter. It is possible then to set specific targets for the s-CO2 system based on the results of this analysis, which is the objective of the next sections. Turbofan overall performance The turbofan overall efficiency is the product of the thermal and propulsive efficiencies, ηOV = ηTHηPR, (4-1) where ηTH stands for the thermal efficiency and ηPR for the propulsive efficiency. The thermal efficiency is the standard efficiency of a gas power cycle, which indicates the quantity of energy that is transformed into useful power in the engine, ηTH = W ̇ PR , (4-2) fFL LH VFL where fFL is the fuel mass flow and LHVFL the correspondent lower heating value. W ̇ PR stands for the propulsion power generated by the engine, which is not completely transformed into thrust. Consequently, a second indicator, the propulsive efficiency, is necessary to quantify the quality of the transformation of the engine power into the actual thrust, ηPR = W ̇ TT . (4-3) W ̇ PR Where W ̇ TT is the thrust power, that is the power that actually moves the aircraft, W ̇ TT = FTTv0, (4-4) where v0 and FTT correspond to the aircraft velocity and the engine thrust respectively. The turbofan engine generates the propulsive power by means of the core and the fan, J.S. Bahamonde Noriega W ̇ PR = W ̇ PR,CR + W ̇ PR,FN, (4-5) Master of Science ThesisPDF Image | Design method for s-CO2 gas turbine power plants
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