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take-off conditions, but the core weight estimate was reduced (from the value typical for a turbofan engine) because of an assumed one-third reduction in low-pressure shaft and power turbine weight due to higher shaft speed and a shorter power shaft. The turboelectric system weighs 5000 lb (2300 kg) more than the 16-engine system but has 9 percent lower TSFC including the 1 percent electrical and refrigeration loss at takeoff. (The electrical loss at cruise would be lower, due to much lower required refrigerator power at cruise, but the take- off efficiency is used to make the estimates that follow.) Table 3 shows a comparison of different propulsion systems (16 turboelectric distributed fans with 2 cooling options, 16 conventional small turbofan engines, and 2 conventional large turbofan engines) with the same thrust requirement. Weights exclude propulsors (fans), which would have similar total weights in all systems. TSFC values shown in table 3 are based on best present-day values for the engine size. Refrigerator weight is based on 5 lb per hp input and 30 percent efficiency and HTS AC losses on a 12-μm filament characteristic dimension. To compare the turboelectric system with the 16-turbofan system, by balancing out the opposite effects of lower SFC and higher weight of the turboelectric system, the Breguet range equation, sufficient to determine relative ranking, is applied to both systems, with the requirement of equal aircraft range and approximating the entire flight as cruise. Solving for the required change in fuel weight between the 16-engine case and the turboelectric case, we find that the turboelectric aircraft would require 7 percent, or 3000 lb (1400 kg) less mission fuel. Thus, the slightly heavier turboelectric aircraft would have a net fuel savings of roughly 7 percent on each flight, compared to the baseline aircraft powered by 16 small engines. This estimate TABLE 3.—COMPARISON OF DIFFERENT PROPULSION SYSTEMS Propulsion Components System Weight, lb Efficiency, TSFC, (kg) % hr–1 7300 ---- 0.57 (3300) 15 000 99.1 ---- (6800) 7300 ---- 0.57 (3300) Turboelectric distributed fans (refrigerated) Turboelectric distributed fans (LH2 cooled) Conventional small distributed turbofans Conventional large nondistributed turbofans Two 42 380- hp engine cores Total Two 42 080- hp engine cores Two 42 080- hp electric generators (LH2 cooled) Sixteen 5250- hp motors (LH2 cooled) Total Sixteen 5250-hp engine cores Two 42 000- hp engine cores 1900 (860) 3100 (1400) 12 300 (5600) 10 000 (4500) 8700 (4000) 99.9+ ---- 99.9+ ---- 99.9 ---- 91a 0.63 ---- 0.57 Two 42 380- hp electric generators (including refrigerators) 3000 (1300) 99.7 ---- Sixteen 5250-hp motors (including refrigerator) 4700 (2100) 99.4 ---- aRelative to 42 000-hp engine core at 0.57 thrust specific fuel consumption. 8PDF Image | Distributed TurboElectric Propulsion for Hybrid Wing Aircraft
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