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Chapter2. Theory 7 cycle (Eq. 2.5). Here, β is the fuel-to-air-ratio (FAR) and Hc the heat of combus- tion. The thermodynamic efficiency of an engine can be increased by either in- creasing the nozzle exit velocity c9 of the air or decreasing the FAR, assuming that F, c0, Hc = const. Decreasing the FAR also lowers the specific fuel consumption (SFC) [4]. ηth ≡ WU = c29 − c20 (2.5) Q ̇ i 2 · β · H c The second performance indicator is the propulsive efficiency (Eq. 2.6). It de- scribes how much of the thermodynamic work WU produced is converted into usable thrust WF. The propulsive efficiency is greatest for c9 c0. This di- rectly conflicts with the optimisation of the thermal efficiency as described above, meaning that an increase in propulsive efficiency always goes in hand with a de- crease in thermal efficiency. ηp≡WF= 2 (2.6) WU 1 + c9 c0 Both efficiencies can be combined into the overall efficiency η of an engine, Eq. 2.7. η = ηth · ηp (2.7) Since the propulsive efficiency can only be enhanced by modifying c9, this value is no longer available for improving thermal efficiency. Therefore, the latter may only be increased by lowering the FAR β, assuming c0, Hc = const. This is pos- sible by either increasing the mass flow m ̇ 0 or by increasing the overall pressure ratio (OAPR) of the compressor, thus raising the temperature at the compressor outlet and reducing the amount of heat needed for combustion. In modern civil aviation, turbofan engines are the most commonly used engine type. These double-shafted machines consist of a core engine that is encased by a bypass duct and make use of high bypass ratios (BPR) μ. This allows increas- ing m ̇ 0, while reducing the average exit velocity c9 and c19, thus providing an optimal propulsive efficiency while maintaining a high level of thrust. Moreover, the higher throughput reduces the FAR, therefore lowering the SFC and improv- ing thermal efficiency. Turboprop engines, having a propeller instead of a fan and lacking an outer nacelle, are another engine type that is used for smaller and lighter regional aircraft, as their maximum airspeed cannot match that of turbo- fan engines.PDF Image | Investigation of wing installation effects on the sound field of a model jet engine
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