Effects of aero-engine degradation on specific fuel consumption at varying ambient and turbine inlet temperatures.
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Date
2023-08-04
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FETiCON
Abstract
The paper presents the effects of aero-engine degradation on specific fuel consumption (SFC) at varying ambient temperature (ABT) and turbine inlet temperature (TIT). The ABT and TIT were varied using analytically developed equations. The SFC, ABT and TIT were modelled to determine the performance of the engine at each instance. A 4- stage compressor and a single stage turbine were investigated for 0 to 10% area reduction of the blades. Increase in degradation and margin to permanent failure were examined. The ranges of ABT and TIT considered were 295 to 325 K and 1083-1245 K respectively. SFC against ABT, TIT, mass flow rate and net power produced at each level of blade degradation were plotted. Results showed that for undegraded compressor blades, the changes in the ABT did not have significant effect on the compressor’s exit temperature. However, at 8% blade degradation, the effect was noticeable and became risky at 10% where the exit temperature seemed to be increasing beyond tolerable temperature of the material. It was also observed that SFC increased with increasing TIT. The results predict that margin to permanent failure of the engine would occur at 10% compressor’s blade degradation when the SFC would have risen to 0.5 kg/kWh, ABT (315 K), TIT (1100 K) and fuel flow rate at 0.4 kg/s. In conclusion, to prevent complete engine-out, the revolution per minute of the engine at these conditions should be reduced to 80% and landing procedures initiated.
KEYWORDS: Specific fuel consumption (SFC), ambient temperature (ABT), turbine inlet temperature (TIT) and surface area degradation.