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By the results at the same engine overall pressure ratio and inlet turbine temperature the radial-axial engine produce more thrust so is more powerful because thrust parameter is higher than one, if the fan has a low overall pressure ratio and is determined a high bypass ratio.
The paper presented a computing method of comparison for two types of turbofan configuration on condition of the same inlet turbine temperature, engine overall pressure ratio and power turbine and calculates the engine performance for two different turbofan engines configurations.
The second set of diagrams from fig.4 present the variations of percent specific fuel consumption parameter with fan overall pressure ratio and bypass ratio for at one inlet turbine temperature.
The first set of diagrams from fig.3 present the variations of percent thrust parameter with fan overall pressure ratio and bypass ratio for at one inlet turbine temperature.
The results are diagrams with variation curves of thrust and fuel consumption, function of the bypass ratio [K.sub.F.E] and overall pressure ratio [[pi].sub.F.t.E] of the fan at constant inlet turbine temperature [ITT.sub.R]
From equations (9) it is calculated the overall pressure ratio of the fan for the second engine and the overall pressure ratio of LPC and HPC depending on inlet enthalpy of fan and compressor.
The overall pressure ratio of the engines are equal in value but different in configuration.
Design D achieves low mission NOx emissions by reducing the engine overall pressure ratio and combustor temperature, which is similar to design C (minimum LTO NOx emissions).
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