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3.3.2.3 Turbomachinery efficiencies In an ideal compression or expansion process the assumption is made that there is no change in entropy. In a real process however, several losses take place as the fluid flows through the component resulting in an entropy generation. For a compressor this results in a higher temperature and enthalpy, and hence work, at a given pressure ratio compared to what would be expected from an ideal process. For a turbine, the outlet pressure will always be lower at a given power output requirement [15]. The two most common ways to account for losses in the turbomachinery components is the isentropic and polytropic efficiency. Isentropic efficiency The isentropic efficiency of a compressor is defined as the ratio between the change in enthalpy for an ideal process, and the change in enthalpy for the actual process. For a turbine the isentropic efficiency is defined as ratio between the change in enthalpy for the actual process, and the change in enthalpy for the ideal process [15]. Polytropic efficiency The isentropic efficiency can be misleading when comparing compressors and turbines with different pressure ratios or at different inlet conditions. If the necessary calculations are performed for each stage of a multistage component, with the assumption that each stage operates at the same isentropic efficiency, the result would be that the efficiency of the whole component is lower than the stage efficiency. Consequently isentropic efficiency is not a suitable parameter when performing optimization studies. For such studies, the polytropic efficiency can be used. The polytropic efficiency can be defined as the isentropic efficiency at an infinitely small stage in the compression or expansion process, such that it can be assumed constant throughout the entire process [15]. Therefore the turbomachinery polytropic efficiencies have been used in this project. The efficiency calculations are based on outputs from both the thermodynamic analysis and the sizing procedure, and are based on the following parameters: Entry into service correction, Reynolds number index effect, size variation and normalized efficiency. These are all based on empirical data. The method used can be found in [21]. 3.3.3 Combustion chamber In order to commence the combustion chamber sizing, a few assumptions need to be made by the designer. These assumptions are based on the guidelines in [22] where the full sizing procedure can also be found. A typical burner can be seen in figure 6. Loading Combustor volume must be derived considering the combustor loading at a number of flight conditions. At static sea level maximum power the combustor loading should be less than 10 ๐๐ . A critical point for the burner is the ability to relight during windmilling following an ๐ ยท๐๐ก๐1.8ยท๐3 engine flameout. In order to achieve this the designer must make sure that the combustor loading at the highest required altitude and lowest flight Mach number for relight does not exceed 300 ๐๐ [23]. To minimize the volume of the burner, the loading should be close to 300 at ๐ ยท๐๐ก๐1.8ยท๐3 windmilling conditions. A smaller burner however, leads to a higher pressure loss. The definition can be found in appendix A. Residence time The residence time depends on the length of the liner and the Mach number after the diffuser, and should typically exceed 3ms. Long residence times however, can result in increased NOx. 24PDF Image | Conceptual Design of a Supersonic Jet Engine
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