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Chapter 3.0 Approach The objective of the present research is to evaluate the existing loss and deviation models at the meanline by comparing them to experimental data obtained for a rotor and a stage. A study was conducted of the compressible meanline code (CMLC) developed by Hale at Arnold Engineering Development Center (AEDC). The initial objectives were to comprehend how the code functioned and to prepare it for the correlation study. This was accomplished by reviewing the theory in the CMLC for completeness and correctness. A review of the CMLC FORTRAN coding was conducted and modifications were performed which made the codes more user friendly and expandable. The CMLC was also updated to handle additional input situations and compute source terms. Lastly, test cases were executed in order to verify the code with regard to accuracy and robustness. 3.1 CMLC Theory The CMLC is a compressible, 1-D, steady-state, stage-by-stage characteristics solver. It also has the capability to become a pseudo 2-D solver if the positions of streamtubes and their respective inputs are known. The CMLC code assumes a perfect gas with constant properties, inviscid flow and adiabatic walls upstream and downstream of the blades, and constant rothalpy within a streamtube through the blades. The blade rows are replaced by semi-actuator disks, and all of the losses and inefficiencies that are manifested in the span of the blade are modeled by loss and deviation correlations. Semi- actuator disk theory replaces the blade geometry with an externally imposed discontinuity in the flow properties over the axial spacing of the bladed region (Hale, 1996). Below is a listing of the equations and methodology used by the CMLC. Given the relative inlet Mach number M1, the swirl angle α1, static pressure P1, static temperature T1, compressor rotational speed Ω, streamline radii r1 and r2 at the inlet and exit of the blade, the 3-D streamtube contraction ratio MVDR, and loss (ω3D) and deviation (δ), all thermodynamic and fluid flowfield properties may be obtained. Below is a list of some compressible flow relations that the CMLC uses throughout its progression. 19PDF Image | Gas Turbine Design Axial Flow Compressors
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