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model this experimental data correctly, a linear interpolation was performed for that region of the data and a slope was incorporated on the choke line. 3.4 Modeling Decisions The two experimental configurations available for modeling were NASA Rotor 1- B and NASA Stage 35 (see Appendices A and B, respectively). Rotor 1-B was a transonic rotor which had a mid-span damper. Experimental data was available for Rotor 1-B for its 100%, 90%, 70%, and 50% speed lines, with each speed line consisting of six to eight data points at various mass flow rates. At the meanline, the Rotor 1-B 100% and 90% speed lines corresponded to supersonic relative inlet conditions and the 70% and 50% speed lines corresponded to subsonic relative inlet conditions. Stage 35 consisted of a rotor (Rotor 35), and a stator (Stator 35) which was exposed to the exit flow of Rotor 35 in a stationary frame of reference. Rotor 35 information consisted of three data sets, which were the 100%, 90%, and 70% speed lines, with each speed line containing five data points at various mass flow rates. Two-dimensional cascade data is obtained using a constant inlet relative Mach number with a varying angle of attack in order to create the loss curve. To obtain an analogous loss curve for constant inlet relative Mach number would be extremely difficult for a 3-D annular cascade. It would require varying the rotor speed and throttle simultaneously until the inlet relative Mach number matched that for the previous test condition. Therefore, 3-D rotor data is obtained by opening the throttle of the compressor, which increases mass flow, inlet relative Mach number, and subsequently decreases the angle of attack. A difference arises due to the fact that off-minimum-loss loss curves created in 2-D cascades use a constant inlet relative Mach number, while off- minimum-loss curves in 3-D cascades occur over a range of inlet relative Mach numbers. This creates a problem in comparing 2-D to 3-D loss curves because only one point of each 2-D constant Mach number loss curve can be compared to experimental 3-D data. 27PDF Image | Gas Turbine Design Axial Flow Compressors
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