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Master Thesis Report Verification of 2D Fitting Results Table 5.3: Calculated BC Data at tip radius Parameters Speed of Sound Relative Stagnation Pressure Relative Stagnation Temperature Peripheral Speed Relative Tangential Speed Absolute Tangential Speed Hub Radius Absolute axial speed Inlet relative flow angle Symbols Values alocal 340.263 m/s βin 71.085 ◦ Units P01,rel 313517.943 T01,rel 397.901 K U 431.765 m/s Wθ 444.21 m/s Cθ 12.44 m/s Rhub 0.096375 m Caxial 152.215 m Pascal In order to ensure that the inlet relative flow angle matches the metal blade inlet angle, the value of the axial velocity was adjusted to ensure a small or zero incidence angle for the various radial position considered. The computed inlet boundary conditions for profiles at other radial position is presented in table 5.4. For the purpose of verifying the 2D fitting approach, 4 different blade profiles located at various span position distributed across the hub and tip was used. Their radial position is also presented in table 5.4. Table 5.4: Calculated Inlet BC Data at other radial position Parameters Peripheral Speed Absolute tangential Speed Absolute Speed Relative Speed Relative Stagnation Pressure Relative Stagnation Temperature Inlet Relative Flow Angle Inlet Blade Metal Angle Inlet Incidence Angle Axial Velocity Symbols Radius 0.1265 U 212.52 Cθ 25.27 C 233.373 C 332.22 P01,rel 186627.41 T01,rel 343.09 βin 45.71 Metalin 44.01 - 1.697 Cax 232 Radius 0.1565 262.923 20.43 232.89 366.215 210111.6973 354.906 50.69 49.608 1.083 232 Radius 0.1865 313.32 17.145 232.63 403.774 241482.33 Units 5.2 2D Outlet Boundary Conditions In order to compute the outlet boundary conditions, the radial equilibrium condition was used to compute the stagnation condition at each radial position. Since the static pressure at 1 outlet condi- tion is required, the outlet pressure at the mean radius was estimated based on the design pressure ratio and the assumed inlet static pressure. It should be pointed out that a simplification of the radial equilibrium condition was used when computing the outlet stagnation condition at each radial position. Theory of Radial Equilibrium The theory of radial equilibrium is based on the fact that the flow in axial turbomachines are in general three dimensional. This implies that the radial velocities through a blade row may become 54.93 59.55 55.4 60.86 -0.47 -1.31 232 232 Radius 0.2265 380.524 m/s 14.117 m/s 232.429 m/s 457.784 m/s Pascal K ◦ ◦ ◦ m/s 298778.283 369.3015 392.463 40PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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