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Sandia.txt
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Sandia.txt
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Carleton University
Department of Mechanical and Aerospace Engineering
COMPRESSOR PERFORMANCE ANALYSIS RESULTS
Gas Turbine Project
~~~~~~~~~~~~~~~~~~~~~ COMPRESSOR DESIGN ~~~~~~~~~~~~~~~~~~~~~
Compressor Rotational Speed [RPM].............| 75000
Mass Flow Rate [kg/s].........................| 3.5300000
Number of Full Blades.........................| 12
Number of Splitter Blades.....................| 0
Length of Full Blade [m]......................| 0.0000000
Length of Splitter Blade [m]..................| 0.0000000
Length of Meanline Path [m]...................| 0.0353553
Inlet Blade Thickness [m].....................| 0.0007620
Inlet Hub Radius [m]..........................| 0.0025375
Inlet Shroud Radius [m].......................| 0.0093720
Inlet Meanline Radius [m].....................| 0.0068656
Outlet Blade Thickness[m].....................| 0.0007620
Outlet Passage Width[m].......................| 0.0017120
Outlet Tip Radius [m].........................| 0.0186817
Rotor Axial Length [m]........................| 0.0089161
Impeller Roughness............................| 0.0000050
Tip Clearance [m].............................| 0.0002540
Diffuser Exit Radius [m]......................| 0.0296000
Diffuser Exit Passage Width [m]...............| 0.0017120
~~~~~~~~~~~~~~~~~~ THERMODYNAMIC PROPERTIES ~~~~~~~~~~~~~~~~~~
~~~~~~~~~~~~~~~~~~~~ ROTOR INLET - Station 1 ~~~~~~~~~~~~~~~~~
Total Enthalpy (H01): 309.3829231 kJ/kg
Total Entropy (S01): 1.3566805 kJ/kg-K
Total Temperature (T01): 305.3000000 K
Total Pressure (P01): 7690.0000000 kPa
Total Density (rho01): 587.0729767 kg/m^3
Static Enthalpy (H1): 309.1024876 kJ/kg
Static Entropy (S1): 1.3566805 kJ/kg-K
Static Temperature (T1): 304.6215758 K
Static Pressure (P1): 7525.9420234 kPa
Static Density (rho1): 582.8917979 kg/m^3
~~~~~~~~~~~~~ ROTOR LOSSES - Between Stations 1 & 2 ~~~~~~~~~~
Incidence Loss: 0.0000000 kJ/kg
Blade Loading Loss: 0.0624311 kJ/kg
Skin Friction Loss: 1.7614837 kJ/kg
Tip Clearance Loss: 0.5382693 kJ/kg
Mixing Loss: 0.0031799 kJ/kg
Disk Friction Loss: 0.1316572 kJ/kg
Leakage Work Loss: 0.8060351 kJ/kg
Recirculation Work Loss: 0.0000000 kJ/kg
Internal Loss Total: 2.3653641 kJ/kg
Parasitic Loss Total: 0.9376923 kJ/kg
~~~~~~~~~~~~~~~~~~~ ROTOR OUTLET - Station 2 ~~~~~~~~~~~~~~~~
Total Enthalpy (H02): 322.7285618 kJ/kg
Total Entropy (S02): 1.3639870 kJ/kg-K
Total Temperature (T02): 324.0836368 K
Total Pressure (P02): 14072.2154634 kPa
Total Density (rho02): 664.8543440 kg/m^3
Static Enthalpy (H2): 317.7696553 kJ/kg
Static Entropy (S2): 1.3639870 kJ/kg-K
Static Temperature (T2): 317.7001302 K
Static Pressure (P2): 11450.5076959 kPa
Static Density (rho2): 638.1561278 kg/m^3
Rotor Efficiency: 0.7524992 kg/m^3
~~~~~~~~~~~~~~~~~~ DIFFUSER OUTLET - Station 4 ~~~~~~~~~~~~~~~
Total Enthalpy (H04): 322.7285618 kJ/kg
Total Entropy (S04): 1.3672910 kJ/kg-K
Total Temperature (T04): 324.1989348 K
Total Pressure (P04): 13983.8831397 kPa
Total Density (rho04): 660.7825645 kg/m^3
Static Enthalpy (H4): 321.3123022 kJ/kg
Static Entropy (S4): 1.3672910 kJ/kg-K
Static Temperature (T4): 322.0259400 K
Static Pressure (P4): 13054.2783133 kPa
Static Density (rho4): 651.8805825 kg/m^3
Diffuser Efficiency: 0.7426447 kg/m^3
~~~~~~~~~~~~~~~~~~~~~~~ VELOCITY TRIANGLES ~~~~~~~~~~~~~~~~~~~
Imp. Inlet Velocity Triangle (Mean)
Tangential Velocity (U1): 53.9226319 m/s
Axial Velocity (Cm1): 23.6827152 m/s
Relative Velocity (W1): 58.8941528 m/s
Relative Tang. Component (Wu1): -53.9226319 m/s
Relative Flow Angle (Beta1): -66.2890103 deg
Absolute Velocity (C1): 23.6827152 m/s
Absolute Tang. Component (Cu1): 0.0000000 m/s
Inlet Swirl Angle (Alpha1): 0.0000000 deg
Inlet Mach Number (M1): 0.3055268
Imp. Inlet Velocity Triangle (Hub):
Tangential Velocity (U1h): 19.9293611 m/s
Axial Velocity (Cm1h): 23.6827152 m/s
Relative Velocity (W1h): 30.9523898 m/s
Relative Tang. Component (Wu1h): -19.9293611 m/s
Relative Flow Angle (Beta1h): -40.0811147 deg
Absolute Velocity (C1h): 23.6827152 m/s
Absolute Tang. Component (Cu1h): 0.0000000 m/s
Inlet Swirl Angle (Alpha1): 0.0000000 deg
Inlet Mach Number (M1h): 0.1605726
Imp. Inlet Velocity Triangle (Tip):
Tangential Velocity (U1t): 73.6078871 m/s
Axial Velocity (Cm1t): 23.6827152 m/s
Relative Velocity (W1t): 77.3239422 m/s
Relative Tang. Component (Wu1t): -73.6078871 m/s
Relative Flow Angle (Beta1t): -72.1648577 deg
Absolute Velocity (C1t): 23.6827152 m/s
Absolute Tang. Component (Cu1t): 0.0000000 m/s
Inlet Swirl Angle (Alpha1): 0.0000000 deg
Inlet Mach Number (M1t): 0.4011355
Imp. Outlet Velocity Triangle:
Tangential Velocity (U2): 146.7257328 m/s
Radial Velocity (Cr2): 29.8511305 m/s
Absolute Velocity Tangential (Cu2): 94.9065726 m/s
Absolute Velocity (C2): 99.4904393 m/s
Swirl Angle (Alpha 2): 72.5399808 deg
Relative Velocity Tangential (Wu2): -51.8191602 m/s
Relative Velocity (W2): 59.8023022 m/s
Flow Angle (Beta2): -64.3483175 deg
Metal Angle (Beta2m): -60.0553209 deg
Absolute Mach Number (M2): 0.3054650
Relative Mach Number (M2r): 0.2348778
Diff. Outlet Velocity Triangle:
Meridional Velocity (Cm4): 18.7614290 m/s
Absolute Velocity Tangential (Cu4): 49.8048926 m/s
Absolute Velocity (C4): 53.2214106 m/s
Swirl Angle (Alpha 4): 69.3586810 deg
Absolute Mach Number (M4): 0.1680693
~~~~~~~~~~~~~~ NON-DIMENSIONAL DESIGN PARAMETERS ~~~~~~~~~~~~~
de Haller number: 1.1708520
Flow Factor: 0.2034485
Work Coefficient: 0.5763514
Flow Coefficient: 0.0373761
Rotational Mach Number: 0.4997746
*************************************************************
COMPRESSOR PRESSURE RATIO: 1.8184503
COMPRESSOR EFFICIENCY: 0.7426447
*************************************************************