There are two ways of using this code.
- If you need to design from scratch.
- If you already have a design
Designing from Scratch - Building the 2D geometry which will later be used to build the 3D Blade. The code below shows how to construct a stator
import numpy as np
from pyturbo.aero import *
from pyturbo.helper import *
stator_hub = airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58) # This creates the camberline
stator_hub.le_thickness_add(0.04)
ps_height = [0.0500,0.0200,-0.0100]
ps_height_loc = exp_ratio(1.2,len(ps_height)+2,0.95)
ps_height_loc = np.append(ps_height_loc,[1])
stator_hub.ps_thickness_add(thicknessArray=ps_height,expansion_ratio=1.2)
ss_height=[0.2400, 0.2000, 0.1600, 0.1400]
stator_hub.ss_thickness_add(thicknessArray=ss_height,camberPercent=0.8,expansion_ratio=1.2)
stator_hub.le_thickness_match()
stator_hub.te_create(radius=0.001,wedge_ss=2.5,wedge_ps=2.4)
stator_hub.flow_guidance2(10)
Below is the camberline plotted by calling.
stator_hub.plot_camber()
Subsequently the design blade geometry with control points are plotted
stator_hub.plot2D()
Second derivative for both suction and pressure sides
stator_hub.plot_derivative2()
Plot of the stator with pitch to chord of 0.75
stator_hub.plot2D_channel(0.75)
