#!/usr/bin/env python3
import math
import sys

import pycalculix as pyc
import matplotlib.pyplot as plt

# We'll be modeling a rotating jet engine part
model_name = 'compr-rotor'
model = pyc.FeaModel(model_name)
# this sets dist units to meters, labels our consistent units
model.set_units('m')

# set whether or not to show gui plots
show_gui = True
if '-nogui' in sys.argv:
    show_gui = False
# set element shape
eshape = 'quad'
if '-tri' in sys.argv:
    eshape = 'tri'

# problem + geometry constants
rpm = 1000     # rotor speed in rpm
rad_inner = 1
rad_flowpath = 3
disk_width = 1
disk_ht = 0.5
disk_angle = 45 # from horizontal, internal to disk
web_width = 0.2
arm_length = .5
arm_th = 0.05
airfoil_width = 0.4
airfoil_ht = 1
rad_disk_top = 0.1
rad_disk_bot = 0.1
rad_web_top = 0.1
rad_web_bot = 0.1

# derived dimensions
diskramp_ax = (disk_width - web_width)/2
diskramp_rad = math.tan(math.radians(disk_angle))*diskramp_ax
web_ht = rad_flowpath - arm_th - diskramp_rad - rad_inner
flowpath_ax = (web_width + 2*arm_length - airfoil_width) / 2.0

# these are deltas
disk_loop = [[disk_ht,0],[diskramp_rad,diskramp_ax],
             [web_ht,0,],[0,-arm_length],
             [arm_th,0],[0,flowpath_ax],
             [0,airfoil_width],[0,flowpath_ax],
             [-arm_th,0],[0,-arm_length],[-web_ht,0],
             [-diskramp_rad,diskramp_ax],
             [-disk_ht,0],[0,-disk_width]]
airfoil_loop = [[airfoil_ht,0],[0,airfoil_width],
                [-airfoil_ht,0],[0,-airfoil_width]]

# make part
part = pyc.Part(model)
part.goto(rad_inner,0)
lines = []
for [drad, dax] in disk_loop:
    [L, p1, p2] = part.draw_line_delta(drad, dax)
    lines.append(L)

# go to where we'll draw the airfoil
mypt = lines[6].pt(0) # first point of line 8
part.goto(mypt.x,mypt.y)
for [drad, dax] in airfoil_loop:
    part.draw_line_delta(drad, dax)

# fillets [[line1, line2, fillet_rad],[
fillet_list = [[0,13,rad_disk_bot],[12,13,rad_disk_bot],
               [0,1,rad_disk_top],[11,12,rad_disk_top],
               [1,2,rad_web_bot],[10,11,rad_web_bot],
               [2,3,rad_web_top],[9,10,rad_web_top]]
for [i1, i2, rad] in fillet_list:
    part.fillet_lines(lines[i1], lines[i2], rad)
# view the geometry
model.plot_geometry(model_name+'_geom', pnum=False, lnum=False,
                    display=show_gui)

# set loads and constraints
model.set_rpm(10000, part)
model.set_constr('fix',part.left,'y')

# set part material
mat = pyc.Material('nickel_alloy')
mat.set_mech_props(8220, 208*10**9, 0.3)
model.set_matl(mat, part)

# mesh model
model.set_eshape(eshape, 2)
model.set_etype('axisym', 'A0')
model.set_etype('plstress', 'A1', 0.1)
model.get_item('L15').set_ediv(8)
model.get_item('L6').set_ediv(8)
model.get_item('L2').set_ediv(24)
model.get_item('L10').set_ediv(24)
model.mesh(1.0, 'gmsh') # mesh with 1.0 fineness, smaller is finer
# plot the part elements
model.plot_elements(model_name+'_elem', display=show_gui)
model.plot_constraints(model_name+'_constr', display=show_gui)

# make and solve the model
prob = pyc.Problem(model, 'struct')
prob.solve()

# view the results
disp = False    # turn off display plotting
g = 0.0         # turn off adding results displacement to the model
fields = 'Sx,Sy,Sz,S1,S2,S3,Seqv,ux,uy,uz,utot' # fields to plot
fields = fields.split(',')
for field in fields:
    fname = model_name+'_'+field
    prob.rfile.nplot(field, fname, display=disp, gmult=g)

#!/usr/bin/env python3
import math
import sys

import pycalculix as pyc
import matplotlib.pyplot as plt

# We'll be modeling a rotating jet engine part
model_name = 'compr-rotor'
model = pyc.FeaModel(model_name)
# this sets dist units to meters, labels our consistent units
model.set_units('m')

# set whether or not to show gui plots
show_gui = True
if '-nogui' in sys.argv:
    show_gui = False
# set element shape
eshape = 'quad'
if '-tri' in sys.argv:
    eshape = 'tri'

# problem + geometry constants
rpm = 1000     # rotor speed in rpm
rad_inner = 1
rad_flowpath = 3
disk_width = 1
disk_ht = 0.5
disk_angle = 45 # from horizontal, internal to disk
web_width = 0.2
arm_length = .5
arm_th = 0.05
airfoil_width = 0.4
airfoil_ht = 1
rad_disk_top = 0.1
rad_disk_bot = 0.1
rad_web_top = 0.1
rad_web_bot = 0.1

# derived dimensions
diskramp_ax = (disk_width - web_width)/2
diskramp_rad = math.tan(math.radians(disk_angle))*diskramp_ax
web_ht = rad_flowpath - arm_th - diskramp_rad - rad_inner
flowpath_ax = (web_width + 2*arm_length - airfoil_width) / 2.0

# these are deltas
disk_loop = [[disk_ht,0],[diskramp_rad,diskramp_ax],
             [web_ht,0,],[0,-arm_length],
             [arm_th,0],[0,flowpath_ax],
             [0,airfoil_width],[0,flowpath_ax],
             [-arm_th,0],[0,-arm_length],[-web_ht,0],
             [-diskramp_rad,diskramp_ax],
             [-disk_ht,0],[0,-disk_width]]
airfoil_loop = [[airfoil_ht,0],[0,airfoil_width],
                [-airfoil_ht,0],[0,-airfoil_width]]

# make part
part = pyc.Part(model)
part.goto(rad_inner,0)
lines = []
for [drad, dax] in disk_loop:
    [L, p1, p2] = part.draw_line_delta(drad, dax)
    lines.append(L)

# go to where we'll draw the airfoil
mypt = lines[6].pt(0) # first point of line 8
part.goto(mypt.x,mypt.y)
for [drad, dax] in airfoil_loop:
    part.draw_line_delta(drad, dax)

# fillets [[line1, line2, fillet_rad],[
fillet_list = [[0,13,rad_disk_bot],[12,13,rad_disk_bot],
               [0,1,rad_disk_top],[11,12,rad_disk_top],
               [1,2,rad_web_bot],[10,11,rad_web_bot],
               [2,3,rad_web_top],[9,10,rad_web_top]]
for [i1, i2, rad] in fillet_list:
    part.fillet_lines(lines[i1], lines[i2], rad)
# view the geometry
model.plot_geometry(model_name+'_geom', pnum=False, lnum=False,
                    display=show_gui)

# set loads and constraints
model.set_rpm(10000, part)
model.set_constr('fix',part.left,'y')

# set part material
mat = pyc.Material('nickel_alloy')
mat.set_mech_props(8220, 208*10**9, 0.3)
model.set_matl(mat, part)

# mesh model
model.set_eshape(eshape, 2)
model.set_etype('axisym', 'A0')
model.set_etype('plstress', 'A1', 0.1)
model.get_item('L15').set_ediv(8)
model.get_item('L6').set_ediv(8)
model.get_item('L2').set_ediv(24)
model.get_item('L10').set_ediv(24)
model.mesh(1.0, 'gmsh') # mesh with 1.0 fineness, smaller is finer
# plot the part elements
model.plot_elements(model_name+'_elem', display=show_gui)
model.plot_constraints(model_name+'_constr', display=show_gui)

# make and solve the model
prob = pyc.Problem(model, 'struct')
prob.solve()

# view the results
disp = False    # turn off display plotting
g = 0.0         # turn off adding results displacement to the model
fields = 'Sx,Sy,Sz,S1,S2,S3,Seqv,ux,uy,uz,utot' # fields to plot
fields = fields.split(',')
for field in fields:
    fname = model_name+'_'+field
    prob.rfile.nplot(field, fname, display=disp, gmult=g)

#!/usr/bin/env python3 # We'll be modeling a rotating jet engine part # this sets dist units to meters, labels our consistent units # set whether or not to show gui plots # set element shape # problem + geometry constants # rotor speed in rpm # from horizontal, internal to disk # derived dimensions # these are deltas # make part # go to where we'll draw the airfoil # first point of line 8 # fillets [[line1, line2, fillet_rad],[ # view the geometry # set loads and constraints # set part material # mesh model # mesh with 1.0 fineness, smaller is finer # plot the part elements # make and solve the model # view the results # turn off display plotting # turn off adding results displacement to the model # fields to plot