Adding Modules

1. Click Select Modules in the Model Panel. The Physical Model Selection dialog box opens.
2. Select Centrifugal under Available Modules and click Add.
3. Select Cavitation under Available Modules and click Add.

4. Click Close to close the Physical Model Selection dialog box.
   

General Operating Parameters

1. Select Centrifugal in the Model Panel.
2. Enter Number of Revolutions and Time Steps Per Pocket Rotation as 4 and 180 respectively for the Time Definition in the Model Tab of Properties Panel.
3. Enter Number of Blades as 2 under Pump Configuration.

4. Enter the parameters for the Angular Velocity Definition as follows:

   • Rotational Direction: Counterclockwise

   • Rotational Speed: 4000 rpm

   • Rotational Axis Vector: 1,0,0

The boundary conditions are specified as follows:

Inlet

1. Select oilgallery_inlet from the Boundaries list under Volumes in the Geometric Entities Panel.
2. Select Inlet from the Centrifugal drop-down list in the Model Tab of Properties Panel.
3. Select Specified Pressure Inlet from the Flow drop-down list in the Model Tab of Properties Panel.
4. Enter Inlet Pressure as 600000 Pa.
5. Enter Gas Mass Fraction as 9e-05.

Outlet

1. Select  conrod_outlet_d, conrod_outlet_u, mb_outlet_d and mb_outlet_u from the Boundaries list in the Geometric Entities Panel.

2. Select Outlet from the Centrifugal drop-down list in the Model Tab of Properties Panel.
3. Select Specified Pressure Outlet from the Flow drop-down list in the Model Tab of Properties Panel.
4. Enter Pressure as 101325 Pa.
5. Enter Gas Mass Fraction as 0.013066.

Fluid Properties

1. Select Volumes in the Geometric Entities Panel.
2. Select Model Tab in the Properties Panel.

3. Enter the parameters for Property list as follows:

   • Material: Oil
   • Dynamic Viscosity: 0.007 Pa-s
   • Density: 800 kg/m³
   • Liquid Bulk Modulus(B0): 1.5e09 Pa
   • Liquid Reference Pressure: 101325 Pa
   • Saturation Pressure: 400 Pa

4. Enter the parameters for Cavitation list as follows:

   • Gas Schmidt Number: Constant
   • Value: 1
   • Cavitation Property: Properties
   • Gas Molecular Weight: 28.97
   • Vapour Molecular Weight: 300

5. Enter the Value for Initial Condition for Flow Module as follows:

   • Pressure: 600000 Pa

6. Enter the Value for Initial Condition for Cavitation Module as follows:

   • Gas Mass Fraction: 9e-05

Global Expression

1. Click Edit Expression icon on the View Toolbar to open the Expression Editor dialog box.
2. Copy and paste the expressions written under Description drop-down list for Global Expressions, see Figure 7.158.
   
Description

#myvector=[10,0,0]

#display.myvector=myvector

#display.angle = atan2(z-0.1075,y)*180/pi

#

#================================================================================

# Global Data for Main Bearings and Conrod bearings --Distorted Surface Model

# ================================================================================

#----------------------------------------------------------------

# 1. Constants and Parameters

#----------------------------------------------------------------

halfpi=pi*0.5

twopi=2*pi

thirdpi=pi/3

quatpi=pi/4

quat3pi = 3*pi/4

sixthpi=pi/6

twothirdpi = 2*thirdpi

r2d = 180/pi

n2o=2*pi/60

#----------------------------------------------------------------

#2. Input Data and Operating Conditions:

#----------------------------------------------------------------

# center of rotation of main bearings

rotationCenter= [0, 0, 0]

#Rotation axis of main bearings

rotationAxis = [1,0,0]

# Vertical axis :"Axis bisecting the V angle or axis parallel to cylinder axis" in case of inline cylinders

V_Axis = [0,1,0]

# Horizontal axis

H_Axis = V_Axis^rotationAxis

#cylinder offset for inline engines in meter from vertical axis

delta = 0 # zero(0) for V-cylinder engines

#Cylinder axis angle from Horizontal axis for bank 1 and bank 2

#For V-12 cylinders with V angle 60 degree

alpha1 = pi/2 #Bank 1

alpha2 = pi/2 #Bank 2

#Engine rotation in rpm (absolute)

rpm = 4000

n = 1 # for clockwise rotation n = 2 and counterclockwise n =1

bank_angle = 0 # angle between two banks (V-angle), positive if orientation(bank1 to bank 2) is along the direction of rotation; negative if opposite to the direction of rotation equals zero(0) for inline cylinder engines

no_of_cylinders = 1

#firing interval angle: crank angle rotation between two successive firing;

firing_interval_angle = 4*pi/no_of_cylinders

#Engine cylinder firing order

#12-9-10-5-6-1-2-3-4-7-8-11

ref_cyl_no = 1 # 1st fired cylinder number

theta_ref = -pi/2 # initial angular position of the conrod bearing for the 1st fired cylinder from the Horizontal Axis

#Firing order positon of cylinders

#Default value is ‘ref_cyl_no’ if cylinders are absent

cyl_1 = 1 # Here cylinder 1 is the 1st fired cylinder

cyl_2 = 3 # Cylinder 2 fires at 3rd position

cyl_3 = 5

cyl_4 = 2

cyl_5 = 4

cyl_6 = 6

cyl_7 = ref_cyl_no #Default value ‘ref_cyl_no’, change the position value if you have cyl_7

cyl_8 = ref_cyl_no #Default value ‘ref_cyl_no’, change the position value if you have cyl_8

cyl_9 = ref_cyl_no

cyl_10 = ref_cyl_no

cyl_11 = ref_cyl_no

cyl_12 = ref_cyl_no

#main bearing inner/outer radius (m)

mbri = 0.025

mbro = 0.0250315

#conrod bearing inner/outer radius (m)

conri=0.0235

conro=0.0235305

#crankshaft radius(m)

rc=0.0442

#conrod length(m)

cl=0.137

#ratio of rc over cl

rrc=rc/cl

#minimum clearance (micron)

epsmin=3e-6

# magnifying factor for viewing purpose, has to be 1 for solving fluid flow

magnifier = 1

range = 3 # range to determine where the mesh need to be moved

#convert time to total rotating angle

t2d = time*rpm*6

#crank angle to read in the eccentricity

crAngle = mod(t2d,720)

# main bearing orbiting distances (get from table with angle in degree, and (y,z) in mm)

m1H = table("Mainbearing_orbit_z.txt", crAngle)/1000

m1V = table("Mainbearing_orbit_y.txt", crAngle)/1000

#m2H = table("main_2_y.txt", crAngle)/1000

#m2V = table("main_2_z.txt", crAngle)/1000

#m3H = table("main_1_y.txt", crAngle)/1000

#m3V = table("main_1_z.txt", crAngle)/1000

#m4H = table("main_2_y.txt", crAngle)/1000

#m4V = table("main_2_z.txt", crAngle)/1000

#m5H = table("main_1_y.txt", crAngle)/1000

#m5V = table("main_1_z.txt", crAngle)/1000

#m6H = table("main_2_y.txt", crAngle)/1000

#m6V = table("main_2_z.txt", crAngle)/1000

#m7H = table("main_1_y.txt", crAngle)/1000

#m7V = table("main_1_z.txt", crAngle)/1000

#************************DO NOT CHANGE THESE CALCULATIONS BELOW************************

omega =-1*((-1)^n)*rpm*n2o

omegav = omega*rotationAxis

omt=time*omega

# Initial angular position of the conrod bearings

theta1_0 = theta_ref + ((-1)^n)* ((cyl_1- ref_cyl_no)* firing_interval_angle)

#theta2_0 = theta_ref + ((-1)^n)* ((cyl_2- ref_cyl_no)* firing_interval_angle - bank_angle)

#theta3_0 = theta_ref + ((-1)^n)* ((cyl_3- ref_cyl_no)* firing_interval_angle)

#theta4_0 = theta_ref + ((-1)^n)* ((cyl_4- ref_cyl_no)* firing_interval_angle - bank_angle)

#theta5_0 = theta_ref + ((-1)^n)* ((cyl_5- ref_cyl_no)* firing_interval_angle)

#theta6_0 = theta_ref + ((-1)^n)* ((cyl_6- ref_cyl_no)* firing_interval_angle - bank_angle)

#theta7_0 = theta_ref + ((-1)^n)* ((cyl_7- ref_cyl_no)* firing_interval_angle)

#theta8_0 = theta_ref + ((-1)^n)* ((cyl_8- ref_cyl_no)* firing_interval_angle - bank_angle)

#theta9_0 = theta_ref + ((-1)^n)* ((cyl_9- ref_cyl_no)* firing_interval_angle)

#theta10_0 = theta_ref + ((-1)^n)* ((cyl_10- ref_cyl_no)* firing_interval_angle - bank_angle)

#theta11_0 = theta_ref + ((-1)^n)* ((cyl_11- ref_cyl_no)* firing_interval_angle)

#theta12_0 = theta_ref + ((-1)^n)* ((cyl_12- ref_cyl_no)* firing_interval_angle - bank_angle)

# the theta's dictate the instantaneous angular position of the conrod bearing w.r.t. Horizontal axis

theta1 = theta1_0 + omt

#theta2 = theta2_0 + omt

#theta3 = theta3_0 + omt

#theta4 = theta4_0 + omt

#theta5 = theta5_0 + omt

#theta6 = theta6_0 + omt

#theta7 = theta7_0 + omt

#theta8 = theta8_0 + omt

#theta9 = theta9_0 + omt

#theta10 = theta10_0 + omt

#theta11 = theta11_0 + omt

#theta12 = theta12_0 + omt

#************************DO NOT CHANGE THESE CALCULATIONS ABOVE************************

# conrod bearing orbiting distances (get from table with angle in degree, and (y,z) in mm)

rod1H = table("Conrodbearing_orbit_z.txt", mod((theta1*r2d),720))/1000

rod1V = table("Conrodbearing_orbit_y.txt", mod((theta1*r2d),720))/1000

#rod2H = table("conrod_y.txt", mod((theta2*r2d),720))/1000

#rod2V = table("conrod_z.txt", mod((theta2*r2d),720))/1000

#rod3H = table("conrod_y.txt", mod((theta3*r2d),720))/1000

#rod3V = table("conrod_z.txt", mod((theta3*r2d),720))/1000

#rod4H = table("conrod_y.txt", mod((theta4*r2d),720))/1000

#rod4V = table("conrod_z.txt", mod((theta4*r2d),720))/1000

#rod5H = table("conrod_y.txt", mod((theta5*r2d),720))/1000

#rod5V = table("conrod_z.txt", mod((theta5*r2d),720))/1000

#rod6H = table("conrod_y.txt", mod((theta6*r2d),720))/1000

#rod6V = table("conrod_z.txt", mod((theta6*r2d),720))/1000

#rod7H = table("conrod_y.txt", mod((theta7*r2d),720))/1000

#rod7V = table("conrod_z.txt", mod((theta7*r2d),720))/1000

#rod8H = table("conrod_y.txt", mod((theta8*r2d),720))/1000

#rod8V = table("conrod_z.txt", mod((theta8*r2d),720))/1000

#rod9H = table("conrod_y.txt", mod((theta9*r2d),720))/1000

#rod9V = table("conrod_z.txt", mod((theta9*r2d),720))/1000

#rod10H = table("conrod_y.txt", mod((theta10*r2d),720))/1000

#rod10V = table("conrod_z.txt", mod((theta10*r2d),720))/1000

#rod11H = table("conrod_y.txt", mod((theta11*r2d),720))/1000

#rod11V = table("conrod_z.txt", mod((theta11*r2d),720))/1000

#rod12H = table("conrod_y.txt", mod((theta12*r2d),720))/1000

#rod12V = table("conrod_z.txt", mod((theta12*r2d),720))/1000

#======================================================================

#************** DO NOT CHANGE ANYTHING BELOW THIS LINE ****************

#======================================================================

#3. Calculations

#----------------------------------------------------------------

cl2=cl*cl

#the gamma’s dictate the instantaneous angular position of the conrod bearing w.r.t. Cylinder axis

gamma1 = theta1 - alpha1

#gamma2 = theta2 - alpha2

#gamma3 = theta3 - alpha1

#gamma4 = theta4 - alpha2

#gamma5 = theta5 - alpha1

#gamma6 = theta6 - alpha2

#gamma7 = theta7 - alpha1

#gamma8 = theta8 - alpha2

#gamma9 = theta9 - alpha1

#gamma10 = theta10 - alpha2

#gamma11 = theta11 - alpha1

#gamma12 = theta12 - alpha2

gammai1 = theta_ref - alpha1

#gammai2 = theta20 - alpha2

#gammai3 = theta30 - alpha1

#gammai4 = theta40 - alpha2

#gammai5 = theta50 - alpha1

#gammai6 = theta60 - alpha2

#gammai7 = theta70 - alpha1

#gammai8 = theta80 - alpha2

#gammai9 = theta90 - alpha1

#gammai10 = theta100 - alpha2

#gammai11 = theta110 - alpha1

#gammai12 = theta120 - alpha2

# Distance along the cylinder axis

rr1=rc*cos(gamma1)

#rr2=rc*cos(gamma2)

#rr3=rc*cos(gamma3)

#rr4=rc*cos(gamma4)

#rr5=rc*cos(gamma5)

#rr6=rc*cos(gamma6)

#rr7=rc*cos(gamma7)

#rr8=rc*cos(gamma8)

#rr9=rc*cos(gamma9)

#rr10=rc*cos(gamma10)

#rr11=rc*cos(gamma11)

#rr12=rc*cos(gamma12)

rp1 = rr1+(cl2-(rc*sin(gamma1)-delta)^2)^0.5

#rp2 = rr2+(cl2-(rc*sin(gamma2)-delta)^2)^0.5

#rp3 = rr3+(cl2-(rc*sin(gamma3)-delta)^2)^0.5

#rp4 = rr4+(cl2-(rc*sin(gamma4)-delta)^2)^0.5

#rp5 = rr5+(cl2-(rc*sin(gamma5)-delta)^2)^0.5

#rp6 = rr6+(cl2-(rc*sin(gamma6)-delta)^2)^0.5

#rp7 = rr7+(cl2-(rc*sin(gamma7)-delta)^2)^0.5

#rp8 = rr8+(cl2-(rc*sin(gamma8)-delta)^2)^0.5

#rp9 = rr9+(cl2-(rc*sin(gamma9)-delta)^2)^0.5

#rp10 = rr10+(cl2-(rc*sin(gamma10)-delta)^2)^0.5

#rp11 = rr11+(cl2-(rc*sin(gamma11)-delta)^2)^0.5

#rp12 = rr12+(cl2-(rc*sin(gamma12)-delta)^2)^0.5

#Ratio of Crank radius projection to Connecting rod projection

pr_ratio1 = rr1/(rr1-rp1)

#pr_ratio2 = rr2/(rr2-rp2)

#pr_ratio3 = rr3/(rr3-rp3)

#pr_ratio4 = rr4/(rr4-rp4)

#pr_ratio5 = rr5/(rr5-rp5)

#pr_ratio6 = rr6/(rr6-rp6)

#pr_ratio7 = rr7/(rr7-rp7)

#pr_ratio8 = rr8/(rr8-rp8)

#pr_ratio9 = rr9/(rr9-rp9)

#pr_ratio10 = rr10/(rr10-rp10)

#pr_ratio11 = rr11/(rr11-rp11)

#pr_ratio12 = rr12/(rr12-rp12)

#connecting rod angle with the cylinder axis

alphaP1 = -atan((rc*sin(gamma1)-delta)/(rp1-rr1))

#alphaP2 = -atan((rc*sin(gamma2)-delta)/(rp2-rr2))

#alphaP3 = -atan((rc*sin(gamma3)-delta)/(rp3-rr3))

#alphaP4 = -atan((rc*sin(gamma4)-delta)/(rp4-rr4))

#alphaP5 = -atan((rc*sin(gamma5)-delta)/(rp5-rr5))

#alphaP6 = -atan((rc*sin(gamma6)-delta)/(rp6-rr6))

#alphaP7 = -atan((rc*sin(gamma7)-delta)/(rp7-rr7))

#alphaP8 = -atan((rc*sin(gamma8)-delta)/(rp8-rr8))

#alphaP9 = -atan((rc*sin(gamma9)-delta)/(rp9-rr9))

#alphaP10 = -atan((rc*sin(gamma10)-delta)/(rp10-rr10))

#alphaP11 = -atan((rc*sin(gamma11)-delta)/(rp11-rr11))

#alphaP12 = -atan((rc*sin(gamma12)-delta)/(rp12-rr12))

#conrod-piston angle

delta1 =-asin(rrc*sin(gamma1))

#delta2 =-asin(rrc*sin(gamma2))

#delta3 =-asin(rrc*sin(gamma3))

#delta4 =-asin(rrc*sin(gamma4))

#delta5 =-asin(rrc*sin(gamma5))

#delta6 =-asin(rrc*sin(gamma6))

#delta7 =-asin(rrc*sin(gamma7))

#delta8 =-asin(rrc*sin(gamma8))

#delta9 =-asin(rrc*sin(gamma9))

#delta10 =-asin(rrc*sin(gamma10))

#delta11 =-asin(rrc*sin(gamma11))

#delta12 =-asin(rrc*sin(gamma12))

deltai1 =-asin(rrc*sin(gammai1))

#deltai2 =-asin(rrc*sin(gammai2))

#deltai3 =-asin(rrc*sin(gammai3))

#deltai4 =-asin(rrc*sin(gammai4))

#deltai5 =-asin(rrc*sin(gammai5))

#deltai6 =-asin(rrc*sin(gammai6))

#deltai7 =-asin(rrc*sin(gammai7))

#deltai8 =-asin(rrc*sin(gammai8))

#deltai9 =-asin(rrc*sin(gammai9))

#deltai10 =-asin(rrc*sin(gammai10))

#deltai11 =-asin(rrc*sin(gammai11))

#deltai12 =-asin(rrc*sin(gammai12))

beta1 =delta1-deltai1

#beta2 =delta2-deltai2

#beta3 =delta3-deltai3

#beta4 =delta4-deltai4

#beta5 =delta5-deltai5

#beta6 =delta6-deltai6

#beta7 =delta7-deltai7

#beta8 =delta8-deltai8

#beta9 =delta9-deltai9

#beta10 =delta10-deltai10

#beta11 =delta11-deltai11

#beta12 =delta12-deltai12

# Conrod center position

cc1 = rc*cos(theta1)*H_Axis + rc*sin(theta1)*V_Axis

#cc2 = rc*cos(theta2)*H_Axis + rc*sin(theta2)*V_Axis

#cc3 = rc*cos(theta3)*H_Axis + rc*sin(theta3)*V_Axis

#cc4 = rc*cos(theta4)*H_Axis + rc*sin(theta4)*V_Axis

#cc5 = rc*cos(theta5)*H_Axis + rc*sin(theta5)*V_Axis

#cc6 = rc*cos(theta6)*H_Axis + rc*sin(theta6)*V_Axis

#cc7 = rc*cos(theta7)*H_Axis + rc*sin(theta7)*V_Axis

#cc8 = rc*cos(theta8)*H_Axis + rc*sin(theta8)*V_Axis

#cc9 = rc*cos(theta9)*H_Axis + rc*sin(theta9)*V_Axis

#cc10 = rc*cos(theta10)*H_Axis + rc*sin(theta10)*V_Axis

#cc11 = rc*cos(theta11)*H_Axis + rc*sin(theta11)*V_Axis

#cc12 = rc*cos(theta12)*H_Axis + rc*sin(theta12)*V_Axis

# Conrod initial center position

cci1 = rc*cos(theta_ref)*H_Axis + rc*sin(theta_ref)*V_Axis

#cci2 = rc*cos(theta20)*H_Axis + rc*sin(theta20)*V_Axis

#cci3 = rc*cos(theta30)*H_Axis + rc*sin(theta30)*V_Axis

#cci4 = rc*cos(theta40)*H_Axis + rc*sin(theta40)*V_Axis

#cci5 = rc*cos(theta50)*H_Axis + rc*sin(theta50)*V_Axis

#cci6 = rc*cos(theta60)*H_Axis + rc*sin(theta60)*V_Axis

#cci7 = rc*cos(theta70)*H_Axis + rc*sin(theta70)*V_Axis

#cci8 = rc*cos(theta80)*H_Axis + rc*sin(theta80)*V_Axis

#cci9 = rc*cos(theta90)*H_Axis + rc*sin(theta90)*V_Axis

#cci10 = rc*cos(theta100)*H_Axis + rc*sin(theta100)*V_Axis

#cci11 = rc*cos(theta110)*H_Axis + rc*sin(theta110)*V_Axis

#cci12 = rc*cos(theta120)*H_Axis + rc*sin(theta120)*V_Axis

dummy_axis = [1,1,1]

#Main bearing orbiting

m1 = (m1H*H_Axis/(H_Axis&dummy_axis)+m1V*V_Axis/(V_Axis&dummy_axis))*magnifier

#m2 = (m2H*H_Axis/(H_Axis&dummy_axis)+m2V*V_Axis/(V_Axis&dummy_axis))*magnifier

#m3 = (m3H*H_Axis/(H_Axis&dummy_axis)+m3V*V_Axis/(V_Axis&dummy_axis))*magnifier

#m4 = (m4H*H_Axis/(H_Axis&dummy_axis)+m4V*V_Axis/(V_Axis&dummy_axis))*magnifier

#m5 = (m5H*H_Axis/(H_Axis&dummy_axis)+m5V*V_Axis/(V_Axis&dummy_axis))*magnifier

#m6 = (m6H*H_Axis/(H_Axis&dummy_axis)+m6V*V_Axis/(V_Axis&dummy_axis))*magnifier

#m7 = (m7H*H_Axis/(H_Axis&dummy_axis)+m7V*V_Axis/(V_Axis&dummy_axis))*magnifier

#Conrod bearing orbiting

rod1 = (rod1H*H_Axis/(H_Axis&dummy_axis) + rod1V*V_Axis/(V_Axis&dummy_axis))*magnifier

#rod2 = (rod2H*H_Axis/(H_Axis&dummy_axis) + rod2V*V_Axis/(V_Axis&dummy_axis))*magnifier

#rod3 = (rod3H*H_Axis/(H_Axis&dummy_axis) + rod3V*V_Axis/(V_Axis&dummy_axis))*magnifier

#rod4 = (rod4H*H_Axis/(H_Axis&dummy_axis) + rod4V*V_Axis/(V_Axis&dummy_axis))*magnifier

#rod5 = (rod5H*H_Axis/(H_Axis&dummy_axis) + rod5V*V_Axis/(V_Axis&dummy_axis))*magnifier

#rod6 = (rod6H*H_Axis/(H_Axis&dummy_axis) + rod6V*V_Axis/(V_Axis&dummy_axis))*magnifier

#rod7 = (rod7H*H_Axis/(H_Axis&dummy_axis) + rod7V*V_Axis/(V_Axis&dummy_axis))*magnifier

#rod8 = (rod8H*H_Axis/(H_Axis&dummy_axis) + rod8V*V_Axis/(V_Axis&dummy_axis))*magnifier

#rod9 = (rod9H*H_Axis/(H_Axis&dummy_axis) + rod9V*V_Axis/(V_Axis&dummy_axis))*magnifier

#rod10 = (rod10H*H_Axis/(H_Axis&dummy_axis) + rod10V*V_Axis/(V_Axis&dummy_axis))*magnifier

#rod11 = (rod11H*H_Axis/(H_Axis&dummy_axis) + rod11V*V_Axis/(V_Axis&dummy_axis))*magnifier

#rod12 = (rod12H*H_Axis/(H_Axis&dummy_axis) + rod12V*V_Axis/(V_Axis&dummy_axis))*magnifier

 

3. Click OK to close the Expression Editor dialog box.

Conrod Local Expression

1. Select conrod Volume in the Geometric Entities Panel.

2. Select Volume Remesh under dropdown list in the Model Tab of Properties Panel.

3. Select Expression under Method dropdown list.
4. Enter the coordnew.x, coordnew.y, coordnew.z for X, Y, Z respectively.
5. Click Edit Expression icon under Coordinates to open the Expression Editor dialog box.
6. Copy and paste the expressions written under Description drop-down list for Local Expressions, see Figure 7.159.
   
Description

#====================================================

# Conrod 1 bearing local variables CB1 -- remesh

# ===================================================

#initial center coordinates

cc0 = cci1

beta = alpha1 + alphaP1 #if conrod1 belongs to Bank 1

loc = m1+ cc1-rod1 #if conrod2 belongs to main bearing 1

mdv = rod1

#========================================================================================

#************** DO NOT CHANGE ANYTHING EXCEPT FILE NAME BELOW THIS LINE ****************

#========================================================================================

#bearing inner and outer radius

ri = conri

ro =conro

dr = ro - ri

# assumption: The original mesh is a concentric circular ring

dc = coord - cc0

dH = dc&H_Axis

dV = dc&V_Axis

drp2 = dH*dH+dV*dV

drp=drp2^0.5

r_ratio = (drp-ri)/dr

pangle=mod(atan2(dV,dH)+twopi, twopi)

#new position angle due to conrod rotation

anew = pangle + beta

#assume mesh rotate with inner shell

aout = pangle*r2d #deg

#mapping with the provided table convention

aout_mod = (aout>0)? mod(aout, 360) : 360 - mod(-aout, 360)

rin = ri

# text file unit is mm

rout_tmp1 = table("Conrodbearing_distorted.txt", aout_mod)/1000 #File unit is in mm

#rout_tmp1 = ro

rout = rin + (rout_tmp1-rin)*magnifier

cosanew = cos(anew)

sinanew = sin(anew)

a = cosanew*H_Axis+sinanew*V_Axis

# calculate inner radius which changes due to both rod orbiting and MB orbiting

md = len(mdv)+1e-30

md2 = md^2

adotmd=a&mdv

cosalpha=adotmd/md

bb =md*cosalpha

cc = rin^2-md2

rin_tmp1 = bb + sqrt(bb^2 + cc)

rin_tmp = rin_tmp1<(rout - epsmin)?rin_tmp1:(rout-epsmin)

rnew = rin_tmp + (rout-rin_tmp)*r_ratio

# rotation + main bearing orbiting + outer shell reverse conrod orbiting

coordnew = rnew*a+ loc + (coord&rotationAxis)*rotationAxis

 

7. Click OK to close the Expression Editor dialog box.

Crossdrill Local Expression

1. Select crossdrill Volume in the Geometric Entities Panel.

2. Select Volume Remesh under dropdown list in the Model Tab of Properties Panel.

3. Select Translation under Method dropdown list.
4. Enter the m1.x, m1.y, m1.z for X, Y, Z values respectively.

Groove Local Expression

1. Select groove Volume in the Geometric Entities Panel.

2. Select Volume Remesh under dropdown list in the Model Tab of Properties Panel.

3. Select Expression under Method dropdown list.
4. Enter the coordnew.x, coordnew.y, coordnew.z for X, Y, Z values respectively.
5. Click Edit Expression icon under Coordinates to open the Expression Editor dialog box.
6. Copy and paste the expressions written under Description drop-down list for Local Expressions, see Figure 7.161.
   
Description

#====================================================

# Groove local variables -- remesh

# ===================================================

#==============================================

#************** DO NOT CHANGE ANYTHING EXCEPT FILE NAME BELOW THIS LINE ****************

#==============================================

#bearing inner and outer radius

ri = mbri

ro = mbro

dr = (ro-ri)*magnifier*range

ronew = ro+dr

# assumption: The original mesh is a concentrical circular ring

dc = coord-rotationCenter

dH = dc&H_Axis

dV = dc&V_Axis

drp2 = dH*dH+dV*dV

drp=drp2^0.5

r_ratio1 = (ronew-drp)/dr

r_ratio=(r_ratio1>0) ? ((r_ratio1<1)? r_ratio1 : 1 ) : 0

pangle=mod( atan2(dV,dH)+twopi , twopi )

aout = (pangle+halfpi)*r2d

aout_mod =(aout>0)? mod(aout, 360) : 360 - mod(-aout, 360)

rin = ri

rout1 = table("Mainbearing_distorted.txt", aout_mod)/1000 #File unit is in mm

rout=rin+(rout1-rin)*magnifier

rnew = drp + (rout-ro)*r_ratio

coordnew = rnew*cos(pangle)*H_Axis+rnew*sin(pangle)*V_Axis +(coord&rotationAxis)*rotationAxis

 

7. Click OK to close the Expression Editor dialog box.

Shaft Bearing Local Expression

1. Select mb Volume in the Geometric Entities Panel.

2. Select Volume Remesh under dropdown list in the Model Tab of Properties Panel.

3. Select Expression under Method dropdown list.
4. Enter the coordnew.x, coordnew.y, coordnew.z for X, Y, Z values respectively.
5. Click Edit Expression icon under Coordinates to open the Expression Editor dialog box.
6. Copy and paste the expressions written under Description drop-down list for Local Expressions, see Figure 7.162.
   
Description

#====================================================

# Main bearing local variables -- remesh

# ===================================================

orb = m1

#==============================================

#************** DO NOT CHANGE ANYTHING EXCEPT FILE NAME BELOW THIS LINE ****************

#==============================================

#bearing inner and outer radius

ri = mbri

ro = mbro

dr = ro - ri

# assumption: The original mesh is a concentrical circular ring

dc = coord-rotationCenter

dH = dc&H_Axis

dV = dc&V_Axis

drp2 = dH*dH+dV*dV

drp=drp2^0.5

r_ratio = (drp-ri)/dr

pangle=mod( atan2(dV,dH)+twopi , twopi )

aout = (pangle+halfpi)*r2d

aout_mod =(aout>0)? mod(aout, 360) : 360 - mod(-aout, 360)

rin = ri

rout1 = table("Mainbearing_distorted.txt", aout_mod)/1000 #File unit is in mm

rout=rin+(rout1-rin)*magnifier

# calculate inner radius considering orbiting of the inner surface (still a circle), to get

# more orthogonal mesh

aa = drp2

bb = dc&orb

cc = rin^2-(orb.y^2 +orb.x^2+orb.z^2)

rin1 = (bb + (bb^2 + aa*cc)^0.5)/drp

dr1=rout-rin1

rin2=(dr1<epsmin)?rout-epsmin:rin1

rnew = rin2 + (rout-rin2)*r_ratio

coordnew = rnew*cos(pangle)*H_Axis+rnew*sin(pangle)*V_Axis+(coord&rotationAxis)*rotationAxis

 

7. Click OK to close the Expression Editor dialog box.

Conrod outer velocity

1. Select conrod_outer from Boundaries list in the Geometric Entities Panel.
2. Select Cartesian from the Options drop-down list for the Flow module in the Model Tab of Properties Panel.
3. Enter u1, u2 and u3 for Velocity under X, Y, Z respectively.
4. Click Edit Expression icon to open the Expression Editor dialog box.
5. Copy and paste the expressions written under Description drop-down list for Local Expressions, see Figure 7.163.
   Description

    

   #conrod rotating rate

   omegac=omega*rr1/(rr1-rp1)

   omegacv = omegac*rotationAxis

   #bearing center velocity

   vc = omegav^cc1

   #velocity at point (x,z) on the bearing

   v = vc+ omegacv^(coord-cc1)

   u1=v.x

   u2=v.y

   u3=v.z

6. Click OK to close the Expression Editor dialog box.