Get the Turbofan beta merged

Turbofan/Turbofan.mdl.py

@@ -0,0 +1,230 @@
+from openmdao.main.api import Assembly, Component
+from openmdao.lib.drivers.api import DOEdriver
+from openmdao.lib.doegenerators.api import FullFactorial
+from openmdao.lib.casehandlers.api import DumpCaseRecorder
+from openmdao.lib.datatypes.api import Float
+from openmdao.lib.drivers.api import BroydenSolver
+
+from pycycle.api import (FlightConditions, Inlet, SplitterBPR, CompressorRline, Duct,
+    Burner, TurbinePRmap, NozzleConvergent, Shaft, Nmech, FlowStationVar)
+
+class Turbofan(Assembly): 
+
+   def configure(self):
+
+        #component definition
+        fc = self.add('fc', FlightConditions())
+        fc.alt = 34000
+        fc.MN = .8
+        fc.Wout = 674.2
+
+        inlet = self.add('inlet', Inlet() )
+        inlet.ram_recovery = .995
+
+        fan = self.add('fan', CompressorRline())
+        fan.eff = .867
+        fan.PR = 1.645
+
+        split = self.add( 'split', SplitterBPR())
+        split.BPR = 5.041
+
+        bypduct = self.add( 'bypduct', Duct())
+        bypduct.dPqP = .01
+
+        bypnoz = self.add( 'bypnoz', NozzleConvergent())
+        bypnoz.cfg = .9962
+        self.connect('fc.Fl_O.Ps', 'bypnoz.PsExh')       
+
+        duct1 = self.add( 'duct1', Duct())
+        duct1.dPqP = .0025
+
+        lpc = self.add( 'lpc', CompressorRline())
+        lpc.eff = .868
+        lpc.PR = 2.488       
+
+        duct2 = self.add( 'duct2', Duct())
+        duct2.dPqP = .0025
+
+        hpc = self.add( 'hpc', CompressorRline())
+        hpc.eff = .865
+        hpc.PR = 5.609 
+        hpc.Wfrac1=.055
+        hpc.hfrac1=1
+        hpc.Pfrac1=1
+        hpc.Wfrac2=.035
+        hpc.hfrac2=1
+        hpc.Pfrac2=1
+
+
+        burner = self.add( 'burner', Burner())
+        burner.ID_fuel = 3
+        burner.hFuel = -1200
+        burner.Wfuel = 1.899
+        burner.dPqP = .055
+
+
+        hpt = self.add( 'hpt', TurbinePRmap())
+        hpt.eff = .9133
+        hpt.PR = 2.670
+
+        duct3 = self.add( 'duct3', Duct())
+        duct3.dPqP = .005
+
+        lpt = self.add( 'lpt', TurbinePRmap())
+        lpt.eff = .9323
+        lpt.PR = 4.886
+
+        duct4 = self.add( 'duct4', Duct())
+        duct4.dPqP = .01
+
+        prinoz = self.add( 'prinoz', NozzleConvergent())
+        prinoz.cfg = .9978
+        self.connect('fc.Fl_O.Ps', 'prinoz.PsExh')    
+
+        hpshaft = self.add( 'hpshaft', Shaft())
+        hpspeed = self.add( 'hpspeed', Nmech())
+        hpspeed.Nmech = 8000
+
+        lpshaft = self.add( 'lpshaft', Shaft() )
+        lpspeed = self.add( 'lpspeed', Nmech())
+        hpspeed.Nmech = 2000
+
+        #inter component connections
+        self.connect( 'fc.Fl_O', 'inlet.Fl_I' )
+        self.connect( 'inlet.Fl_O', 'fan.Fl_I' )
+        self.connect( 'fan.Fl_O', 'split.Fl_I' )
+        self.connect( 'split.Fl_O2', 'bypduct.Fl_I' )
+        self.connect( 'bypduct.Fl_O', 'bypnoz.Fl_I' )
+        self.connect( 'split.Fl_O1', 'duct1.Fl_I' )
+        self.connect( 'duct1.Fl_O', 'lpc.Fl_I' )
+        self.connect( 'lpc.Fl_O', 'duct2.Fl_I' )
+        self.connect( 'duct2.Fl_O', 'hpc.Fl_I' )
+        self.connect( 'hpc.Fl_O', 'burner.Fl_I' )
+        self.connect( 'burner.Fl_O',  'hpt.Fl_I')
+        self.connect( 'hpt.Fl_O', 'duct3.Fl_I' )
+        self.connect( 'duct3.Fl_O', 'lpt.Fl_I' )
+        self.connect( 'lpt.Fl_O', 'duct4.Fl_I' )
+        self.connect( 'duct4.Fl_O', 'prinoz.Fl_I' )
+        self.connect( 'hpc.Fl_bld1', 'hpt.Fl_bld1' )
+        self.connect( 'hpc.Fl_bld2', 'hpt.Fl_bld2' )
+
+        self.connect( 'hpspeed.Nmech', ['hpshaft.Nmech','hpc.Nmech', 'hpt.Nmech'] )
+        self.connect( 'lpspeed.Nmech', ['lpshaft.Nmech','fan.Nmech','lpc.Nmech', 'lpt.Nmech'] )
+        self.connect( 'hpc.trq', 'hpshaft.trq1' )
+        self.connect( 'hpt.trq', 'hpshaft.trq2' )       
+        self.connect( 'fan.trq', 'lpshaft.trq1' )
+        self.connect( 'lpc.trq', 'lpshaft.trq2' )
+        self.connect( 'lpt.trq', 'lpshaft.trq3' )       
+
+        hpspeed.Nmech = 8000
+        lpspeed.Nmech = 2000
+
+        driver = self.driver
+        comp_list = [
+        	'inlet',
+                'fan',
+                'split',
+                'bypduct',
+                'bypnoz',
+                'lpc',
+                'hpc', 
+                'burner',
+                'hpt', 
+                'lpt', 
+                'prinoz',
+                'hpshaft',
+                'lpshaft',
+                'fc'
+          ]
+
+        solver = self.add('solver',BroydenSolver())
+
+        solver.workflow.add( comp_list )
+        driver.workflow.add('solver')
+
+from collections import OrderedDict
+TF1 = Turbofan()
+
+TF1.run()
+
+#TF1.run()
+
+print 'high shaft torques'
+print TF1.hpshaft.trqNet
+print TF1.hpshaft.trq1
+print TF1.hpshaft.trq2
+
+print 'Low shaft torques'
+print TF1.lpshaft.trqNet
+print TF1.lpshaft.trq1
+print TF1.lpshaft.trq2
+print TF1.lpshaft.trq3
+
+print TF1.hpc.trq
+print TF1.hpt.trq
+
+
+print 'fc'
+print TF1.fc.Fl_O.Pt
+print TF1.fc.Fl_O.Ps
+print TF1.fc.Fl_O.Tt
+print TF1.fc.Fl_O.W
+
+print 'inlet'
+print TF1.inlet.Fl_O.Pt
+print TF1.inlet.Fl_O.Tt
+print TF1.inlet.Fl_O.W
+
+print 'split'
+print TF1.split.Fl_O1.Pt
+print TF1.split.Fl_O1.Tt
+print TF1.split.Fl_O1.W
+
+print 'split'
+print TF1.split.Fl_O2.Pt
+print TF1.split.Fl_O2.Tt
+print TF1.split.Fl_O2.W
+
+print 'bypduct'
+print TF1.bypduct.Fl_O.Pt
+print TF1.bypduct.Fl_O.Tt
+print TF1.bypduct.Fl_O.W
+
+print 'lpc'
+print TF1.lpc.Fl_O.Pt
+print TF1.lpc.Fl_O.Tt
+print TF1.lpc.Fl_O.W
+
+print 'hpc'
+print TF1.hpc.Fl_O.Pt
+print TF1.hpc.Fl_O.Tt
+print TF1.hpc.Fl_O.W
+
+print TF1.hpc.Fl_bld1.Pt
+print TF1.hpc.Fl_bld1.Tt
+print TF1.hpc.Fl_bld1.W
+
+print TF1.hpc.Fl_bld2.Pt
+print TF1.hpc.Fl_bld2.Tt
+print TF1.hpc.Fl_bld2.W
+
+print 'burner'
+print TF1.burner.Fl_O.Pt
+print TF1.burner.Fl_O.Tt
+print TF1.burner.Fl_O.W  
+
+print 'hpt'
+print TF1.hpt.Fl_I.ht
+print TF1.hpt.Fl_O.Pt
+print TF1.hpt.Fl_O.Tt
+print TF1.hpt.Fl_O.W  
+
+print 'lpt'
+print TF1.lpt.Fl_O.Pt
+print TF1.lpt.Fl_O.Tt
+print TF1.lpt.Fl_O.W  
+
+print TF1.hpshaft.trqNet
+print TF1.burner.Wfuel/(TF1.prinoz.Fg+TF1.bypnoz.Fg-TF1.fc.Fram)*3600.
+
+

Turbofan/api.py

@@ -0,0 +1,13 @@
+from splitterT import SplitterBPR
+from start import FlowStart, FlowStartStatic
+from inletT import Inlet
+from nozzleT import Nozzle
+from ductT import Duct
+from compressor import Compressor
+from heat_exchanger import HeatExchanger
+from cycle_component import CycleComponent
+from flowstation import FlowStation, FlowStationVar
+
+from flightconditions import FlightConditions
+from burner import Burner
+from turbine import Turbine

src/pycycle/api.py

@@ -1,9 +1,26 @@
-from splitter import SplitterBPR, SplitterW
-from start import FlowStart, FlowStartStatic
-from inlet import Inlet
-from nozzle import Nozzle
-from duct import Duct
+#-------------------------------------------------
+#  load in flowstation/thermo info
+#-------------------------------------------------
+from flowstation import FlowStation, FlowStationVar
+
+#-------------------------------------------------
+#  load in component info
+#-------------------------------------------------
+from burner import Burner
 from compressor import Compressor
+from compressor_rline import CompressorRline
+from duct import Duct
+from flightconditions import FlightConditions
 from heat_exchanger import HeatExchanger
+from inlet import Inlet
+from nozzle_convergent import NozzleConvergent
+from nozzle import Nozzle
+from shaft import Shaft, Nmech
+from splitter_bpr import SplitterBPR
+from start import FlowStart
+from turbine_prmap import TurbinePRmap
+
 from cycle_component import CycleComponent
-from flowstation import FlowStation, FlowStationVar
+
+
+

src/pycycle/burner.py

@@ -0,0 +1,43 @@
+from openmdao.main.api import Component
+from openmdao.lib.datatypes.api import Float, VarTree, Int
+
+from pycycle.flowstation import FlowStation, FlowStationVar
+from pycycle.cycle_component import CycleComponent
+
+
+class Burner(CycleComponent): 
+    """The burner takes mixes one cantera flow with another at cantera reactant
+       and user supplied enthalpy.  If this cantera reactant is fuel, burning will
+       occur"""
+
+    #IO Variables
+    ID_fuel = Int( 0, iotype="in", desc="reactant id number of the flow being mixed (fuel being burned)", units = "lbm/s" ) 
+    dPqP = Float( 0.0, iotype="in", desc="pressure differential as a fraction of incomming pressure", units = "lbf/inch**2" )
+    hFuel = Float( 0.0, iotype="in", desc="enthalpy of incoming fuel", units = "Btu/lbm" )
+    Wfuel = Float( 0.0, iotype="in", desc="fuel weight flow", units = "lbm/s" )
+
+    #flow connections
+    Fl_I = FlowStationVar( iotype="in", desc="incoming flow stream to the burner", copy=None )
+    Fl_O = FlowStationVar( iotype="out", desc="flow stream leaving the burner", copy=None )
+
+
+    def execute(self): 
+        Fl_I = self.Fl_I
+        Fl_O = self.Fl_O 
+
+        #set the exit station to the inlet as a starting point
+        Fl_O.copy_from( Fl_I )
+
+        #mix the new reactant with the flow
+        Fl_O.burn( self.ID_fuel, self.Wfuel, self.hFuel ) 
+
+        #apply the pressure drop
+        Fl_O.setTotal_hP( Fl_O.ht, Fl_O.Pt*(1-self.dPqP) )
+
+
+if __name__ == "__main__": 
+    from openmdao.main.api import set_as_top
+
+    c = set_as_top(Burner())
+    c.run()
+