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Build # 150

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Pull #16

travis-ci-com

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web-flow

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Pull Request Pull Request #16: Add CFM56 surrogate and B737-800 test case

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/openconcept/components/cfm56.py

from __future__ import division
import numpy as np
import openmdao.api as om
import openconcept
from openconcept.utilities.surrogates.cached_kriging_surrogate import KrigingSurrogate

def CFM56(num_nodes=1, plot=False):
    """
    A simple turboshaft which generates shaft power consumes fuel.

    This model assumes constant power specific fuel consumption (PSFC).

    Inputs
    ------
    throttle: float
        Engine throttle. Controls power and fuel flow.
        Produces 100% of rated power at throttle = 1.
        Should be in range 0 to 1 or slightly above 1.
        (vector, dimensionless)
    fltcond|h: float
        Altitude
        (vector, dimensionless)
    fltcond|M: float
        Mach number
        (vector, dimensionless)

    Outputs
    -------
    thrust : float
        Thrust developed by the engine (vector, lbf)
    fuel_flow : float
        Fuel flow consumed (vector, lbm/s)
    T4 : float
        Turbine inlet temperature (vector, Rankine)

    Options
    -------
    num_nodes : int
        Number of analysis points to run (sets vec length; default 1)
    """
    file_root = openconcept.__path__[0] + r'/components/empirical_data/cfm56/'
    thrustdata = np.load(file_root + 'cfm56thrust.npy')
    fuelburndata = np.load(file_root + 'cfm56wf.npy')
    t4data = np.load(file_root + r'cfm56t4.npy')
    krigedata = []
    for ialt, altitude in enumerate(np.array([35, 30, 25, 20, 15, 10, 5, 0])*1000.):
        for jmach, mach in enumerate(np.array([8, 7, 6, 5, 4, 3, 2, 1, 0.])*0.1):
            for kthrot, throttle in enumerate(np.array([10, 9, 8, 7, 6, 5, 4, 3, 2])*0.1):
                thrustijk = thrustdata[ialt, jmach, kthrot]
                if thrustijk > 0.0:
                    krigedata.append(np.array([throttle, altitude, mach, thrustijk.copy(), fuelburndata[ialt, jmach, kthrot].copy(), t4data[ialt, jmach, kthrot].copy()]))

    a = np.array(krigedata)
    comp = om.MetaModelUnStructuredComp(vec_size=num_nodes)
    comp.add_input('throttle', np.ones((num_nodes,))*1., training_data=a[:,0], units=None)
    comp.add_input('fltcond|h', np.ones((num_nodes,))*0., training_data=a[:,1], units='ft')
    comp.add_input('fltcond|M', np.ones((num_nodes,))*0.3, training_data=a[:,2], units=None)

    comp.add_output('thrust', np.ones((num_nodes,))*10000.,
                    training_data=a[:,3], units='lbf',
                    surrogate=KrigingSurrogate(cache_trained_model=True, cached_model_filename='cfm56thrust.pkl'))
    comp.add_output('fuel_flow', np.ones((num_nodes,))*3.0,
                    training_data=a[:,4], units='lbm/s',
                    surrogate=KrigingSurrogate(cache_trained_model=True, cached_model_filename='cfm56fuelburn.pkl'))
    comp.add_output('T4', np.ones((num_nodes,))*3000.,
                    training_data=a[:,5], units='R',
                    surrogate=KrigingSurrogate(cache_trained_model=True, cached_model_filename='cfm56T4.pkl'))
    comp.options['default_surrogate'] = KrigingSurrogate(lapack_driver='gesvd', cache_trained_model=True)

    if plot:
        import matplotlib.pyplot as plt
        prob = om.Problem()
        prob.model.add_subsystem('comp', comp)
        prob.setup()

        machs = np.linspace(0.0, 0.8, 25)
        alts = np.linspace(0.0, 35000., 25)
        machs, alts = np.meshgrid(machs, alts)
        pred = np.zeros((25, 25, 3))
        for i in range(25):
            for j in range(25):
                prob['comp.throttle'] = 0.95
                prob['comp.fltcond|h'] = alts[i,j]
                prob['comp.fltcond|M'] = machs[i,j]
                prob.run_model()
                pred[i,j,0] = prob['comp.thrust'][0].copy()
                pred[i,j,1] = prob['comp.fuel_flow'][0].copy()
        plt.figure()
        plt.xlabel('Mach')
        plt.ylabel('Altitude')
        plt.title('SFC (lb / hr lb) OM')
        # plt.contourf(machs, alts, pred[:,:,0])
        plt.contourf(machs, alts, (pred[:,:,1] / pred[:,:,0])*60*60, levels=np.linspace(0.3,1.2,20))
        plt.colorbar()
        plt.figure()
        plt.xlabel('Mach')
        plt.ylabel('Altitude')
        plt.title('Thrust (lb)')
        # plt.contourf(machs, alts, pred[:,:,0])
        plt.contourf(machs, alts, pred[:,:,1], levels=20)
        plt.colorbar()
        plt.figure()
        plt.xlabel('Mach')
        plt.ylabel('Altitude')
        plt.title('Fuel Flow (lb)')
        # plt.contourf(machs, alts, pred[:,:,0])
        plt.contourf(machs, alts, pred[:,:,0], levels=20)
        plt.colorbar()
        plt.show()
    return comp

1	from __future__ import division	1✔
2	import numpy as np	1✔
3	import openmdao.api as om	1✔
4	import openconcept	1✔
5	from openconcept.utilities.surrogates.cached_kriging_surrogate import KrigingSurrogate	1✔
6
7	def CFM56(num_nodes=1, plot=False):	1✔
8	"""
9	A simple turboshaft which generates shaft power consumes fuel.
10
11	This model assumes constant power specific fuel consumption (PSFC).
12
13	Inputs
14	------
15	throttle: float
16	Engine throttle. Controls power and fuel flow.
17	Produces 100% of rated power at throttle = 1.
18	Should be in range 0 to 1 or slightly above 1.
19	(vector, dimensionless)
20	fltcond\|h: float
21	Altitude
22	(vector, dimensionless)
23	fltcond\|M: float
24	Mach number
25	(vector, dimensionless)
26
27	Outputs
28	-------
29	thrust : float
30	Thrust developed by the engine (vector, lbf)
31	fuel_flow : float
32	Fuel flow consumed (vector, lbm/s)
33	T4 : float
34	Turbine inlet temperature (vector, Rankine)
35
36	Options
37	-------
38	num_nodes : int
39	Number of analysis points to run (sets vec length; default 1)
40	"""
41	file_root = openconcept.__path__[0] + r'/components/empirical_data/cfm56/'	1✔
42	thrustdata = np.load(file_root + 'cfm56thrust.npy')	1✔
43	fuelburndata = np.load(file_root + 'cfm56wf.npy')	1✔
44	t4data = np.load(file_root + r'cfm56t4.npy')	1✔
45	krigedata = []	1✔
46	for ialt, altitude in enumerate(np.array([35, 30, 25, 20, 15, 10, 5, 0])*1000.):	1✔
47	for jmach, mach in enumerate(np.array([8, 7, 6, 5, 4, 3, 2, 1, 0.])*0.1):	1✔
48	for kthrot, throttle in enumerate(np.array([10, 9, 8, 7, 6, 5, 4, 3, 2])*0.1):	1✔
49	thrustijk = thrustdata[ialt, jmach, kthrot]	1✔
50	if thrustijk > 0.0:	1✔
51	krigedata.append(np.array([throttle, altitude, mach, thrustijk.copy(), fuelburndata[ialt, jmach, kthrot].copy(), t4data[ialt, jmach, kthrot].copy()]))	1✔
52
53	a = np.array(krigedata)	1✔
54	comp = om.MetaModelUnStructuredComp(vec_size=num_nodes)	1✔
55	comp.add_input('throttle', np.ones((num_nodes,))*1., training_data=a[:,0], units=None)	1✔
56	comp.add_input('fltcond\|h', np.ones((num_nodes,))*0., training_data=a[:,1], units='ft')	1✔
57	comp.add_input('fltcond\|M', np.ones((num_nodes,))*0.3, training_data=a[:,2], units=None)	1✔
58
59	comp.add_output('thrust', np.ones((num_nodes,))*10000.,	1✔
60	training_data=a[:,3], units='lbf',
61	surrogate=KrigingSurrogate(cache_trained_model=True, cached_model_filename='cfm56thrust.pkl'))
62	comp.add_output('fuel_flow', np.ones((num_nodes,))*3.0,	1✔
63	training_data=a[:,4], units='lbm/s',
64	surrogate=KrigingSurrogate(cache_trained_model=True, cached_model_filename='cfm56fuelburn.pkl'))
65	comp.add_output('T4', np.ones((num_nodes,))*3000.,	1✔
66	training_data=a[:,5], units='R',
67	surrogate=KrigingSurrogate(cache_trained_model=True, cached_model_filename='cfm56T4.pkl'))
68	comp.options['default_surrogate'] = KrigingSurrogate(lapack_driver='gesvd', cache_trained_model=True)	1✔
69
70	if plot:	1✔
71	import matplotlib.pyplot as plt	×
72	prob = om.Problem()	×
73	prob.model.add_subsystem('comp', comp)	×
74	prob.setup()	×
75
76	machs = np.linspace(0.0, 0.8, 25)	×
77	alts = np.linspace(0.0, 35000., 25)	×
78	machs, alts = np.meshgrid(machs, alts)	×
79	pred = np.zeros((25, 25, 3))	×
80	for i in range(25):	×
81	for j in range(25):	×
82	prob['comp.throttle'] = 0.95	×
83	prob['comp.fltcond\|h'] = alts[i,j]	×
84	prob['comp.fltcond\|M'] = machs[i,j]	×
85	prob.run_model()	×
86	pred[i,j,0] = prob['comp.thrust'][0].copy()	×
87	pred[i,j,1] = prob['comp.fuel_flow'][0].copy()	×
88	plt.figure()	×
89	plt.xlabel('Mach')	×
90	plt.ylabel('Altitude')	×
91	plt.title('SFC (lb / hr lb) OM')	×
92	# plt.contourf(machs, alts, pred[:,:,0])
93	plt.contourf(machs, alts, (pred[:,:,1] / pred[:,:,0])6060, levels=np.linspace(0.3,1.2,20))	×
94	plt.colorbar()	×
95	plt.figure()	×
96	plt.xlabel('Mach')	×
97	plt.ylabel('Altitude')	×
98	plt.title('Thrust (lb)')	×
99	# plt.contourf(machs, alts, pred[:,:,0])
100	plt.contourf(machs, alts, pred[:,:,1], levels=20)	×
101	plt.colorbar()	×
102	plt.figure()	×
103	plt.xlabel('Mach')	×
104	plt.ylabel('Altitude')	×
105	plt.title('Fuel Flow (lb)')	×
106	# plt.contourf(machs, alts, pred[:,:,0])
107	plt.contourf(machs, alts, pred[:,:,0], levels=20)	×
108	plt.colorbar()	×
109	plt.show()	×
110	return comp	1✔

mdolab / openconcept / 150

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