Propulsion-Assignment/solution.py at master · Surendhran-P/Propulsion-Assignment · GitHub

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from engine import *
import json


def turbojet():
    Tt0, Pt0 = freestream(M0, T0, P0)
    Tt2, Pt2 = inlet(M0, Tt0, Pt0, Inlet.eta, Inlet.pi)
    Tt3, Pt3 = compressor(Tt2, Pt2, Compressor.eta, Compressor.pi, Compressor.tau, Compressor.e)
    Tt4, Pt4, f, tau_lambda = burner(Tt3, Pt3, QR, Burner.pi, f_input, Burner_outlet_temp, Burner.tau, Burner.eta, tau_lambda_input)
    Tt5, Pt5 = turbine(Tt4, Pt4, Tt3, Tt2, f, tau_lambda, Turbine.eta, Turbine.pi, Turbine.tau, Turbine.e, eta_m)
    Tt9, Pt9 = nozzle(Tt5, Pt5, Nozzle.eta, Nozzle.pi, NPR, p_ratio)


def turbojet_ab():
    Tt0, Pt0, V0, a0 = freestream(M0, T0, P0)
    Tt2, Pt2 = inlet(M0, Tt0, Pt0, Inlet.eta, Inlet.pi)
    Tt3, Pt3 = compressor(Tt2, Pt2, Compressor.eta, Compressor.pi, Compressor.tau, Compressor.e)
    Tt4, Pt4, f, tau_lambda = burner(Tt3, Pt3, QR, Burner.pi, f_input, Burner_outlet_temp, Burner.tau, Burner.eta, tau_lambda_input)
    Tt5, Pt5, alpha = turbine(Tt4, Pt4, Tt3, Tt2, f, Turbine.eta, Turbine.pi, Turbine.tau, Turbine.e, eta_m)
    Tt7, Pt7, f_ab = afterburner(Tt5, Pt5, QR_AB, CP_M, Afterburner.pi, f_ab_input, f, Afterburner.eta, tau_lambda_ab, Afterburner.tau, Afterburner_outlet_temp)
    Tt9, Pt9 = nozzle(Tt7, Pt7, Nozzle.eta, Nozzle.pi, NPR, p_ratio)

    T9, P9, M9, V9 = engine_outlet_static(Tt9, Pt9, p_ratio)


    Temps = (Tt0, Tt2, Tt3, Tt4, Tt5, None, Tt7, Tt9)
    Pressures = (Pt0, Pt2, Pt3, Pt4, Pt5, None, Pt7, Pt9)

    St = specific_thrust(V9, V0, f, f_ab)
    Tsfc = tsfc(St, f, f_ab)
    eta_th = thermal_efficiency(V0, V9, f, f_ab)
    eta_prop = propulsive_efficiency(St, V0, V9, f, f_ab)
    eta_o = overall_efficiency(eta_th, eta_prop)


    solution = {
        'stations': data_parse.output_station([Inlet, Compressor, Burner, Turbine, Afterburner, Nozzle]),
        'temperatures': data_parse.output_temperature(Temps),
        'pressures': data_parse.output_pressure(Pressures),
        'other_parameters': {
            'f': f,
            'f_ab': f_ab
        },
        'performance parameters': {
            'Specific Thrust': St,
            'TSFC': Tsfc,
            'Thermal Efficiency': eta_th,
            'Propulsive Efficiency': eta_prop,
            'Overall Efficiency': eta_o
        }
    }

    print(json.dumps(solution['performance parameters'], indent=2))

    return solution


def turbofan_ab ():
    Tt0, Pt0, V0, a0 = freestream(M0, T0, P0)
    Tt2, Pt2 = inlet(M0, Tt0, Pt0, Inlet.eta, Inlet.pi)
    Tt13, Pt13 = fan(Tt2, Pt2, Fan.eta, Fan.pi, Fan.tau, Fan.e)
    Tt3, Pt3 = compressor(Tt2, Pt2, Compressor.eta, Compressor.pi, Compressor.tau, Compressor.e)
    Tt4, Pt4, f, tau_lambda = burner(Tt3, Pt3, QR, Burner.pi, f_input, Burner_outlet_temp, Burner.tau, Burner.eta, tau_lambda_input)
    Tt5, Pt5, alpha = turbine(Tt4, Pt4, Tt3, Tt2, f, tau_lambda, Turbine.eta, Turbine.pi, Turbine.tau, Turbine.e, eta_m)
    Tt15, Pt15, M15 = duct(Tt13, Pt13, M5, pi_fd)
    Tt6, Pt6, CP_M = mixer(Tt5, Pt5, Tt15, Pt15, f, alpha, tau_lambda, M5, M15, pi_Mf)
    Tt7, Pt7, f_ab = afterburner(Tt6, Pt6, QR_AB, CP_M, Afterburner.pi, f_ab_input, f, Afterburner.eta, tau_lambda_ab, Afterburner.tau, Afterburner_outlet_temp)
    Tt9, Pt9 = nozzle(Tt7, Pt7, Nozzle.eta, Nozzle.pi, NPR, p_ratio, pi_fd)

    T9, P9, M9, V9 = engine_outlet_static(Tt9, Pt9, p_ratio)

    Temps = (Tt0, Tt2, Tt3, Tt4, Tt5, Tt6, Tt7, Tt9, Tt13, Tt15)
    Pressures = (Pt0, Pt2, Pt3, Pt4, Pt5, Pt6, Pt7, Pt9, Pt13, Pt15)

    St = specific_thrust(V9, V0, f, f_ab, alpha)
    Tsfc = tsfc(St, f, f_ab)
    eta_th = thermal_efficiency(V0, V9, f, f_ab, alpha)
    eta_prop = propulsive_efficiency(St, V0, V9, f, f_ab, alpha)
    eta_o = overall_efficiency(eta_th, eta_prop)

    solution = {
        'stations': data_parse.output_station([Inlet, Fan, Compressor, Burner, Turbine, Mixer, Afterburner, Nozzle]),
        'temperatures': data_parse.output_temperature(Temps),
        'pressures': data_parse.output_pressure(Pressures),
        'other_parameters': {
            'f': f,
            'f_ab': f_ab,
            'alpha': alpha
        },
        'performance parameters': {
            'Specific Thrust': St,
            'TSFC': Tsfc,
            'Thermal Efficiency': eta_th,
            'Propulsive Efficiency': eta_prop,
            'Overall Efficiency': eta_o
        }
    }

    print(json.dumps(solution['performance parameters'], indent=2))
    return solution

def output (engine):
    """Writes output json file based on engine type
     Args:
        engine (str): Type of engine ('Turbojet_AB' or 'Turbofan_Mixed')
    """
    if engine == 'Turbojet_AB':
        data_parse.write_output_json('turbojet_afterburner.json', turbojet_ab())
    if engine == 'Turbofan_Mixed':
        data_parse.write_output_json('turbofan_mixed exhaust.json', turbofan_ab())