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

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from dataclasses import dataclass
import data_parse

@dataclass
class Station:
    name: str
    eta: float = None  # Isentropic efficiency
    pi: float = None   # Pressure ratio
    tau: float = None  # Temperature ratio
    e: float = None    # Adiabatic efficiency

var = int(input())

if var == 1:
    input_data = data_parse.read_input_json('Turbojet_Afterburner_input.json')
if var == 2:
    input_data = data_parse.read_input_json('Turbofan_Mixed_Exhaust_input.json')


# ---- Constants ----
Constants = input_data['Constants']
Other_constants = input_data['Other_inputs']

GAMMA_C  = Constants['GAMMA_C']    # Ratio of specific heats for air
GAMMA_T  = Constants["GAMMA_T"]    # Ratio of specific heats for combustion gases
GAMMA_AB = Constants["GAMMA_AB"]   # Ratio of specific heats for afterburner gases
GAMMA_m  = Constants["GAMMA_M"]    # Ratio of specific heats for mixer gases
R        = 287                     # Specific gas constant for air in J/(kg·K)
CP_C     = Constants["CP_C"]       # Specific heat at constant pressure for air in J/(kg·K)
CP_T     = Constants["CP_T"]       # Specific heat at constant pressure for combustion gases in J/(kg·K)
CP_AB    = Constants["CP_AB"]      # Specific heat at constant pressure for afterburner gases in J/(kg·K)
CP_M     = Constants["CP_M"]       # Specific heat at constant pressure for mixer gases
QR       = Constants["QR"]         # Heat release from fuel in J/kg
QR_AB    = Constants["QR_AB"]      # Heat release from afterburner fuel in J/kg

"""Needs to be extracted from json file data"""
Freestream = Station("Freestream")
Inlet = Station("Inlet")
Compressor = Station("Compressor")
Burner = Station("Burner")
Turbine = Station("Turbine")
Nozzle = Station("Nozzle")
Mixer = Station("Mixer")
Afterburner = Station("Afterburner")
Fan = Station("Fan")

station_tuple = (Freestream, Inlet, Compressor, Burner, Turbine, Nozzle, Mixer, Afterburner, Fan)


for s in station_tuple:
    s.eta, s.pi, s.tau, s.e = input_data['Stations'][s.name].values()


# ---- Input Conditions ----
M0 = Other_constants["M0"]        # Freestream Mach number
T0 = Other_constants["T0"]        # Freestream temperature in K
P0 = Other_constants["P0"]        # Freestream pressure in Pa

tau_lambda_input = Other_constants["tau_lambda"]   # Burner outlet and freestream temperature ratio
f_input = Other_constants["f"]        # Fuel-to-air ratio
Burner_outlet_temp = Other_constants["Burner_outlet_temp"]  # Burner outlet temperature in K

eta_m = Other_constants["Turbine_mechanical_efficiency"]      # Mechanical efficiency of turbine

tau_lambda_ab = Other_constants["tau_lambda_ab"]  # Afterburner fuel-to-air temperature ratio
f_ab_input = Other_constants["f_ab"]      # Afterburner fuel-to-air ratio
Afterburner_outlet_temp = Other_constants["Afterburner_outlet_temp"]  # Afterburner outlet temperature in K

pi_fd = Other_constants["pi_fd"]    # Mixer fan pressure ratio
M5 = Other_constants["M5"]          # Mixer cold stream Mach number
M15 = Other_constants["M15"]        # Mixer hot stream Mach number
pi_Mf = Other_constants["pi_fd"]    # Mixer fan pressure ratio
p_ratio = Other_constants["p_ratio"]  # P9 / P0
NPR = Other_constants["NPR"]          # Nozzle pressure ratio Pt7/P0