propulsion¶
-
class
propulsion.
Propulsion
(**kwargs)[source]¶ Bases:
openmdao.components.meta_model_structured_comp.MetaModelStructuredComp
Interpolates engine parameters from engine deck.
The Propulsion component requires the following inputs:
inputs['z']
: aircraft z-position [m]inputs['M_0']
: ambient Mach number [-]inputs['TS']
: engine thrust-setting [-]
The Propulsion component computes the following outputs:
outputs['W_f']
: engine fuel consumptionoutputs['F_n']
: engine net thrust [N]outputs['Tti_c']
: combustor inlet total temperature [K]outputs['Pti_c']
: combustor inlet total pressure [Pa]outputs['V_j']
: engine jet velocity [m/s]outputs['rho_j']
: engine jet density [kg/m3]outputs['A_j']
: engine jet area [m2]outputs['Tt_j']
: engine jet total temperature [K]outputs['M_j']
: engine jet Mach number [-]outputs['mdoti_c']
: engine combustor inlet mass flow [kg/s]outputs['Ttj_c']
: engine combustor exit total temperature [K]outputs['DTt_des_c']
: engine design turbine total temperature drop [K]outputs['rho_ti_c']
: engine turbine inlet density [kg/m3]outputs['c_ti_c']
: engine turbine inlet speed of sound [m/s]outputs['rho_te_c']
: engine turbine exit density [kg/m3]outputs['c_te_c']
: engine turbine exit speed of sound [m/s]outputs['DTt_f']
: engine fan total temperature rise [K]outputs['mdot_f']
: engine fan mass flow [kg/s]outputs['N_f']
: engien fan rotational speed [rpm]outputs['A_f']
: engien fan inlet area [m2]outputs['d_f']
: engien fan diameter [m]
The thermodynamic engine cycle module is developed using the numerical propulsion system simulation (NPSS) software. A look-up table is implemented of the engine parameters as a function of flight Mach number, \(M_0 \in [0,0.5]\), flight altitude, \(z\in [0, 5000]m\), and engine thrust-setting, \(TS \in [30, 105] \%\). The thrust-setting, TS, at a particular Mach number and altitude is defined as a fraction of the maximum thermodynamic available thrust at these flight conditions. The maximum available thrust is defined as the thrust obtained when the engine is operated at 100% fan corrected speed (Ntextsubscript{1c2}).