# Numerical parameter file (SimpleGasTurbine_numpar.txt) # Generated by MTT at Tue Mar 31 12:15:00 BST 1998 # %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% # %% Version control history # %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% # %% $Id$ # %% $Log$ # %% Revision 1.1 2000/12/28 16:55:29 peterg # %% To RCS # %% # %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% #Dummies alpha = 1; c_v = 1; density = 1; ideal_gas = 1; j_s = 1; k = 1; k_p = 1; m = 1; m_c = 1; p_1 = 1; r = 1; r_l = 1; t_1 = 1; v = 1; v_c = 1; # Parameters c_p = 1005.0; c_v = 718.0; gamma_0 = c_p/c_v; alpha = (gamma_0-1)/gamma_0; k = 1.0; p_1 = 1e5; # 1 bar p_4 = p_1; r = c_p-c_v; t_1 = 288.0; # In v_c = 1.0; %Set the CC pressure and temperature t_3 = 1000.0; r_p = 6.0; p_3 = r_p*p_1; %Find stored mass to give combustion chamber pressure p_3 (at % temperature t_3 m_c = (p_3*v_c)/(t_3*r); %Equate pressures p_4 = p_1; p_2 = p_3; %Compute ss temperatures (isentropic) t_2 = t_1*pow((p_2/p_1),alpha); t_4 = t_3*pow((p_4/p_3),alpha); %Find the steady-state work output w_0 = c_p*(t_3-t_4) - c_p*(t_2-t_1); %Unit mass flow mdot = 1; %Corresponding shaft speed omega_0 = mdot/k; %Compute the corresponding load resistance (to absorb that work) r_l = w_0/pow((omega_0),2); %Compute shaft inertia to give unit time constant (j_s*r_l) j_s = r_l; %Find angular momentum to give shaft speed omega_0 mom_0 = omega_0*j_s;