turboflow.centrifugal_compressor.choking_criterion module

turboflow.centrifugal_compressor.choking_criterion.evaluate_choking(independents, inlet_state, boundary_conditions, geometry, fluid, model_options, reference_values, component, u_throat=0)

Evaluate throat residuals

turboflow.centrifugal_compressor.choking_criterion.evaluate_throat(w_throat, fluid, mass_flow_rate, rothalpy, s_in, A_throat, theta_throat, u_throat)

Evaluate throat based on w_throat. (See get_res_throat, but more detailed)

turboflow.centrifugal_compressor.choking_criterion.evaluate_throat_mass_flow(w_throat, fluid, mass_flow_rate, rothalpy, s_in, A_throat, theta_throat, u_throat)

Wrapper of evaluate_throat, returning only the residuals. Used like get_res_throat

turboflow.centrifugal_compressor.choking_criterion.evaluate_throat_residual(w_throat, fluid, mass_flow_rate, rothalpy, s_in, A_throat, theta_throat, u_throat)

Wrapper of evaluate_throat, returning only the residuals. Used like get_res_throat

turboflow.centrifugal_compressor.choking_criterion.get_critical_throat(independents, inlet_state, boundary_conditions, geometry, fluid, model_options, reference_values, component, u_throat=0)

Get gradient of get_res_throat at point x

Impeller: rothalpy is rothalpy, w2 is relative flow and u_throat is throat blade speed Stationary components: rothalpy is the stagnation enthalpy, w2 is absolute velocity and u_throat is zero

turboflow.centrifugal_compressor.choking_criterion.get_mass_flow_gradient(w_throat, fluid, mass_flow_rate, rothalpy, s_in, A_throat, theta_throat, u_throat, eps, f0)

turboflow.centrifugal_compressor.choking_criterion.get_residual_gradient(w_throat, fluid, mass_flow_rate, rothalpy, s_in, A_throat, theta_throat, u_throat, eps, f0)

Evaluate gradient of the throat residuals.

turboflow.centrifugal_compressor.choking_criterion.get_throat(independents, inlet_state, boundary_conditions, geometry, fluid, model_options, reference_values, component, u_throat=0)

Get gradient of get_res_throat at point x

Impeller: rothalpy is rothalpy, w2 is relative flow and u_throat is throat blade speed Stationary components: rothalpy is the stagnation enthalpy, w2 is absolute velocity and u_throat is zero