Outlet

class turbodesign.outlet.Outlet

get_static_pressure(percent_hub_shroud: float | ndarray[tuple[Any, ...], dtype[_ScalarT]])

Returns the static pressure at a certain percent hub_shroud

Parameters:

percent_hub_shroud (Union[float,npt.NDArray]) – value or array from 0 to 1 where you want the exit static pressure

Returns:

Returns an array of static pressure

Return type:

npt.NDArray

get_total_pressure(percent_hub_shroud: float | ndarray[tuple[Any, ...], dtype[_ScalarT]])

Returns the total pressure at a certain percent hub shroud

Parameters:

percent_hub_shroud (Union[float,npt.NDArray]) – value or array from 0 to 1 where you want the exit total pressure

Returns:

Returns an array of total pressure

Return type:

npt.NDArray

init_static(P: List[float] | float, percent_radii: List[float] | float, massflow: float | None = None)

Initialize turbine inputs

Parameters:

• P (float) – Exit static pressure [Pa]

• percent_radii (Union[List[float],float]) – percent radii where the exit static pressure is defined.

• massflow (float | None) – initialize with a massflow. Note this is only valid if you set the solver to solve to MassflowConstraint.AngleMatch

init_total(P0: List[float] | float, percent_radii: List[float] | float)

Initialize compressor inputs

Parameters:

• P0 (Union[List[float],float]) – Exit Total Pressure (this will be matched)

• percent_radii (Union[List[float],float]) – percent radii where exit total pressure is defined

transfer_quantities(upstream: BladeRow)

Transfer quantities from upstream row to outlet while maintaining the outlet static pressure

Parameters:

upstream (BladeRow) – Upstream row, for turbines this is a rotor, for compressors this is a stator.