Inlet

class turbodesign.inlet.Inlet[source]

Station defined at Inlet

Inherits:

(BladeRow): Defines the properties of the blade row

__initialize_fluid__(fluid: Solution | None = None, R: float = 287.15, gamma: float = 1.4, Cp: float = 1024)[source]

Initialize the inlet using the fluid. This function should be called by a class that inherits from spool

Parameters:

  • fluid (Solution, optional) – Cantera fluid object. Defaults to None.

  • R (float, optional) – Ideal Gas Constant. Defaults to 287.15 J/(Kg K) for air

  • gamma (float, optional) – _description_. Defaults to 1.4.

  • Cp (float, optional) – _description_. Defaults to 1024 J/(Kg K).

__initialize_velocity__(passage: Passage, num_streamlines: int)[source]
Initialize velocity calculations. Assumes streamlines and inclination angles have been calculated

Call this before performing calculations

Parameters:

  • passage (Passage) – Passage object

  • num_streamlines (int) – number of streamlines

__interpolate_quantities__(num_streamlines: int = 5)[source]

Initializes the inputs

Parameters:

  • num_streamlines (int, optional) – _description_. Defaults to 5.

  • IsCompressor (bool, optional) – This is if static pressure is defined at the inlet and total pressure at the outlet. Defaults to False.

get_total_pressure(percent_hub_shroud: float | NDArray)[source]

Returns the static pressure at a certain percent hub_shroud

Parameters:

percent_hub_shroud (Union[float,npt.NDArray]) – _description_

Returns:

_description_

Return type:

_type_

get_total_temperature(percent_hub_shroud: float | NDArray)[source]

Returns the static pressure at a certain percent hub_shroud

Parameters:

percent_hub_shroud (Union[float,npt.NDArray]) – _description_

Returns:

_description_

Return type:

_type_

init_static(P: float | List[float], T: float | List[float], M: float | List[float], percent_radii: float | List[float] = [0.5])[source]

Initializes the inlet with static quantities at the inlet

Parameters:

  • P (Union[float,List[float]]) – Static Pressure either as a float or array

  • T (Union[float,List[float]]) – Static Temperature either as a float or array

  • M (Union[float,List[float]]) – Mach Number either as a float or array

  • percent_radii (Union[float,List[float]], optional) – Percent radii where P,T, and M are defined. Defaults to [0.5].

init_total(P0: float | List[float], T0: float | List[float], M: float | List[float], percent_radii: float | List[float] | None = None)[source]

Initializes the inlet with total quantities at the inlet

Parameters:

  • P0 (Union[float,List[float]]) – Total Pressure either as a float or array

  • T0 (Union[float,List[float]]) – Total Temperature either as a float or array

  • M (Union[float,List[float]]) – Mach Number either as a float or array

  • percent_radii (Optional[Union[float,List[float]]], optional) – Percent radii where P0, T0, and M are defined. Defaults to None, which uses evenly spaced radii when multiple values exist or [0.5] otherwise.