BladeRow

class turbodesign.bladerow.BladeRow

A single blade row (stator or rotor) in a turbomachine stage.

\*\*Core Configuration**

id

Row identifier.

Type:

int

stage_id

Stage identifier.

Type:

int

row_type

Stator or Rotor.

Type:

RowType

loss_function

Loss model applied to this row.

Type:

LossBaseClass, optional

deviation_function

Deviation model applied to this row.

Type:

DeviationBaseClass, optional

cutting_line

Line perpendicular to the streamline.

Type:

line2D, optional

rp

Degree of reaction.

Type:

float

hub_location

Hub axial location.

Type:

float

shroud_location

Shroud axial location.

Type:

float

\*\*Fluid Properties**

R

Ideal gas constant, J/(kg K). Default 287.15.

Type:

float

gamma

Ratio of specific heats Cp/Cv. Default 1.33.

Type:

float

Cp

Specific heat at constant pressure, J/(kg K). Default 1019.

Type:

float

Cv

Specific heat at constant volume, J/(kg K).

Type:

float

mu

Dynamic viscosity, Pa s.

Type:

float

\*\*Mass Flow**

total_massflow

Total mass flow including upstream cooling, kg/s.

Type:

float

massflow

Mass flow distribution per radial station.

Type:

ndarray

total_massflow_no_coolant

Inlet mass flow without coolant, kg/s.

Type:

float

massflow_target

Custom mass flow distribution for angle matching, kg/s.

Type:

ndarray, optional

\*\*Streamline Geometry**

percent_hub

Where blade row is defined along the hub (0-1).

Type:

float

percent_hub_shroud

Percent streamline length from hub to shroud.

Type:

ndarray

x

Axial coordinates.

Type:

ndarray

r

Radial coordinates.

Type:

ndarray

m

Meridional coordinates.

Type:

ndarray

total_area

Total annular flow area.

Type:

float

area

Flow area per streamline.

Type:

ndarray

\*\*Row Efficiency**

eta_total

Total-to-total isentropic efficiency.

Type:

float

eta_static

Total-to-static isentropic efficiency.

Type:

float

eta_poly

Polytropic efficiency.

Type:

float

stage_loading

Stage loading coefficient (work per stage).

Type:

float

\*\*Flow Angles** *(radians)*

alpha1, alpha2

Absolute flow angles at inlet and exit.

Type:

ndarray

beta1, beta2

Relative flow angles at inlet and exit.

Type:

ndarray

deviation

Flow deviation from metal angle.

Type:

ndarray

beta1_fixed, beta2_fixed

Whether inlet/exit geometry is already defined.

Type:

bool

\*\*Velocities**

Vm

Meridional velocity.

Type:

ndarray

Vx

Axial velocity.

Type:

ndarray

Vt

Tangential (swirl) velocity.

Type:

ndarray

Vr

Radial velocity.

Type:

ndarray

V

Absolute velocity magnitude.

Type:

ndarray

U

Blade peripheral velocity.

Type:

ndarray

W

Relative velocity magnitude.

Type:

ndarray

Wt

Relative tangential velocity.

Type:

ndarray

M

Absolute Mach number.

Type:

ndarray

M_rel

Relative Mach number.

Type:

ndarray

omega

Angular velocity, rad/s.

Type:

float

\*\*Thermodynamic Quantities**

P0

Total pressure, Pa.

Type:

ndarray

T0

Total temperature, K.

Type:

ndarray

P

Static pressure, Pa.

Type:

ndarray

T

Static temperature, K.

Type:

ndarray

rho

Density, kg/m^3.

Type:

ndarray

P0R

Relative total pressure, Pa.

Type:

ndarray

T0R

Relative total temperature, K.

Type:

ndarray

entropy_rise

Entropy rise across row.

Type:

ndarray

\*\*Performance**

power

Power, W.

Type:

float

P0_P

Total-to-static pressure ratio.

Type:

float

P0_ratio

Total-to-total pressure ratio.

Type:

float

flow_coefficient

Flow coefficient (Vm/U).

Type:

float

Reynolds

Reynolds number.

Type:

float

Yp

Pressure loss coefficient.

Type:

ndarray

\*\*Blade Geometry** *(set via properties)*

axial_chord

Axial chord length. Set via property.

Type:

float

aspect_ratio

Height-to-chord ratio. Set via property.

Type:

float

pitch_to_chord

Pitch-to-chord ratio. Set via property.

Type:

float

stagger

Stagger angle, degrees. Set via property.

Type:

float

num_blades

Blade count. Set via property.

Type:

int

tip_clearance

Clearance as fraction of span. Set via property.

Type:

float

te_pitch

Trailing-edge-to-pitch ratio. Set via property.

Type:

float

blade_to_blade_gap

Inter-row gap as fraction of chord. Set via property.

Type:

float

Cp: float = 1019

Cv: float = 893.8596491228071

M: ndarray[tuple[Any, ...], dtype[_ScalarT]]

M_rel: ndarray[tuple[Any, ...], dtype[_ScalarT]]

P: ndarray[tuple[Any, ...], dtype[_ScalarT]]

P0: ndarray[tuple[Any, ...], dtype[_ScalarT]]

P0R: ndarray[tuple[Any, ...], dtype[_ScalarT]]

P0R_is: ndarray[tuple[Any, ...], dtype[_ScalarT]]

P0_P: float = 0

P0_is: ndarray[tuple[Any, ...], dtype[_ScalarT]]

P0_ratio: float = 0

P0_ratio_target: float = 0

P0_stator_inlet: ndarray[tuple[Any, ...], dtype[_ScalarT]]

Power_Type: PowerType = 1

R: float = 287.15

Reynolds: float = 0

T: ndarray[tuple[Any, ...], dtype[_ScalarT]]

T0: ndarray[tuple[Any, ...], dtype[_ScalarT]]

T0R: ndarray[tuple[Any, ...], dtype[_ScalarT]]

T0_is: ndarray[tuple[Any, ...], dtype[_ScalarT]]

T0_stator_inlet: ndarray[tuple[Any, ...], dtype[_ScalarT]]

T_is: ndarray[tuple[Any, ...], dtype[_ScalarT]]

U: ndarray[tuple[Any, ...], dtype[_ScalarT]]

V: ndarray[tuple[Any, ...], dtype[_ScalarT]]

V2: ndarray[tuple[Any, ...], dtype[_ScalarT]]

Vm: ndarray[tuple[Any, ...], dtype[_ScalarT]]

Vr: ndarray[tuple[Any, ...], dtype[_ScalarT]]

Vt: ndarray[tuple[Any, ...], dtype[_ScalarT]]

Vx: ndarray[tuple[Any, ...], dtype[_ScalarT]]

W: ndarray[tuple[Any, ...], dtype[_ScalarT]]

Wt: ndarray[tuple[Any, ...], dtype[_ScalarT]]

Yp: ndarray[tuple[Any, ...], dtype[_ScalarT]]

alpha1: ndarray[tuple[Any, ...], dtype[_ScalarT]]

alpha2: ndarray[tuple[Any, ...], dtype[_ScalarT]]

area: ndarray[tuple[Any, ...], dtype[_ScalarT]]

property aspect_ratio

property axial_chord: float

Returns the mean axial chord defined in the x-direction

Returns:

Axial Chord

Return type:

float

beta1: ndarray[tuple[Any, ...], dtype[_ScalarT]]

beta1_fixed: bool = False

property beta1_metal: ndarray[tuple[Any, ...], dtype[_ScalarT]]

Backward-compatible alias for metal_inlet_angle.

beta1_metal_radii: ndarray[tuple[Any, ...], dtype[_ScalarT]]

beta2: ndarray[tuple[Any, ...], dtype[_ScalarT]]

beta2_fixed: bool = False

property beta2_metal: ndarray[tuple[Any, ...], dtype[_ScalarT]]

Backward-compatible alias for metal_exit_angle.

beta2_metal_radii: ndarray[tuple[Any, ...], dtype[_ScalarT]]

property blade_to_blade_gap: float

Returns the blade to blade gap value

Returns:

_description_

Return type:

float

blockage: float = 0

calculated_massflow: float = 0

property camber: float

Estimates the camber of the blade using a bezier curve. This is not as accurate because thickness is not defined on suction and pressure sides.

Returns:

camber length

Return type:

float

property chord: ndarray[tuple[Any, ...], dtype[_ScalarT]]

Chord defined at mean radius

Returns:

axial chord

Return type:

float

property coolant

cutting_line: <lambda> | None = None

deviation: ndarray[tuple[Any, ...], dtype[_ScalarT]]

deviation_function: DeviationBaseClass | None = None

entropy_rise: ndarray[tuple[Any, ...], dtype[_ScalarT]]

eta_poly: float = 0.0

eta_static: float = 0

eta_total: float = 0

euler_power: float = 0

flow_coefficient: float = 0

gamma: float = 1.33

hub_location: float = 0.0

id: int = 0

incli_curve_radii: ndarray[tuple[Any, ...], dtype[_ScalarT]]

property inlet_to_outlet_pratio: Tuple[float, float]

This is what is varied by the optimization. The range is between [0 and 1] but you should

Returns:

_description_

Return type:

List[float]

property location: float

loss_function: LossBaseClass | None = None

property loss_model

m: ndarray[tuple[Any, ...], dtype[_ScalarT]]

massflow: ndarray[tuple[Any, ...], dtype[_ScalarT]]

massflow_target: ndarray[tuple[Any, ...], dtype[_ScalarT]] | None = None

property metal_exit_angle: ndarray[tuple[Any, ...], dtype[_ScalarT]]

Blade metal exit angle (degrees).

property metal_inlet_angle: ndarray[tuple[Any, ...], dtype[_ScalarT]]

Blade metal inlet angle (degrees).

mprime: ndarray[tuple[Any, ...], dtype[_ScalarT]]

mu: float = 0

property num_blades: float

Configured number of blades (set during design/initialization).

omega: float = 0

percent_hub: float = 0

percent_hub_shroud: ndarray[tuple[Any, ...], dtype[_ScalarT]]

phi: ndarray[tuple[Any, ...], dtype[_ScalarT]]

property pitch: float

Returns the pitch which is the distance from blade to blade

Returns:

pitch

Return type:

float

property pitch_to_chord: ndarray[tuple[Any, ...], dtype[_ScalarT]]

Gets the pitch to chord ratio

Returns:

pitch to chord ratio

Return type:

float

power: float = 0

power_distribution: ndarray[tuple[Any, ...], dtype[_ScalarT]]

power_mean: float = 0

r: ndarray[tuple[Any, ...], dtype[_ScalarT]]

rho: ndarray[tuple[Any, ...], dtype[_ScalarT]]

rm: ndarray[tuple[Any, ...], dtype[_ScalarT]]

row_type: RowType = 1

rp: float = 0.4

property rpm

shroud_location: float = 0.0

property solidity: ndarray[tuple[Any, ...], dtype[_ScalarT]]

Inverse of pitch to chord ratio

Returns:

solidity value

Return type:

float

stage_id: int = 0

stage_loading: float = 0

property stagger: float

Average stagger angle

Returns:

stagger angle

Return type:

float

synchronize_blade_geometry() → None

Couple num_blades, pitch-to-chord/solidity, chord, and stagger.

Uses mean radius from interpolated streamlines to derive pitch, chord, and stagger (axial chord / chord).

property te_pitch

Trailing edge to pitch ratio

Returns:

trailing edge to pitch ratio

Return type:

float

property throat: float

Throat distance

Returns:

throat

Return type:

float

property tip_clearance

Tip clearance as a percentage of annulus height

to_dict()

total_area: float = 0

total_massflow: float = 0

total_massflow_no_coolant: float = 0

x: ndarray[tuple[Any, ...], dtype[_ScalarT]]

Module Functions

turbodesign.bladerow.interpolate_streamline_quantities(row: BladeRow, passage: Passage, num_streamlines: int = 3)

Interpolate all quantities onto the streamline and allocates variables. Run this after setting some initial conditions

Parameters:

• r_streamline (npt.NDArray) – Radii describing the streamline

• passage (Passage) – Passage object describing the geometry of the hub and shroud

• num_streamlines (int) – number of streamlines to consider

Returns:

new row object with quantities interpolated

Return type:

(BladeRow)

turbodesign.bladerow.sutherland(T: float | ndarray[tuple[Any, ...], dtype[_ScalarT]]) → float | ndarray[tuple[Any, ...], dtype[_ScalarT]]

Sutherland viscosity calculation used for reynolds number

Parameters:

T (float) – Temperature in Kelvin

Returns:

Dynamic Viscosity (mu) in Pa*s

Return type:

float