aerosandbox.library.power_turboshaft#

Module Contents#

Functions#

overall_pressure_ratio_turboshaft_technology_limit(...)

Estimates the maximum-practically-achievable overall pressure ratio (OPR) of a turboshaft engine, as a function

power_turboshaft(mass_turboshaft[, overall_pressure_ratio])

Estimates the maximum rated power of a turboshaft engine, given its mass. A regression to historical data.

thermal_efficiency_turboshaft(mass_turboshaft[, ...])

Estimates the thermal efficiency of a turboshaft engine. A regression to historical data.

Attributes#

x

aerosandbox.library.power_turboshaft.overall_pressure_ratio_turboshaft_technology_limit(mass_turboshaft)[source]#

Estimates the maximum-practically-achievable overall pressure ratio (OPR) of a turboshaft engine, as a function of its mass. A regression to historical data.

Based on an envelope of data for both civilian and military turboshafts (including RC-scale turboshafts), available in: aerosandbox/library/datasets/turbine_engines/data.xlsx

See study in /AeroSandbox/studies/TurboshaftStudies/make_fit_overall_pressure_ratio.py for model details.

Parameters:

mass_turboshaft (float) – The mass of the turboshaft engine. [kg]

Returns:

The maximum-practically-achievable overall pressure ratio (OPR) of the turboshaft engine. [-]

Return type:

float

aerosandbox.library.power_turboshaft.power_turboshaft(mass_turboshaft, overall_pressure_ratio=None)[source]#

Estimates the maximum rated power of a turboshaft engine, given its mass. A regression to historical data.

Based on data for both civilian and military turboshafts, available in: aerosandbox/library/datasets/turbine_engines/data.xlsx

See studies in /AeroSandbox/studies/TurboshaftStudies/make_fit_power.py for model details.

Parameters:

  • mass_turboshaft (float) – The mass of the turboshaft engine. [kg]

  • overall_pressure_ratio (float) – The overall pressure ratio of the turboshaft engine. [-] If unspecified, a sensible default based on the technology envelope (with a 0.7x knockdown) will be used.

Returns:

The maximum (rated takeoff) power of the turboshaft engine. [W]

Return type:

float

aerosandbox.library.power_turboshaft.thermal_efficiency_turboshaft(mass_turboshaft, overall_pressure_ratio=None, throttle_setting=1)[source]#

Estimates the thermal efficiency of a turboshaft engine. A regression to historical data.

Based on data for both civilian and military turboshafts, available in: aerosandbox/library/datasets/turbine_engines/data.xlsx

See studies in /AeroSandbox/studies/TurboshaftStudies/make_turboshaft_fits.py for model details.

Thermal efficiency knockdown at partial power is based on:

Ingmar Geiß, “Sizing of the Series Hybrid-electric Propulsion System of General Aviation Aircraft”, 2020. PhD Thesis, University of Stuttgart. Page 18, Figure 3.2.

Parameters:

  • mass_turboshaft (float) – The mass of the turboshaft engine. [kg]

  • overall_pressure_ratio (float) – The overall pressure ratio of the turboshaft engine. [-] If unspecified, a sensible default based on the technology envelope (with a 0.7x knockdown) will be used.

  • throttle_setting (float) – The throttle setting of the turboshaft engine. [-] 1 is full throttle, 0 is no throttle.

Returns:

The thermal efficiency of the turboshaft engine. [-]

Return type:

float

aerosandbox.library.power_turboshaft.x[source]#