aerosandbox.library.propulsion_turbofan#

Module Contents#

Functions#

thrust_turbofan(mass_turbofan)

Estimates the maximum rated dry thrust of a turbofan engine. A regression to historical data.

thrust_specific_fuel_consumption_turbofan(...)

Estimates the thrust-specific fuel consumption (TSFC) of a turbofan engine. A regression to historical data.

mass_turbofan(m_dot_core_corrected, ...)

Computes the combined mass of a bare turbofan, nacelle, and accessory and pylon weights.

m_dot_corrected_over_m_dot(temperature_total_2, ...)

Computes the ratio m_dot_corrected / m_dot, where:

Attributes#

atmo

aerosandbox.library.propulsion_turbofan.thrust_turbofan(mass_turbofan)[source]#

Estimates the maximum rated dry thrust of a turbofan engine. A regression to historical data.

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

Applicable to both turbojets and turbofans, and with sizes ranging from micro-turbines (<1 kg) to large transport aircraft turbofans.

See studies in /AeroSandbox/studies/TurbofanStudies/make_fit_thrust.py for model details.

Parameters:

mass_turbofan (float) – The mass of the turbofan engine. [kg]

Returns:

The maximum (rated takeoff) dry thrust of the turbofan engine. [N]

Return type:

float

aerosandbox.library.propulsion_turbofan.thrust_specific_fuel_consumption_turbofan(mass_turbofan, bypass_ratio)[source]#

Estimates the thrust-specific fuel consumption (TSFC) of a turbofan engine. A regression to historical data.

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

Applicable to both turbojets and turbofans, and with sizes ranging from micro-turbines (<1 kg) to large transport aircraft turbofans.

See studies in /AeroSandbox/studies/TurbofanStudies/make_fit_tsfc.py for model details.

Parameters:

  • mass_turbofan (float) –

  • bypass_ratio (float) –

Return type:

float

aerosandbox.library.propulsion_turbofan.mass_turbofan(m_dot_core_corrected, overall_pressure_ratio, bypass_ratio, diameter_fan)[source]#

Computes the combined mass of a bare turbofan, nacelle, and accessory and pylon weights.

Bare weight depends on m_dot, OPR, and BPR.

Nacelle weight is a function of various areas and fan diameter.

From TASOPT documentation by Mark Drela, available here: http://web.mit.edu/drela/Public/web/tasopt/TASOPT_doc.pdf

Section: “Turbofan Weight Model from Historical Data”

Parameters:

  • m_dot_core_corrected – The mass flow of the core only, corrected to standard conditions. [kg/s]

  • overall_pressure_ratio – The overall pressure ratio (OPR) [-]

  • bypass_ratio – The bypass ratio (BPR) [-]

  • diameter_fan – The diameter of the fan. [m]

Returns: The total engine mass. [kg]

aerosandbox.library.propulsion_turbofan.m_dot_corrected_over_m_dot(temperature_total_2, pressure_total_2)[source]#

Computes the ratio m_dot_corrected / m_dot, where:

  • m_dot_corrected is the corrected mass flow rate, where corrected refers to correction to ISO 3977 standard

temperature and pressure conditions (15C, 101325 Pa).

  • m_dot is the raw mass flow rate, at some other conditions.

Parameters:

  • temperature_total_2 – The total temperature at the compressor inlet face, at the conditions to be evaluated. [K]

  • pressure_total_2 – The total pressure at the compressor inlet face, at the conditions to be evaluated. [Pa]

Returns:

The ratio m_dot_corrected / m_dot.

aerosandbox.library.propulsion_turbofan.atmo[source]#