SUAVE.Components.Energy.Processes.Thrust.Thrust Class Reference

Inheritance diagram for SUAVE.Components.Energy.Processes.Thrust.Thrust:

Public Member Functions
def	__defaults__ (self)
def	compute (self, conditions)
def	compute_stream_thrust (self, conditions)
def	size (self, conditions)
def	size_stream_thrust (self, conditions)

Public Attributes
	tag
	bypass_ratio
	compressor_nondimensional_massflow
	reference_temperature
	reference_pressure
	number_of_engines
	design_thrust
	mass_flow_rate_design
	SFC_adjustment
Public Attributes inherited from SUAVE.Components.Energy.Energy_Component.Energy_Component
	inputs
	outputs
Public Attributes inherited from SUAVE.Components.Physical_Component.Physical_Component
	tag
	mass_properties
	origin
	symmetric
Public Attributes inherited from SUAVE.Components.Component.Component
	tag
	origin
	generative_design_max_per_vehicle
	generative_design_characteristics
	generative_design_special_parent

Detailed Description

A class that handles computation of thrust and other outputs for a gas turbine engine.

Assumptions:
Perfect gas

Source:
https://web.stanford.edu/~cantwell/AA283_Course_Material/AA283_Course_Notes/

Member Function Documentation

__defaults__()

def SUAVE.Components.Energy.Processes.Thrust.Thrust.__defaults__

(

self

)

This sets the default value.

Assumptions:
None

Source:
N/A

Inputs:
None

Outputs:
None

Properties Used:
N/A

Reimplemented from SUAVE.Components.Energy.Energy_Component.Energy_Component.

compute()

def SUAVE.Components.Energy.Processes.Thrust.Thrust.compute	(		self,
			conditions
	)

Computes thrust and other properties as below.

Assumptions:
Perfect gas

Source:
https://web.stanford.edu/~cantwell/AA283_Course_Material/AA283_Course_Notes/

Inputs:
conditions.freestream.
  isentropic_expansion_factor        [-] (gamma)
  specific_heat_at_constant_pressure [J/(kg K)]
  velocity                           [m/s]
  speed_of_sound                     [m/s]
  mach_number                        [-]
  pressure                           [Pa]
  gravity                            [m/s^2]
conditions.throttle                  [-] (.1 is 10%)
self.inputs.
  fuel_to_air_ratio                  [-]
  total_temperature_reference        [K]
  total_pressure_reference           [Pa]
  core_nozzle.
    velocity                         [m/s]
    static_pressure                  [Pa]
    area_ratio                       [-]
  fan_nozzle.
    velocity                         [m/s]
    static_pressure                  [Pa]
    area_ratio                       [-]
  number_of_engines                  [-]
  bypass_ratio                       [-]
  flow_through_core                  [-] percentage of total flow (.1 is 10%)
  flow_through_fan                   [-] percentage of total flow (.1 is 10%)

Outputs:
self.outputs.
  thrust                             [N]
  thrust_specific_fuel_consumption   [N/N-s]
  non_dimensional_thrust             [-]
  core_mass_flow_rate                [kg/s]
  fuel_flow_rate                     [kg/s]
  power                              [W]
  Specific Impulse                   [s]

Properties Used:
self.
  reference_temperature              [K]
  reference_pressure                 [Pa]
  compressor_nondimensional_massflow [-]
  SFC_adjustment                     [-]

compute_stream_thrust()

def SUAVE.Components.Energy.Processes.Thrust.Thrust.compute_stream_thrust	(		self,
			conditions
	)

Computes thrust and other properties as below. 

Assumptions: 

Source: 
Heiser, William H., Pratt, D. T., Daley, D. H., and Unmeel, B. M., 
"Hypersonic Airbreathing Propulsion", 1994 
Chapter 4 - pgs. 175-180

Inputs: 
conditions.freestream. 
   isentropic_expansion_factor        [-]  
   specific_heat_at_constant_pressure [J/(kg K)] 
   velocity                           [m/s] 
   speed_of_sound                     [m/s] 
   mach_number                        [-] 
   pressure                           [Pa] 
   gravity                            [m/s^2] 
conditions.throttle                  [-] (.1 is 10%) 

self.inputs. 
   fuel_to_air_ratio                  [-] 
   total_temperature_reference        [K] 
   total_pressure_reference           [Pa] 

core_nozzle. 
    velocity                         [m/s] 
    static_pressure                  [Pa] 
    area_ratio                       [-] 

fan_nozzle. 
    velocity                         [m/s] 
    static_pressure                  [Pa] 
    area_ratio                       [-] 
    number_of_engines                [-] 
    bypass_ratio                     [-] 
    flow_through_core                [-] percentage of total flow (.1 is 10%) 
    flow_through_fan                 [-] percentage of total flow (.1 is 10%)

Outputs: 
self.outputs. 
  thrust                             [N] 
  thrust_specific_fuel_consumption   [N/N-s] 
  non_dimensional_thrust             [-] 
  core_mass_flow_rate                [kg/s] 
  fuel_flow_rate                     [kg/s] 
  power                              [W] 

Properties Used: 
self. 
  reference_temperature              [K] 
  reference_pressure                 [Pa] 
  compressor_nondimensional_massflow [-] 

size()

def SUAVE.Components.Energy.Processes.Thrust.Thrust.size	(		self,
			conditions
	)

Sizes the core flow for the design condition.

Assumptions:
Perfect gas

Source:
https://web.stanford.edu/~cantwell/AA283_Course_Material/AA283_Course_Notes/

Inputs:
conditions.freestream.speed_of_sound [m/s] (conditions is also passed to self.compute(..))
self.inputs.
  bypass_ratio                       [-]
  total_temperature_reference        [K]
  total_pressure_reference           [Pa]
  number_of_engines                  [-]

Outputs:
self.outputs.non_dimensional_thrust  [-]

Properties Used:
self.
  reference_temperature              [K]
  reference_pressure                 [Pa]
  total_design                       [N] - Design thrust

size_stream_thrust()

def SUAVE.Components.Energy.Processes.Thrust.Thrust.size_stream_thrust	(		self,
			conditions
	)

Sizes the core flow for the design condition. 

   Assumptions: 
   Perfect gas 

   Source: 
   Heiser, William H., Pratt, D. T., Daley, D. H., and Unmeel, B. M., 
   "Hypersonic Airbreathing Propulsion", 1994 
   Chapter 4 - pgs. 175-180
   
   Inputs: 
   conditions.freestream.speed_of_sound [m/s] (conditions is also passed to self.compute(..)) 
   self.inputs. 
      bypass_ratio                       [-] 
      total_temperature_reference        [K] 
      total_pressure_reference           [Pa] 
      number_of_engines                  [-] 

    Outputs: 
      self.outputs.non_dimensional_thrust  [-] 

    Properties Used: 
    self. 
       reference_temperature              [K] 
       reference_pressure                 [Pa] 
       total_design                       [N] - Design thrust 

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The documentation for this class was generated from the following file:

• /Users/emiliobotero/Dropbox/SUAVE/SUAVE/trunk/SUAVE/Components/Energy/Processes/Thrust.py