Module huracan.components.rotary
Rotary components
Expand source code
# SPDX-FileCopyrightText: © 2021 Antonio López Rivera <antonlopezr99@gmail.com>
# SPDX-License-Identifier: GPL-3.0-only
"""
Rotary components
-----------------
"""
from huracan.engine import component
class screw(component):
"""
Screw
-----
Mechanical device to turn rotational to axial motion.
"""
def __init__(self,
eta,
PI=None,
TAU=None):
"""
:type eta: float
:type PI: float
:type TAU: float
"""
self.eta = eta
self.PI = PI
self.TAU = TAU
class compressor(screw):
"""
Compressor
----------
Adiabatic compression.
"""
def __init__(self,
eta,
PI=None,
TAU=None):
"""
:type eta: float
:type PI: float
:type TAU: float
"""
super().__init__(eta=eta,
PI=PI,
TAU=TAU)
def tf(self, gas):
return gas.compression(eta=self.eta, PI=self.PI, TAU=self.TAU)
class turbine(screw):
"""
Turbine
-------
Adiabatic expansion.
"""
def __init__(self,
eta,
PI=None,
TAU=None):
"""
:type eta: float
:type PI: float
:type TAU: float
"""
super().__init__(eta=eta,
PI=PI,
TAU=TAU)
def tf(self, gas):
"""
Before runtime, if no total pressure or temperature
ratio has been provided, a minimum total temperature
ratio is calculated.
This temperature ratio is that required to power the
work exerting components in the turbine's shaft.
"""
if isinstance(self.PI, type(None)) and isinstance(self.TAU, type(None)):
t00 = self.stream.gas.t0
t01 = self.stream.gas.t0 - self.shaft.w_r()/(self.stream.gas.mf*self.stream.gas.cp(t00))
self.TAU = t01/t00
return gas.expansion(eta=self.eta, PI=self.PI, TAU=self.TAU)
def w_r(self):
return self.shaft.w_r()
class fan(screw):
"""
Fan
---
Fundamental differences with a propeller:
- Disk loading.
- Fan shroud.
- Bypass flow.
"""
def __init__(self,
eta,
PI=None,
TAU=None):
"""
:type eta: float
:type PI: float
:type TAU: float
"""
super().__init__(eta=eta,
PI= PI,
TAU=TAU)
def tf(self, gas):
return gas.compression(eta=self.eta, PI=self.PI, TAU=self.TAU)
class prop(screw):
"""
Propeller
---------
"""
def __init__(self,
eta,
w,
PI=None,
TAU=None):
"""
:param w: [W] Propeller break power
:type eta: float
:type w: float
:type PI: float
:type TAU: float
"""
super().__init__(eta=1,
PI=PI,
TAU=TAU)
self.w = w
self.eta_prop = eta
def thrust(self, v0):
return self.w*self.eta_prop/v0
def tf(self, gas):
p = gas.compression(eta=self.eta, PI=self.PI, TAU=self.TAU) # Placeholder
p.w = self.w
return p
class propfan(prop):
"""
Propfan
-------
Fundamental difference with a propeller:
- Disk loading.
"""Classes
class compressor (eta, PI=None, TAU=None)-
Compressor
Adiabatic compression.
:type eta: float :type PI: float :type TAU: float
Expand source code
class compressor(screw): """ Compressor ---------- Adiabatic compression. """ def __init__(self, eta, PI=None, TAU=None): """ :type eta: float :type PI: float :type TAU: float """ super().__init__(eta=eta, PI=PI, TAU=TAU) def tf(self, gas): return gas.compression(eta=self.eta, PI=self.PI, TAU=self.TAU)Ancestors
Methods
def tf(self, gas)-
Expand source code
def tf(self, gas): return gas.compression(eta=self.eta, PI=self.PI, TAU=self.TAU)
class fan (eta, PI=None, TAU=None)-
Fan
Fundamental differences with a propeller: - Disk loading. - Fan shroud. - Bypass flow.
:type eta: float :type PI: float :type TAU: float
Expand source code
class fan(screw): """ Fan --- Fundamental differences with a propeller: - Disk loading. - Fan shroud. - Bypass flow. """ def __init__(self, eta, PI=None, TAU=None): """ :type eta: float :type PI: float :type TAU: float """ super().__init__(eta=eta, PI= PI, TAU=TAU) def tf(self, gas): return gas.compression(eta=self.eta, PI=self.PI, TAU=self.TAU)Ancestors
Methods
def tf(self, gas)-
Expand source code
def tf(self, gas): return gas.compression(eta=self.eta, PI=self.PI, TAU=self.TAU)
class prop (eta, w, PI=None, TAU=None)-
Propeller
:param w: [W] Propeller break power
:type eta: float :type w: float :type PI: float :type TAU: float
Expand source code
class prop(screw): """ Propeller --------- """ def __init__(self, eta, w, PI=None, TAU=None): """ :param w: [W] Propeller break power :type eta: float :type w: float :type PI: float :type TAU: float """ super().__init__(eta=1, PI=PI, TAU=TAU) self.w = w self.eta_prop = eta def thrust(self, v0): return self.w*self.eta_prop/v0 def tf(self, gas): p = gas.compression(eta=self.eta, PI=self.PI, TAU=self.TAU) # Placeholder p.w = self.w return pAncestors
Subclasses
Methods
def tf(self, gas)-
Expand source code
def tf(self, gas): p = gas.compression(eta=self.eta, PI=self.PI, TAU=self.TAU) # Placeholder p.w = self.w return p def thrust(self, v0)-
Expand source code
def thrust(self, v0): return self.w*self.eta_prop/v0
class propfan (eta, w, PI=None, TAU=None)-
Propfan
Fundamental difference with a propeller: - Disk loading.
:param w: [W] Propeller break power
:type eta: float :type w: float :type PI: float :type TAU: float
Expand source code
class propfan(prop): """ Propfan ------- Fundamental difference with a propeller: - Disk loading. """Ancestors
class screw (eta, PI=None, TAU=None)-
Screw
Mechanical device to turn rotational to axial motion.
:type eta: float :type PI: float :type TAU: float
Expand source code
class screw(component): """ Screw ----- Mechanical device to turn rotational to axial motion. """ def __init__(self, eta, PI=None, TAU=None): """ :type eta: float :type PI: float :type TAU: float """ self.eta = eta self.PI = PI self.TAU = TAUAncestors
Subclasses
class turbine (eta, PI=None, TAU=None)-
Turbine
Adiabatic expansion.
:type eta: float :type PI: float :type TAU: float
Expand source code
class turbine(screw): """ Turbine ------- Adiabatic expansion. """ def __init__(self, eta, PI=None, TAU=None): """ :type eta: float :type PI: float :type TAU: float """ super().__init__(eta=eta, PI=PI, TAU=TAU) def tf(self, gas): """ Before runtime, if no total pressure or temperature ratio has been provided, a minimum total temperature ratio is calculated. This temperature ratio is that required to power the work exerting components in the turbine's shaft. """ if isinstance(self.PI, type(None)) and isinstance(self.TAU, type(None)): t00 = self.stream.gas.t0 t01 = self.stream.gas.t0 - self.shaft.w_r()/(self.stream.gas.mf*self.stream.gas.cp(t00)) self.TAU = t01/t00 return gas.expansion(eta=self.eta, PI=self.PI, TAU=self.TAU) def w_r(self): return self.shaft.w_r()Ancestors
Methods
def tf(self, gas)-
Before runtime, if no total pressure or temperature ratio has been provided, a minimum total temperature ratio is calculated. This temperature ratio is that required to power the work exerting components in the turbine's shaft.
Expand source code
def tf(self, gas): """ Before runtime, if no total pressure or temperature ratio has been provided, a minimum total temperature ratio is calculated. This temperature ratio is that required to power the work exerting components in the turbine's shaft. """ if isinstance(self.PI, type(None)) and isinstance(self.TAU, type(None)): t00 = self.stream.gas.t0 t01 = self.stream.gas.t0 - self.shaft.w_r()/(self.stream.gas.mf*self.stream.gas.cp(t00)) self.TAU = t01/t00 return gas.expansion(eta=self.eta, PI=self.PI, TAU=self.TAU) def w_r(self)-
Expand source code
def w_r(self): return self.shaft.w_r()