Difference between revisions of "Intake"

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=basic theory=
 
=basic theory=
 
=restrictor implications=
 
=restrictor implications=
we don't have the math extension yet, so this is gonna look wack until we do <br />
+
we don't have the math extension yet, so this is gonna look wack until we do <br />general [https://www.grc.nasa.gov/WWW/K-12/airplane/mflchk.html equation] for ideal compressible gas flow:[citation needed]<br />[key for variables]
general equation for ideal compressible gas flow:[citation needed]<br />
+
{| class="wikitable"
[key for variables]<br />
+
|-
<math>mdot = \frac{A*p_t}{\sqrt{T_t}}\sqrt{\frac{\gamma}{R}}M(1+\frac{\gamma-1}{2}M^2)^-\frac{\gamma+1}{2(\gamma-1}</math><br />
+
|A<br />
when M becomes 1, the flow is considered choked. The equation becomes:<br />
+
|Area<br />
<math>mdot = \frac{A*p_t}{\sqrt{T_t}}\sqrt{\frac{\gamma}{R}}(1+\frac{\gamma-1}{2})^-\frac{\gamma+1}{2(\gamma-1}</math><br />
+
|-
With some basic assumed values at sea level, the maximum mass air flow through the restrictor can be found:<br />
+
|R<br />
[put table here]<br />
+
|Gas Constant<br />
Plugging these into the equation above yields a steady state mass flow rate of 0.074 kg air per second<br />
+
|-
If we assume an AFR of 13.1 (typical lambda for high torque for NA engines[citation needed]), and a <math>Q_LHV</ math> of 46 MJ/kg [citation needed], the mass air flow yields a power limit of 265.5 kW or 356 hp total energey output. If the thermal efficiency of the engine is assumed to be a nominal 33%, the maximum available mechanical power is 88.5 kW or 118 horsepower with 100% volumetric efficiency.<br />
+
|V<br />
 +
|Velocity<br />
 +
|-
 +
|T_t<br />
 +
|Total Temperature<br />
 +
|-
 +
|r<br />
 +
|Density<br />
 +
|-
 +
|\gamma<br />
 +
|Specific Heat Ratio<br />
 +
|-
 +
|M<br />
 +
|Mach number<br />
 +
|-
 +
|P_t
 +
|Total Pressure<br />
 +
|}
 +
<br />mdot = \frac{A*p_t}{\sqrt{T_t}}\sqrt{\frac{\gamma}{R}}M(1+\frac{\gamma-1}{2}M^2)^-\frac{\gamma+1}{2(\gamma-1}<br />when M becomes 1, the flow is considered choked. The equation becomes:<br />mdot = \frac{A*p_t}{\sqrt{T_t}}\sqrt{\frac{\gamma}{R}}(1+\frac{\gamma-1}{2})^-\frac{\gamma+1}{2(\gamma-1}<br />With some basic assumed values at sea level, the maximum mass air flow through the restrictor can be found:<br />[put table here]<br />Plugging these into the equation above yields a steady state mass flow rate of 0.074 kg air per second<br />If we assume an AFR of 13.1 (typical lambda for high torque for NA engines[citation needed]), and a Q_LHV<!-- math--> of 46 MJ/kg [citation needed], the mass air flow yields a power limit of 265.5 kW or 356 hp total energey output. If the thermal efficiency of the engine is assumed to be a nominal 33%, the maximum available mechanical power is 88.5 kW or 118 horsepower with 100% volumetric efficiency.
  
 
=throttle control=
 
=throttle control=

Revision as of 12:08, 15 May 2020


Current/Proposed Outline:

basic theory

restrictor implications

we don't have the math extension yet, so this is gonna look wack until we do
general equation for ideal compressible gas flow:[citation needed]
[key for variables]

A
Area
R
Gas Constant
V
Velocity
T_t
Total Temperature
r
Density
\gamma
Specific Heat Ratio
M
Mach number
P_t Total Pressure


mdot = \frac{A*p_t}{\sqrt{T_t}}\sqrt{\frac{\gamma}{R}}M(1+\frac{\gamma-1}{2}M^2)^-\frac{\gamma+1}{2(\gamma-1}
when M becomes 1, the flow is considered choked. The equation becomes:
mdot = \frac{A*p_t}{\sqrt{T_t}}\sqrt{\frac{\gamma}{R}}(1+\frac{\gamma-1}{2})^-\frac{\gamma+1}{2(\gamma-1}
With some basic assumed values at sea level, the maximum mass air flow through the restrictor can be found:
[put table here]
Plugging these into the equation above yields a steady state mass flow rate of 0.074 kg air per second
If we assume an AFR of 13.1 (typical lambda for high torque for NA engines[citation needed]), and a Q_LHV of 46 MJ/kg [citation needed], the mass air flow yields a power limit of 265.5 kW or 356 hp total energey output. If the thermal efficiency of the engine is assumed to be a nominal 33%, the maximum available mechanical power is 88.5 kW or 118 horsepower with 100% volumetric efficiency.

throttle control

throttle form factors

cabling

ETC

Manifold design

The intake manifold typically runs from the plenum to the cylinder heads / air intake ports on the engine. It's design can be adjusted to increase performance using the tuning methods below. The manifold also contains ports for the fuel injectors.

Form factors

tuning (ram, helmholtz)

Tuning takes two forms for the intake manifold: the first is in modifying the length of the manifold (ram tuning) and the second is in modifying the shape of the manifold (including Helmholtz resonators).



The basic principle behind ram tuning is that a cylinder intakes air at a particular frequency, i.e. a cylinder only takes in air for a quarter of a four stroke cycle, meaning that there is a stop-starting of the flow of air into the cylinder. This occurs at a frequency dependent on the rpm of the engine, hence ram tuning is done to optimise performance at a selected rpm. The way in which it is implemented is to modify the length of the manifold such that the pressure wave formed on each cycle travels along the manifold and is reflected back, arriving just as the cylinder completes the cycle and takes in its next lot of air. This means that the pressure at the inlet will be higher whenever the engine needs air, giving better volumetric efficiency for the engine.


Helmholtz resonators work by having a thin neck followed by an open cavity attached to the engine's intake. Their design result in low pressure at the neck, sucking in more air, and resulting in higher pressure air in the cavity, which can then feed the engine.

trade-offs

mounting

Supercharging/Turbocharging

theory

trade-offs

manifold design