Unsteady filling of a vacuum tank

[whiteskulleton]

TL;DR Summary

A 60 liter vacuum tank with an initial vacuum of -509 mmHg (251 mmHg absolute) is opened up to the outside air and flows through a 6.5 mm hole.
What is the equation that represents the pressure in terms of time?
What is the equation that represents volumetric flow-rate into the tank in terms of time?

I have a vacuum tank at work that I am trying to determine the flow rate and pressure curve of when I open up the tank and I just cannot figure these equations out.

Environment: average office space
Atmospheric pressure: 29.92 inHg (per weather information)
Temperature: 72°F

Tank info:
Material: Stainless steel
Tank capacity: 60L (I measured it to be 59.5 liters)
Initial vacuum: -509 mmHg (251 mmHg absolute)
Entrance hole diameter: 6.5 mm

Thermodynamics isn't my strong suit (vibrations and dynamics are). After going back through my thermodynamics and fluid dynamics I'm still having problems. So I ran a test on it to see what the real world values were. I used my iPhone and filmed the pressure gauge in slow motion as I opened the tank up. I found that the pressure rose in a very linear manner (R^2=0.995) in the first 4.5 seconds with a slope of 10165 pascals/second. If I take the partial derivative of PV=mRT I get, dm/dt = dp/dt * V/(RT). Plugging in the values above I get the experimental mass flow rate of 10165*0.059528/(287*294.261) = 0.0072 kg/second. That's the mass flow rate but how do I get the volumetric flow-rate? I'm making the assumption that the air is compressing and then expanding which changes the density of the air. So I don't know what the density of the air is entering the tank otherwise I would just divide the mass flow rate by the density to get the volumetric flow rate.

I was also making the assumption that the process was isothermal but then I stumbled upon this:
http://web.mit.edu/16.unified/www/FALL/thermodynamics/notes/node17.html#fig0:TankFilling
which says that the air would have an increase in temperature of at least 200°F... that sounds pretty insane which means that I also have to factor in heat transfer?

I need help of understanding the physics at play here.

 

[Chestermiller]

There are 2 parts to this. First, to use thermodynamics to get the final conditions in the tank. Second, to analyze the fluid flow aspect of the problem. You certainly won't be able to do the second part without first being able to do the first part. So, my advice is to first determine the final conditions in the tank.

Assume the system is adiabatic so that you don't need to deal with heat transfer between the gas and the tank. Let u be the internal energy per mole of the gas in the tank in the final state, and let $u_0$ be the internal energy per mole of the gas in the initial state. Let $n_0$ be the number of moles of gas in the tank in the initial state and let $\Delta n$ be the number of moles of gas entering the tank between the initial and final states. Let $h_{in}$ be the enthalpy per unit mass of gas entering the tank. In terms of only these parameters, please write down the open system (control volume) version of the first law of thermodynamics applicable to the change in this system between the initial and final states.

 

[whiteskulleton]

Thanks for the reply. I'm guessing that this diagram is a correct representation of the system?

Based on the first law of thermodynamics you get

Since you are saying that I should assume that it is adiabatic, that means that there is no heat transfer into the system so Q=0. Since there is no kinetic or potential energy of the final state, all that is left is internal energy. Finally, there is work done on the system that is equal to the pressure times the volume. Thus, the equation should simplify down to:

Where M is the molar mass of air
If I use the equations for internal energy of air and enthalpy of air and plug them in I would get

If I plug in the values I get the final temp. of the system equal to 413.5 Kelvin which is 283.73°F and that seems unlikely which leads me to believe that I made a mistake.

 

[Chestermiller]

Here's my starting analysis. Please see if it makes sense to you based on the open-system version of the 1st law of thermodynamics: $$(n_i+\Delta n)u_f-u_in_i=\Delta nh_{in}$$where $$u_f=u_i+C_v(T_f-T_i)$$and, since the temperature outside is equal to the initial temperature inside,$$h_{in}=u_i+P_{atm}v_{atm}=u_i+RT_i$$

 

[Chestermiller]

I was mistaken about something. This problem doesn't only have to be treated as an open-system problem. It can also be treated using the closed system version of the 1st law. Here is the development using that approach.

Again, let $n_i$ represent the initial number of moles in the tank, and let $\Delta n$ again represent the number of moles forced into the tank by the outside atmosphere. Then, our closed system will be comprised of these $n_i+\Delta n$ moles. The change in internal energy of these moles of air is $(n_i+\Delta n)(u_f-u_i)$. The work done by this combined system on the surrounding air is $W=p_{atm}\Delta V=-\Delta n RT_i$. So, from the closed system version of the first law, we have: $$(n_i+\Delta n)(u_f-u_i)=-W=\Delta nRT_i$$This is the same result as that produced by the open system analysis of post #4.

Basically, your analysis was pretty close to correct to begin with. You just forgot to take into account the gas that was originally present in the tank.

 

[Chestermiller]

When applying this analysis to your problem, I get a final temperature of 198 F. See if you can get $T_f/T_i$ in terms of $\gamma$ and $p_i/p_{atm}$ and then see if you can duplicate this result.

 

[whiteskulleton]

So here are my equations

And here are the initial conditions

You can solve Eq. 2,4,7 outright getting:

I then solve for n in equation 5. Plug that into equation 6. I then plug equation 6 into equation 3 and also plug equation 1 into equation 3 and then solve for the final temperature. I get

Which is the same as what you got. Thus, that means that the temperature jumped over 100F?!
I just measured the surface area of the tank and got about 1.006 m^2. I also learned that the tank material was aluminum so I'm guessing aluminum 6061. If I put my hand on the tank while this is occurring, I would feel some heat correct? Even if I were to calculate the heat flux, I don't have enough real world experience to determine what that feels like.

Anyway, what would be next for calculating the transient information? Based on the experimental data, I got the fill time to be exactly 8.76 seconds and found that data followed the curve

with an average relative error of 0.3622 %
Where y is the pressure in the tank and x is the time.

 

[whiteskulleton]

I finally was able to simplify the equation down:

Now, you did also tell me to add gamma to the equation and simplify. Thus,

 

[Chestermiller]

I finally was able to simplify the equation down:
View attachment 243917
Now, you did also tell me to add gamma to the equation and simplify. Thus,
View attachment 243922

Very nicely done.

To do the transient problem, we need to have a relationship between the pressure drop between inside and outside the tank and the molar flow rate through the orifice. From the information presented in Transport Phenomena by Bird, Stewart, and Lightfoot, it is not clear what the appropriate functional form should be employed for an orifice through which a compressible gas is flowing. So, I'm going to propose a functional form, and we can see how well that works:
$$(p_{atm}-p)=\frac{k}{2\bar{\rho}}\frac{\dot{m}^2}{A^2}$$ where A is the cross sectional area of the hole, $\bar{\rho}$ is the average density ($=\frac{M}{2R}\left[\frac{p_{atm}}{T_{atm}}+\frac{p}{T}\right]$), $\dot{m}=\dot{n}M$ is the mass flow rate through the orifice, and k is a (dimensionless) constant on the order of unity, with $\dot{n}$ equal to the molar flow rate and M representing the molecular weight of air. This equation is dimensionally correct and resembles to some extent the equations recommended in Bird, et al for flow through valves and orifices.

So, for a given pressure difference between the outside air and the air in the tank, we can use this equation to calculate the molar flow rate. The constant k will be an adjustable parameter that can be used in tuning the model.

 

[whiteskulleton]

I just discovered something very interesting. I opened up my Fundamentals of Fluid Mechanics Seventh Edition textbook from college, turned to the last chapter about compressible flow and low and behold, all the equations that I just listed out were there. That would have helped significantly and saved me a lot of time if I found it earlier. However, further in the chapter, I did find an example problem in the textbook called Isentropic Flow in a Converging Duct. It states:
A converging duct passes air steadily from standard atmospheric conditions to a receiver pipe as illustrated:

The throat (minimum) flow cross-sectional area of the converging duct is 1e-4 m^2. The receiver is (a) 80 kPa (abs), (b) 40 kPa (abs)

They then walk you through the problem. The really interesting part comes from when it says:
If p_receiver < p*, then p_throat = p* and the flow is choked. Where:

Thus, the flow at the throat is traveling at the speed of sound!

Now, obviously, my problem isn't steady flow. However, the cross section of the orifice in my experiment is 3.318e-5 m^2 and the tank's initial pressure is 33.4 kPa (abs), both of which are smaller than the example problem. Does that mean that the initial speed of the air in my experiment was going at the speed of sound?! If so, that's awesome! That would also mean that the initial pressure values that I read were not correct because you can't measure the pressure of a system upstream of a flow that is traveling at the speed of sound. Would you concur with this evaluation?

 

[Chestermiller]

View attachment 243906

Can you please post a graph of this? Thanks.

 

[Chestermiller]

I just discovered something very interesting. I opened up my Fundamentals of Fluid Mechanics Seventh Edition textbook from college, turned to the last chapter about compressible flow and low and behold, all the equations that I just listed out were there. That would have helped significantly and saved me a lot of time if I found it earlier. However, further in the chapter, I did find an example problem in the textbook called Isentropic Flow in a Converging Duct. It states:
A converging duct passes air steadily from standard atmospheric conditions to a receiver pipe as illustrated:
View attachment 243929
The throat (minimum) flow cross-sectional area of the converging duct is 1e-4 m^2. The receiver is (a) 80 kPa (abs), (b) 40 kPa (abs)

They then walk you through the problem. The really interesting part comes from when it says:
If p_receiver < p*, then p_throat = p* and the flow is choked. Where:
View attachment 243932
Thus, the flow at the throat is traveling at the speed of sound!

Now, obviously, my problem isn't steady flow. However, the cross section of the orifice in my experiment is 3.318e-5 m^2 and the tank's initial pressure is 33.4 kPa (abs), both of which are smaller than the example problem. Does that mean that the initial speed of the air in my experiment was going at the speed of sound?! If so, that's awesome! That would also mean that the initial pressure values that I read were not correct because you can't measure the pressure of a system upstream of a flow that is traveling at the speed of sound. Would you concur with this evaluation?

The smaller the hole, the more frictional dissipation. By assuming that the gas enters the tank with the same enthalpy as outside, we have been saying that frictional dissipation is the main contributor to the pressure decrease through the hole. We can check afterwards to ascertain whether or not the flow would become sonic and choke. I don't think this will be the case.

 

[Chestermiller]

Your data suggests that, at least initially, the flow might have been close to sonic. Just take the number of moles, divide by the initial molar volume (minimum), the total time, and the hole area. This comes out to about 200 m/s. This doesn't take into account for the fact that the initial molar flow rate was higher than the average molar flow rate.

 

[whiteskulleton]

Can you please post a graph of this? Thanks.

I used this website:
https://planetcalc.com/5992/
It's a very quick way to run different regressions to determine the best one.

X-Data:

0.013020875 0.108853125 0.17968575 0.308333375 0.475516125 0.592181625 0.688014 0.79634625 0.867178875 0.983844375 1.067176875 1.183842375 1.254675 1.375507125 1.4713395 1.588005 1.69633725 1.775503125 1.89633525 1.967167875 2.100499875 2.1713325 2.275498125 2.358830625 2.500495875 2.54632875 2.667160875 2.74632675 2.867158875 2.9379915 3.054657 3.1379895 3.258821625 3.350487375 3.44631975 3.554652 3.64631775 3.75465 3.8379825 3.942148125 4.0379805 4.133812875 4.242145125 4.333810875 4.42964325 4.5379755 4.62964125 4.72964025 4.8379725 4.92963825 5.025470625 5.121303 5.225468625 5.321301 5.42963325 5.521299 5.61296475 5.725463625 5.817129375 5.925461625 6.008794125 6.11295975 6.208792125 6.3046245 6.40962275 6.50120525 6.59828775 6.70637025 6.796875125 6.89537425 6.98970675 7.08678925 7.18937175 7.28645425 7.38078675 7.47236925 7.58045175 7.67753425 7.76911675 7.86619925 7.97428175 8.102314625 8.160647375 8.385645125 8.55385275 8.766350625

Y-Data:

33997.20395 34930.46053 35997.03947 36930.29605 39463.42105 40396.67763 41596.57895 42663.15789 43729.73684 44929.63816 45996.21711 46796.15132 47596.08553 48662.66447 49462.59868 50662.5 51595.75658 52529.01316 53595.59211 54662.17105 55595.42763 56528.68421 57595.26316 58528.51974 59595.09868 60528.35526 61461.61184 62394.86842 63594.76974 64528.02632 65594.60526 66661.18421 67594.44079 68527.69737 69594.27632 70794.17763 71860.75658 72660.69079 73727.26974 74660.52632 75460.46053 76393.71711 77193.65132 78126.90789 78926.84211 79726.77632 80526.71053 81193.32237 81993.25658 82793.19079 83593.125 84259.73684 85059.67105 85726.28289 86392.89474 87059.50658 87726.11842 88392.73026 89059.34211 89859.27632 90392.56579 90925.85526 91592.46711 92125.75658 92659.04605 93192.33553 93858.94737 94258.91447 94792.20395 95325.49342 95725.46053 96258.75 96658.71711 97192.00658 97458.65132 97858.61842 98258.58553 98658.55263 98925.19737 99325.16447 99591.80921 99858.45395 100258.4211 100658.3882 101058.3553 101325

Attached is the raw data in excel format for your convenience.

 

[Chestermiller]

Thanks. This is great. You can use this to calibrate the model. I will outline how later.

 

[whiteskulleton]

Just found the latex info, lol.
So you are proposing the following equation
$$(p_{atm}-p)=\frac{k}{2\bar{\rho}}\frac{\dot{m}^2}{A^2}$$
Where
$$\bar{\rho}=\frac{M}{2R}\left[\frac{p_{atm}}{T_{atm}}+\frac{p}{T}\right]$$
I'm assuming $T$ is the final temperature and $p$ is the initial pressure correct? Plugging in the values, I get $\bar{\rho}=0.757 \frac{kg}{m^3}$
Solving for $\dot{m}$ in the first equation I get $$\dot{m}=\sqrt{1.132\mathrm{x}10^{-7} k}$$$$\dot{n}=1.161\mathrm{x}10^{-5}\sqrt{k}=1.161\mathrm{x}10^{-5}k$$
Now, I'm a little confused about the equation for finding the initial velocity. I'm confused on what you mean by the initial molar volume. My best guess is that it is $\Delta V$ and so $$\Delta V=\frac{\Delta n R T_i}{P_{atm}}=0.02848 \mathrm{m}^3$$$$\bar{V}=\frac{\Delta n}{\Delta V t_{total}A}=141.89\frac{\mathrm{m}}{\mathrm{s}}\mathrm{?}$$

 

[Chestermiller]

Just found the latex info, lol.
So you are proposing the following equation
$$(p_{atm}-p)=\frac{k}{2\bar{\rho}}\frac{\dot{m}^2}{A^2}$$

This is just a tentative choice until we see how well it fits your data.

Where
$$\bar{\rho}=\frac{M}{2R}\left[\frac{p_{atm}}{T_{atm}}+\frac{p}{T}\right]$$
I'm assuming $T$ is the final temperature and $p$ is the initial pressure correct?

T and p are supposed to be the temperature and pressure at time t. Henceforth, u, n, T, and p are the internal energy per mole, the number of moles, the temperature, and the pressure at time t.

In our previous development, we showed that $$n(u-u_i)=(n-n_i)RT_i$$ where $T_i$ is atmospheric temperature. This leads to the equation: $$nC_v(T-T_i)=(n-n_i)RT_i$$which then yields:
$$T=T_i\left(\gamma-(\gamma-1)\frac{n_i}{n}\right)\tag{1}$$

The pressure in the tank at any time can now be determined by the ideal gas law:
$$p=\frac{nRT}{V_T}$$If we substitute the temperature T from Eqn. 1 into this relationship, we obtain: $$p=\frac{RT_i}{V_T}(\gamma n-(\gamma-1)n_i)\tag{2}$$This equation indicates that the pressure is a linear function of the number of moles in the tank. We can differentiate Eqn. 2 with respect to time to obtain the rate of change of pressure in the tank as a function of the rate of change in the number of moles: $$\frac{dp}{dt}=\frac{\gamma RT_i}{V_T}\frac{dn}{dt}$$This can be used to express the rate of change of the number of moles in the tank in terms of the rate of change of pressure: $$\frac{dn}{dt}=\frac{V_T}{\gamma RT_i}\frac{dp}{dt}\tag{3}$$And, it also follows that the mass rate of flow through the hole is given by:
$$\dot{m}=\frac{V_TM}{\gamma RT_i}\frac{dp}{dt}\tag{4}$$

In your experiments, you found that the initial rate of pressure increase in the tank is about 75 mmHg/sec = 0.1 atm /sec. From Eqns. 3 and 4, what does this give you for the molar flow rate and the mass flow rate? This should also provide us enough information to estimate the value of the dimensionless constant k in the flow equation. What do you get for k? (I estimated a value of about 4.5)

 

[Chestermiller]

See this article: https://en.wikipedia.org/wiki/Orifice_plate

I like the pressure-difference vs flow relationship presented in this reference better than the one I proposed in post #16, because the effect of compressibility is more fundamentally based. So I recommend switching to it:
$$\dot{m}=C\epsilon A \sqrt{2\rho_{atm}(p_{atm}-p)}\tag{1}$$
where C is the discharge coefficient of the hole and $\epsilon$ is the correction factor for compressibility: $$\epsilon=0.649+0.351\left(\frac{p}{p_{atm}}\right)^{1/\gamma}\tag{2}$$
This relationship can readily be manipulated into a form very similar to the one I proposed.

Your experimental data on the initial rate of decrease of pressure can be used to determine the value for the discharge coefficient C. I calculate a value of 0.48. What do you obtain?

 

[whiteskulleton]

Let's try this again.
$$\bar{\rho}=\frac{M}{2R}\left[\frac{p_{atm}}{T_{atm}}+\frac{p}{T}\right] $$
Since $\bar{\rho}$ is the average density, then we need to plug in the initial conditions $p=33.463\mathrm{ kPa}$ and $T=295.372\mathrm{ K}$. $\bar{\rho}=0.7950\frac{\mathrm{kg}}{\mathrm{m}^3}$
$$\frac{dn}{dt}=\frac{V_T}{\gamma RT_i}\frac{dp}{dt} $$
For the initial conditions,
$$\frac{dp}{dt}=10.496\frac{\mathrm{kPa}}{\mathrm{s}}\mathrm{; }\frac{dn}{dt}=0.0001818\frac{\mathrm{kmol}}{\mathrm{s}}\mathrm{; }\dot{m}=0.005265\frac{\mathrm{kg}}{\mathrm{s}}$$
Plugging all the values into the equation:
$$(p_{atm}-p)=\frac{k}{2\bar{\rho}}\frac{\dot{m}^2}{A^2}$$
and solving for $k$, I get $k=0.00428$. So maybe you forgot a 0?

 

[Chestermiller]

Let's try this again.
$$\bar{\rho}=\frac{M}{2R}\left[\frac{p_{atm}}{T_{atm}}+\frac{p}{T}\right] $$
Since $\bar{\rho}$ is the average density, then we need to plug in the initial conditions $p=33.463\mathrm{ kPa}$ and $T=295.372\mathrm{ K}$. $\bar{\rho}=0.7950\frac{\mathrm{kg}}{\mathrm{m}^3}$
$$\frac{dn}{dt}=\frac{V_T}{\gamma RT_i}\frac{dp}{dt} $$
For the initial conditions,
$$\frac{dp}{dt}=10.496\frac{\mathrm{kPa}}{\mathrm{s}}\mathrm{; }\frac{dn}{dt}=0.0001818\frac{\mathrm{kmol}}{\mathrm{s}}\mathrm{; }\dot{m}=0.005265\frac{\mathrm{kg}}{\mathrm{s}}$$
Plugging all the values into the equation:
$$(p_{atm}-p)=\frac{k}{2\bar{\rho}}\frac{\dot{m}^2}{A^2}$$
and solving for $k$, I get $k=0.00428$. So maybe you forgot a 0?

I confirm the mass flow rate and the density. Did you use Pa (not kPa) for pressure?

 

[Chestermiller]

We're almost done now. If we combine Eqn. 4 from post #17 with Eqn. 1 from post #18, we obtain:

$$\frac{dp}{dt}=\frac{\gamma RT_{atm}}{MV_T}C\epsilon A \sqrt{2\left(\frac{p_{atm}M}{RT_{atm}}\right)(p_{atm}-p)}\tag{1}$$with $$\epsilon=0.649+0.351\left(\frac{p}{p_{atm}}\right)^{1/\gamma}\tag{2}$$
The value of $\epsilon$ over the time for filling varies from 0.8 initially to 1.0 finally. If we substitute the average value of $\epsilon$, $\bar{\epsilon}=0.9$, into Eqn. 1, we can integrate this equation analytically to solve for the time to fill. See if you can do this. Based on this solution, I obtained a time to fill of about 9.2 sec.

To be more precise, the equation can be integrated numerically. Before doing this however, I would reduce the equation to dimensionless form.

 

[Chestermiller]

I would use the following dimensionless parameters:
$$\phi=1-\frac{p}{p_{atm}}$$
and
$$\tau=\frac{Av_s\sqrt{2\gamma}}{V_T}Ct$$where $v_s$ is the speed of sound in air:
$$v_s=\sqrt{\frac{\gamma RT_{atm}}{M}}$$

 

[Chestermiller]

With the substitutions given in the previous post, the differential equation for the dimensionless pressure variation with dimensionless time becomes:

$$\frac{d\phi}{d\tau}=-\left[0.649+0.351(1-\phi)^{1/\gamma}\right]\sqrt{\phi}$$subject to the initial condition $$\phi(0)=1-\frac{p_i}{p_{atm}}$$

 

[whiteskulleton]

With the substitutions given in the previous post, the differential equation for the dimensionless pressure variation with dimensionless time becomes:

$$\frac{d\phi}{d\tau}=-\left[0.649+0.351(1-\phi)^{1/\gamma}\right]\sqrt{\phi}$$subject to the initial condition $$\phi(0)=1-\frac{p_i}{p_{atm}}$$

Your starting to reach the limits of my knowledge here with that first-order nonlinear differential equation.

What I'm pretty sure of, is that the flow is a choked flow from $p(0)<p<53530.58\mathrm{Pa}$ which means that the mass flow rate is constant and so
$$\dot{m}=C_dA\sqrt{\gamma \rho_{atm}P_{atm}\left (\frac{2}{\gamma+1}\right )^{\frac{\gamma+1}{\gamma-1}}}$$$$\dot{m}=0.007902C_d$$From the experiment $P=53530.58$ @ $t=1.896335$ so:
$$\dot{m}=\frac{V_TM}{\gamma RT_i}\frac{dp}{dt}=\frac{V_TM}{\gamma RT_i}\frac{p(1.896)-p_i}{1.896-0}=0.005326\frac{\mathrm{kg}}{\mathrm{s}}$$$$C_d=0.6740$$

 

[Chestermiller]

Your starting to reach the limits of my knowledge here with that first-order nonlinear differential equation.

What I'm pretty sure of, is that the flow is a choked flow from $p(0)<p<53530.58\mathrm{Pa}$ which means that the mass flow rate is constant and so
$$\dot{m}=C_dA\sqrt{\gamma \rho_{atm}P_{atm}\left (\frac{2}{\gamma+1}\right )^{\frac{\gamma+1}{\gamma-1}}}$$$$\dot{m}=0.007902C_d$$From the experiment $P=53530.58$ @ $t=1.896335$ so:
$$\dot{m}=\frac{V_TM}{\gamma RT_i}\frac{dp}{dt}=\frac{V_TM}{\gamma RT_i}\frac{p(1.896)-p_i}{1.896-0}=0.005326\frac{\mathrm{kg}}{\mathrm{s}}$$$$C_d=0.6740$$

Let's try it both ways and see how the results compare with the data.

 

[whiteskulleton]

Here is the procedure that I used to get the governing equation:
From post #24 and the equation from the Wikipedia article
$$\dot{m}(t)=\left\{\begin{matrix}
0.007902C_d & \textrm{if } 0\leq t\leq 1.8963\\
C_dA \sqrt{2\, \rho_1\, p_{atm}\left ( \frac{\gamma}{\gamma-1} \right )\left [ \left ( \frac{p(t)}{p_{atm}} \right )^\frac{2}{\gamma}-\left ( \frac{p(t)}{p_{atm}} \right )^\frac{\gamma+1}{\gamma} \right ]} & \textrm{if }1.8963< t
\end{matrix}\right. \tag{3}$$$$C_d=0.6740$$
I then plug the pressure from the experimental data into the piecewise function above in excel to get the mass flow rate.

I then get the mass at each data point by doing integration by the trapezoidal rule
$$\sum_{n=1}^{\infty}m_n(t_n)=\frac{\dot m(t_n)-\dot m(t_{n-1})}{2(t_n-t_{n-1})}+m(t_{n-1})\tag{4}$$From post #7
$$m_0=n_iM=\frac{P_iV_TM}{RT_i}=0.02350\, \textrm{kg}\tag{5}$$
I then calculate the pressure at each data point using equation 2 from post 17:
$$p=\frac{RT_i}{V_T}(\gamma n-(\gamma-1)n_i)\tag{6}$$
$$\sum_{n=1}^{\infty}p_n(t_n)=\frac{RT_i}{V_T}(\gamma \frac{m_n(t_n)}{M}-(\gamma-1)\frac{m_0}{M})\tag{7}$$Finally, I look at the percent error at each data point to see how well this model fits to the experimental data:
$$\textrm{% Error}=\left |\frac{p_n(t_n)-p_{exp}(t_n)}{p_{exp}(t_n)} \right |\cdot 100$$
Looking at the data, I got the max error to be 2.62% with an average of 1.064%. Thus, I feel that these equations accurately model the experimental data. I did try the other equation that you recommended with the expansibility factor but it lead to more error.
Thus, the governing equations for $p<53530.58\mathrm{Pa}$:
$$\frac{dm}{dt}=C_dA\sqrt{\gamma \rho_{atm}P_{atm}\left (\frac{2}{\gamma+1}\right )^{\frac{\gamma+1}{\gamma-1}}}\tag{8}$$Integrating and plugging $m_0$ from eq. 5 into yields:
$$m(t)=C_dA\sqrt{\gamma \rho_{atm}P_{atm}\left (\frac{2}{\gamma+1}\right )^{\frac{\gamma+1}{\gamma-1}}}t+\frac{P_iV_TM}{RT_i}\tag{9}$$ Which is then put into equation 6 giving the final governing equation for $p<53530.58\mathrm{Pa}$:
$$p(t)=\frac{RT_i}{V_T}\left (\frac{\gamma C_dA}{M}\sqrt{\gamma \rho_{atm}P_{atm}\left (\frac{2}{\gamma+1}\right )^{\frac{\gamma+1}{\gamma-1}}}t+\frac{\gamma P_iV_T}{RT_i}-(\gamma-1)n_i \right )\tag{10}$$ To get the other half, we have to plug in the other equation but that is a function of pressure and I'm not quite sure how to integrate that.

Starting this experiment, I had no idea the complexity involved with finding the governing equations and thus far it has been an amazing learning experience.

 

[whiteskulleton]

This sort of brings me to the next real world application. We are testing the holding force of suction cups using this tank. The standard vacuum pressures that we recommend should be above 40% vacuum or $p<60795\,\mathrm{Pa(abs)}$. We test the suction cups by connecting the tank to a pressure regulator and then slowly decreasing the pressure until the suction cup drops a known weight. The relationship between holding force and pressure is linear. However, if the surface that the suction cup is holding on to is cardboard, there is a leakage rate. What we are trying to do is figure out the pressure drop as a function of leakage rate of different surfaces. I plan on running a test in the next few days where I connect the suction cup directly to the tank and to a known weight in a cardboard box and then let the tank drain drain until the box falls. Since the pressure of test will be less than 53530 kPa (abs), that should mean that the flow is throttled as the leakage rate is significantly less than this past experiment I ran and thus means that the leakage area is less than the tubing area. Or $A_L<A$.

 

[JBA]

With respect to the above, I have created the below graph for the filling mass flow vs tank pressure for tank pressures from 4.7 to 13.7 psia (the same graph with more refined values can be provided if desired) that illustrates the two conditions, sonic and subsonic nozzle flow that exist for this problem. This graph does not necessarily reflect the actual rates because, for lack of a confirmed value, it is for a nozzle coefficient of "1.0" (but I can revise it for any other coefficient you might desire). Because of the wide range of pressure differentials during the filling both of the above flow conditions that have substantially different profiles exist during the filling and make developing an accurate single curve fitting difficult. In such cases, for programming purposes, I have resorted to breaking the total curve into separate sonic and subsonic curves using the sonic pressure ratio for the gas as an (if,then,or value) function to select the appropriate curve for for a curve fitting for each flow region.
The excel program I use to obtain the graph's values calculates the mass flow for a Pin air of 14.7 psia & 70°F (R critical = .5283) for the values for each tank pressure point and I used those to develop the shown graph (the program actually calculates values for both regions simultaneously and then uses the (if, then,or) function to present a final value selected.

P tank (psia)	lb/sec (lb/sec)
4.7​	0.0175​
5.7​	0.0175​
6.7​	0.0175​
7.7​	0.0175​
8.7​	0.0174​
9.7​	0.0168​
10.7​	0.0159​
11.7​	0.0144​
12.7​	0.0123​
13.7​	0.0091​

 

[Chestermiller]

Here is the procedure that I used to get the governing equation:
From post #24 and the equation from the Wikipedia article
$$\dot{m}(t)=\left\{\begin{matrix}
0.007902C_d & \textrm{if } 0\leq t\leq 1.8963\\
C_dA \sqrt{2\, \rho_1\, p_{atm}\left ( \frac{\gamma}{\gamma-1} \right )\left [ \left ( \frac{p(t)}{p_{atm}} \right )^\frac{2}{\gamma}-\left ( \frac{p(t)}{p_{atm}} \right )^\frac{\gamma+1}{\gamma} \right ]} & \textrm{if }1.8963< t
\end{matrix}\right. \tag{3}$$$$C_d=0.6740$$
I then plug the pressure from the experimental data into the piecewise function above in excel to get the mass flow rate.

I then get the mass at each data point by doing integration by the trapezoidal rule
$$\sum_{n=1}^{\infty}m_n(t_n)=\frac{\dot m(t_n)-\dot m(t_{n-1})}{2(t_n-t_{n-1})}+m(t_{n-1})\tag{4}$$From post #7
$$m_0=n_iM=\frac{P_iV_TM}{RT_i}=0.02350\, \textrm{kg}\tag{5}$$
I then calculate the pressure at each data point using equation 2 from post 17:
$$p=\frac{RT_i}{V_T}(\gamma n-(\gamma-1)n_i)\tag{6}$$
$$\sum_{n=1}^{\infty}p_n(t_n)=\frac{RT_i}{V_T}(\gamma \frac{m_n(t_n)}{M}-(\gamma-1)\frac{m_0}{M})\tag{7}$$Finally, I look at the percent error at each data point to see how well this model fits to the experimental data:
$$\textrm{% Error}=\left |\frac{p_n(t_n)-p_{exp}(t_n)}{p_{exp}(t_n)} \right |\cdot 100$$
Looking at the data, I got the max error to be 2.62% with an average of 1.064%. Thus, I feel that these equations accurately model the experimental data. I did try the other equation that you recommended with the expansibility factor but it lead to more error.
Thus, the governing equations for $p<53530.58\mathrm{Pa}$:
$$\frac{dm}{dt}=C_dA\sqrt{\gamma \rho_{atm}P_{atm}\left (\frac{2}{\gamma+1}\right )^{\frac{\gamma+1}{\gamma-1}}}\tag{8}$$Integrating and plugging $m_0$ from eq. 5 into yields:
$$m(t)=C_dA\sqrt{\gamma \rho_{atm}P_{atm}\left (\frac{2}{\gamma+1}\right )^{\frac{\gamma+1}{\gamma-1}}}t+\frac{P_iV_TM}{RT_i}\tag{9}$$ Which is then put into equation 6 giving the final governing equation for $p<53530.58\mathrm{Pa}$:
$$p(t)=\frac{RT_i}{V_T}\left (\frac{\gamma C_dA}{M}\sqrt{\gamma \rho_{atm}P_{atm}\left (\frac{2}{\gamma+1}\right )^{\frac{\gamma+1}{\gamma-1}}}t+\frac{\gamma P_iV_T}{RT_i}-(\gamma-1)n_i \right )\tag{10}$$ To get the other half, we have to plug in the other equation but that is a function of pressure and I'm not quite sure how to integrate that.

Starting this experiment, I had no idea the complexity involved with finding the governing equations and thus far it has been an amazing learning experience.

I would have done this somewhat differently. From our previous development, you have an equation for the mass flow rate in terms of the rate of change of pressure given by $$\dot{m}=\frac{V_TM}{\gamma RT_i}\frac{dp}{dt}$$ So you could substitute this for the mass flow rate in your flow equation and obtain a differential equation entirely in terms of the pressure, with the time derivative of pressure directly expressed as a function of pressure itself. You could then solve this ordinary differential equation numerically (say by forward Euler) to obtain the pressure as a function of time. You could then compare the entire curve with the experimental data.

You have split the behavior into two parts, representing the initial sonic part and the subsequent sub-sonic part. And you have used the theoretical equations in Wiki for determining the mass flow rate. I prefer working with the ISO standards recommendations (approximations) because they have extensively been applied and validated in practice. I also like the idea of using a continuous description of the compression parameter so that no judgments need to be made about when to switch from one representation to the other.

What I'm going to do is use Eqn. 1 and 2 in post #21 to solve for the pressure in your experiment as a function of time. I have already started doing this using a value of 0.48 for C, which was based on the initial rate of pressure decline from your data, together with a value for $\epsilon$ of 0.8 using Eqn. 2 for the initial conditions. This, of course, worked well at predicting the pressure variation at short times (< 2 seconds), but it deviated from the data a bit at larger times, and ended up predicting a filling time of about 11 seconds (compared to the observed value of about 9 seconds). My next iteration will be to use your value of 0.67 for C, and to adjust $\epsilon$ so it again matches the rate of pressure decrease at short times. To do this, I will have to modify the parameterization of the compression factor $\epsilon$ so that it matches properly at the two end points. The form I will be using will be:
$$\epsilon=\left[0.649+0.351\left(\frac{p}{p_{atm}}\right)^{1/\gamma}\right]^{2.5}\tag{2-mod}$$
Together with C = 0.67, this parameterization will match your "choked flow" mass flow rate at short times and will match the condition that, as p approaches atmospheric, $\epsilon$ approaches unity. With this change, I am confident that the model will do a much better job of matching the entire pressure profile as well as the fill time.

I'll keep you posted.

Chet

 

[Chestermiller]

I completed the model calculation I described in my previous post. The new calculation again matches the rate of pressure decline and choke mass flow rate at short times, but also matches the observed fill time of about 9 seconds. I'll present comparison graphs later.

Chet

 

[Chestermiller]

The circles are the experimental data. The line is the model calculation as I described in my most recent posts.

 

[whiteskulleton]

I just ran another test in the same exact geometry conditions as before. The starting pressure was at -510 mmHg or 33330 Pa(abs). However I stopped the flow suddenly at 57462 Pa(abs). It then dropped to a final pressure of 54929 Pa(abs). Since the change in pressure occurs in a closed system, it is an isochoric process. Thus:$$\frac{T_1}{P_1}=\frac{T_2}{P_2}$$ Solving gets me $T_1=309 \,K$. Based on the adiabatic assumption, the temperature of the air when I stopped it should be approximately 336 K. That's an error of 8.7%. Do you think that this is cause for concern for the models we made?

 

[Chestermiller]

I just ran another test in the same exact geometry conditions as before. The starting pressure was at -510 mmHg or 33330 Pa(abs). However I stopped the flow suddenly at 57462 Pa(abs). It then dropped to a final pressure of 54929 Pa(abs). Since the change in pressure occurs in a closed system, it is an isochoric process. Thus:$$\frac{T_1}{P_1}=\frac{T_2}{P_2}$$ Solving gets me $T_1=309 \,K$. Based on the adiabatic assumption, the temperature of the air when I stopped it should be approximately 336 K. That's an error of 8.7%. Do you think that this is cause for concern for the models we made?

What was the time interval over which the pressure dropped?

 

[JBA]

If using a adiabatic solution when filling from the 14.7 psia pressure air into the lower pressure tank there is a expansion cooling for that gas mass relative to the transitive pressure ratio during the fill. Only the air mass that is heated by the compression by using the initial 4.85 and final 14.7 pressures is the air mass in the vessel before filling can be this equation. The relative percentage of each gas mass and its BTU contribution must be used to determine the actual vessel air temperature of the mixture after filling.
The additional heat transfer into or out of the tank is transitive during the fill due the changing internal temperature as well and also dependent upon the fill time. This combination can lead to a significant difference between the calculated and actual finished contained air temperatures. The best method for determining a reasonably accurate final temperature is by measurement at the completion of your fill test.

I learned these lessons when responding to a request to develop a program that would "accurately determine the number of bottle fills of a given size and desired pressure from a supply tank of a given size and pressure" relative to accurate test results from multiple and consistent test fillings with accurate and calibrated instruments. In the end, the above combination of temperature factors for the bottles being filled defeated the project after some six months of intense work.

 

[Chestermiller]

If using a adiabatic solution when filling from the 14.7 psia pressure air into the lower pressure tank there is a expansion cooling for that gas mass relative to the transitive pressure ratio during the fill. Only the air mass that is heated by the compression by using the initial 4.85 and final 14.7 pressures is the air mass in the vessel before filling can be this equation. The relative percentage of each gas mass and its BTU contribution must be used to determine the actual vessel air temperature of the mixture after filling.

There is also significant viscous heating occurring in the air flow through the entrance hole, essentially the same as that present with the Joule Thomson effect. So even though the gas enters the tank at a lower pressure than atmospheric, its expansion cooling is fully offset by the viscous heating in flow through the hole, so that its temperature essentially does not change in passing through the hole. It then compresses within the tank, and its temperature rises as a result. This is the essence of the first law of thermodynamics analysis presented early in this thread. Either one accepts the first law of thermodynamics or one doesn't.

 

[JBA]

This is not consistent with the bottle temperatures in the prior project where the air was being injected into 14.7 psia & 54°F atmospheric pressure bottles and being increased to 4514.7 psia with only a consistent 102°F measured final temperature in testing and verified by an equally limited pressure drop upon cooling to ambient. See the below test data example which is consistent over multiple such fillings.

Pressure (psig)	Pressure (psia)	Temp (°F)
0	14.7	54
500	514.7	61
1000	1014.7	67.2
1500	1514.7	74
2000	2014.7	79.9
2500	2514.7	83.4
3000	3014.7	87.7
3500	3514.7	92.3
4000	4014.7	96.4
4500	4514.7	101.9

 

[Chestermiller]

This is not consistent with the bottle temperatures in the prior project where the air was being injected into 14.7 psia & 54°F atmospheric pressure bottles and being increased to 4514.7 psia with only a consistent 102°F measured final temperature in testing and verified by an equally limited pressure drop upon cooling to ambient. See the below test data example which is consistent over multiple such fillings.

Pressure (psig)	Pressure (psia)	Temp (°F)
0	14.7	54
500	514.7	61
1000	1014.7	67.2
1500	1514.7	74
2000	2014.7	79.9
2500	2514.7	83.4
3000	3014.7	87.7
3500	3514.7	92.3
4000	4014.7	96.4
4500	4514.7	101.9

I'm not familiar with the details of the experiment you describe, so I can't comment intelligently. But, if you can identify something wrong with how the first law of thermodynamics was applied (by two different members using two different equivalent versions of the first law) in the first several posts of the current thread to the problem at hand, please point it out.

 

[whiteskulleton]

I just ran the test again but this time filmed it. Below is the raw video. I don't have time right now to analyze and extract the data. It's filmed at 240 fps but I like to upload it and slow it down by 8x using this website:
https://ezgif.com/video-speed


Also, attached is a pdf of the geometry of the inside of the flow. That is, it's the geometry of the actual air itself. It looks like the pressure was stopped at -342 mmHg and then fell to -360 mmHg.

 

[Chestermiller]

COMPARISON OF EXPANDABILITY PARAMETERIZATIONS

My goal in the present post is to provide a comparison of the expandability parameterizations that we have been using in our models. This is to show that they are virtually indistinguishable.

Even though you didn't officially employ the expandability form of the equation in your model, it is possible to derive the expandability factor $\epsilon$ from your equations. For the choked case of $p/p_{atm}<0.528$, you employed $$\dot{m}=C_dA\sqrt{\gamma \rho_{atm}P_{atm}\left (\frac{2}{\gamma+1}\right )^{\frac{\gamma+1}{\gamma-1}}}$$We can show that this translates into an expandability factor of $$\epsilon=\sqrt{\frac{\gamma}{2}\left(\frac{2}{\gamma+1}\right)^{\frac{\gamma+1}{\gamma-1}}\frac{1}{\left(1-\frac{p}{p_{atm}}\right)}}$$

And for the non-choked case of $p/p_{atm}>0.528$, you used $$\dot{m}=C_dA \sqrt{2\, \rho_1\, p_{atm}\left ( \frac{\gamma}{\gamma-1} \right )\left [ \left ( \frac{p}{p_{atm}} \right )^\frac{2}{\gamma}-\left ( \frac{p}{p_{atm}} \right )^\frac{\gamma+1}{\gamma} \right ]}$$
This translates into an expandability factor of
$$\epsilon=\sqrt{\left(\frac{\gamma}{\gamma-1}\frac{(p/p_{atm})^{2/\gamma}-(p/p_{atm})^{(\gamma+1)/\gamma}}{1-(p/p_{atm))}}\right)}$$
The corresponding relationship I've been using over the full range of pressure ratios has been:
$$\epsilon=\left[0.649+0.351\left(\frac{p}{p_{atm}}\right)^{1/\gamma}\right]^{2.5}$$

I have made a plot of how closely these two parameterizations compare:

In the figure, the circles are the parameterization you have been using, involving the choked flow region, and the solid curve is the parameterization I have been using. As you can see, the match is remarkable. Both will result in an excellent fit to your experimental pressure vs time data (as we've already seen in post #31. An equally acceptable parameterization would be the simple linear fit $\epsilon=0.385+0.615p/p_{atm}$ which would again span both the choked and unchoked regions.

What do you think?

 

[JBA]

@Chestermiller, I continue to be astounded by the depth and width of your knowledge of the deep technical physics of many processes; and, in the event that we diverge on a subject, if ask by someone which path to take I would generally recommend that your's, by far, has the highest probability of being correct.

I find the above to be amazing. In all of my reviewing of reference texts available to me on the analysis and physics of fluid and gas flow the focus was on Bernoulli's equations and the standard array P/T = PT etc using k = 1.4 etc. I have never seen anything with as much depth as presented here. That is why for the majority of the thread I was satisfied to be a "fly on the wall" observer.

On the expansion cooling issue, after reviewing my prior project I realize there is a disconnect between that system and the one here with regard to expansion cooling of the source air being delivered to the tank. In this case, there is an infinite supply of ambient temperature air provided during the filling. In my tank to bottle filling project there is a finite initial high pressure supply in the supply tank. As a result, as that tank is depressurized it goes through and expansion cooling of the remaining air in the tank; and, therefore, the air delivered to the bottle is progressively colder as the filling progresses and it has nothing to do with the expansion thru the flow valve to the bottle. I also now realize, if the viscous heating you mentioned occurs, the delivered air can then be subject to compression heating from its initial feed reduced temperature, all of which is something I need to investigate.

At the same time, I still have a problem resolving the nozzle flow ΔT/ΔP first law issue simply because in years of flow testing, I have not observed the degree of temperature change the classical first law predicts; and, I am most experienced with pressures in the 1 to 10 thousand psig range where there are can be extreme ΔP changes, i.e. such as the 14.7 to 4500 psia compression as exists in the scuba filling tests or flowing valve and nozzle certification tests with the reverse condition.

I am not taking a hard stand on this issue, it is just that I am having difficulty reconciling my prior observations with the first law results.

Above you stated:

There is also significant viscous heating occurring in the air flow through the entrance hole, essentially the same as that present with the Joule Thomson effect. So even though the gas enters the tank at a lower pressure than atmospheric, its expansion cooling is fully offset by the viscous heating in flow through the hole, so that its temperature essentially does not change in passing through the hole.

I am really interested in being able to read any reference material that you may recommend that discusses this issue. I have not heard or read this before and all of my prior references have only made vague statements about the Joule Thomson effect and have never covered it to any depth.

 

[Chestermiller]

@Chestermiller, I continue to be astounded by the depth and width of your knowledge of the deep technical physics of many processes; and, in the event that we diverge on a subject, if ask by someone which path to take I would generally recommend that your's, by far, has the highest probability of being correct.

I find the above to be amazing. In all of my reviewing of reference texts available to me on the analysis and physics of fluid and gas flow the focus was on Bernoulli's equations and the standard array P/T = PT etc using k = 1.4 etc. I have never seen anything with as much depth as presented here. That is why for the majority of the thread I was satisfied to be a "fly on the wall" observer.

On the expansion cooling issue, after reviewing my prior project I realize there is a disconnect between that system and the one here with regard to expansion cooling of the source air being delivered to the tank. In this case, there is an infinite supply of ambient temperature air provided during the filling. In my tank to bottle filling project there is a finite initial high pressure supply in the supply tank. As a result, as that tank is depressurized it goes through and expansion cooling of the remaining air in the tank; and, therefore, the air delivered to the bottle is progressively colder as the filling progresses and it has nothing to do with the expansion thru the flow valve to the bottle. I also now realize, if the viscous heating you mentioned occurs, the delivered air can then be subject to compression heating from its initial feed reduced temperature, all of which is something I need to investigate.

At the same time, I still have a problem resolving the nozzle flow ΔT/ΔP first law issue simply because in years of flow testing, I have not observed the degree of temperature change the classical first law predicts; and, I am most experienced with pressures in the 1 to 10 thousand psig range where there are can be extreme ΔP changes, i.e. such as the 14.7 to 4500 psia compression as exists in the scuba filling tests or flowing valve and nozzle certification tests with the reverse condition.

I am not taking a hard stand on this issue, it is just that I am having difficulty reconciling my prior observations with the first law results.

Above you stated:

I am really interested in being able to read any reference material that you may recommend that discusses this issue. I have not heard or read this before and all of my prior references have only made vague statements about the Joule Thomson effect and have never covered it to any depth.

Thank you for your kind thoughts. A few years ago, another PF member and I were very puzzled about the Joule Thomson effect, and were trying to get an understanding of why, when an ideal gas experiences an adiabatic pressure drop in passing through a valve or porous plug, its enthalpy per unit mass and temperature do not change as a result of expansion cooling. So we collaborated on this and analyzed the problem in private conversations for several weeks. We finally came to the (correct) conclusion that the viscous heating was exactly cancelling out the expansion cooling.

In the case of an incompressible fluid that passes through a porous plug or valve, it experiences a temperature rise equivalent to the rate of frictional flow work done on the fluid divided by the product of mass flow rate and heat capacity. This is what happens when there is no expansion cooling. In both cases, the change in enthalpy per unit mass is equal to zero (neglecting changes in kinetic energy). The difference is in the equation of state for an incompressible fluid compared to and ideal gas. I hope that this helps.

I have never seen any discussion of these mechanistics in any treatment in the open literature. But I am fully confident that it is correct. I'll try to locate the original link to the thread where we reported back the results of our deliberations.

Chet

 

[Chestermiller]

Actually, this goes back to 2013 (has it really been that long ago) that Toolbox and I collaborated on this. Here is the link: https://www.physicsforums.com/threa...d-throttling-valves.67757/page-2#post-4328829 Post #37 presents the results of our deliberations.

 

[JBA]

Thank you for taking the time to review and reply to my extended post. I have read your summary report and while it does not provide any specific supporting analyses; and, because of my confidence in your rigorous approach to problem solving as well as the fact that I no longer have access to a required flow testing facility to investigate it in that manner I am fully prepared to accept the validity of your conclusions.

At the same time, I am afraid I am back again with my concerns on the 1st Law issue. This time it relates directly to the issue addressed in this thread as an example of my concerns.

Using this as an example, using the 1st Law equation as presented in post#8, I to calculate the final Tank temperature, ignoring tank heat transfer, to be as follows:

P i =	4.85​	psia
T I =	70​	°F
T I =	530​	°R
P f =	14.7​	psia
k air =	1.4​
T f =	655​	°R
T f =	281​	°F

Which would indicate that even with an large amount of Tank heat loss during the 9 sec filling time, there would be an additional amount of filling time required as the Tank consumed the air required to maintain its target 14.7 psia pressure level; or, if the fill valve were to be closed, a substantial post fill pressure drop would be expected as the tank cools to ambient temperature.

If you are willing to continue consuming your time with my ongoing inquiries I would really appreciate your feedback on this issue; if not, I fully understand because it getting to one of those extended "OK, but what about" situations.

Jack

 

[Chestermiller]

Thank you for taking the time to review and reply to my extended post. I have read your summary report and while it does not provide any specific supporting analyses; and, because of my confidence in your rigorous approach to problem solving as well as the fact that I no longer have access to a required flow testing facility to investigate it in that manner I am fully prepared to accept the validity of your conclusions.

At the same time, I am afraid I am back again with my concerns on the 1st Law issue. This time it relates directly to the issue addressed in this thread as an example of my concerns.

Using this as an example, using the 1st Law equation as presented in post#8, I to calculate the final Tank temperature, ignoring tank heat transfer, to be as follows:

P i =	4.85​	psia
T I =	70​	°F
T I =	530​	°R
P f =	14.7​	psia
k air =	1.4​
T f =	655​	°R
T f =	281​	°F

Which would indicate that even with an large amount of Tank heat loss during the 9 sec filling time, there would be an additional amount of filling time required as the Tank consumed the air required to maintain its target 14.7 psia pressure level; or, if the fill valve were to be closed, a substantial post fill pressure drop would be expected as the tank cools to ambient temperature.

If you are willing to continue consuming your time with my ongoing inquiries I would really appreciate your feedback on this issue; if not, I fully understand because it getting to one of those extended "OK, but what about" situations.

Jack

655 R = 195 F, not 281 F. This agrees roughly with the results of my calculations and those of the OP.

 

[JBA]

My error, checking my conversion program confirms that 195°F is indeed correct; but, that still does not address my concerns regarding the issue of a pressure drop associated with the return of the tank's temperature to ambient or does your calculation method account for this as well.
If so, this type of calculation with a single equation that crosses the Pcr point and accounts for the pressure vs temperature reduction is something I would very much like to learn and understand.

 

[Chestermiller]

My error, checking my conversion program confirms that 195°F is indeed correct; but, that still does not address my concerns regarding the issue of a pressure drop associated with the return of the tank's temperature to ambient or does your calculation method account for this as well.
If so, this type of calculation with a single equation that crosses the Pcr point and accounts for the pressure vs temperature reduction is something I would very much like to learn and understand.

The analysis in this thread (so far) assumes that the process takes place adiabatically, and does not include heat transfer from the gas to the tank walls and surroundings. This, of course, can be included, but, for a 9 second process, its inclusion does not seem worthwhile.

With regard to your question regarding the critical pressure, I don't quite follow. However, if changes are occurring at high pressures, we would need to include consideration of non-ideal gas effects. For the present problem, that wasn't necessary.

 

[JBA]

Adiabatic, I understand, thanks

With regard to my question regarding the critical pressure, it wasn't focused upon the critical pressure; but, on the fact that, if I understand it correctly, you appear to have a method to calculate the flow rates for the full range of pressure ratios including both the critical and sub critical pressure regions without having to calculate the two regions separately and sum the results; and, if so, I really want to understand that method.

 

[Chestermiller]

Adiabatic, I understand, thanks

With regard to my question regarding the critical pressure, it wasn't focused upon the critical pressure; but, on the fact that, if I understand it correctly, you appear to have a method to calculate the flow rates for the full range of pressure ratios including both the critical and sub critical pressure regions without having to calculate the two regions separately and sum the results; and, if so, I really want to understand that method.

OK. The calculations involve integrating an equation expressing the time derivative of pressure as a function of pressure itself. The key parameter in the calculation is the expansivity factor $\epsilon$, which is a function of the ratio of the pressure in the tank to the outside pressure. There are two regions of functionality, as you indicated, critical and sub critical. The expansivity factor is continuous at the transition between these regions.

The OP and I got our information on the expansivity factor from a Wiki link on Oriface Plates: https://en.wikipedia.org/wiki/Orifice_plate

We have experimented with different forms of the relationship, as discussed in post #39. Three of these forms give nearly identical results for the functionality: the theoretical form recommended on the link, a continuous approximation that I proposed, and a linear approximation, also continuous over the entire range. All three of these functionalities give nearly identical results for the tank pressure vs time, and match the OP's experimental data on pressure vs time astonishingly well.

 

[JBA]

Thanks for the reference, until this point I was surprised that I had not encountered any of the type of analysis that you were using but I now understand because in our pressure relief industry and products we are required by the customers to design our products with high efficiency nozzles, generally in the Cd = 97-98 range; and, in our flow testing and ASME certification facility we use ASME certified Cd sonic nozzles for flow measurement. As a result, all of my technical references and investigations have specifically focused on nozzle design where beta ratio focused theories are not an issue , as opposed to orifice plate flow measurement technology.