Pressure Gradient for Nitrous Flow

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SUMMARY

The discussion focuses on calculating the necessary tank pressure for a vessel supplying Nitrous Oxide to a combustion chamber, targeting a mass flow rate of 2 lbs/sec and a downstream pressure of 800 psi. The user seeks guidance on fluid dynamics principles, specifically referencing the Darcy friction equation to determine pressure loss due to friction in the tubing. Key parameters include a temperature of 308.15 K, a tubing length of 1.3 meters, and a Steel Woven PTFE tubing type with a diameter of 3/8". The conversation emphasizes the importance of understanding fluid flow and pressure dynamics in rocket engineering applications.

PREREQUISITES
  • Understanding of fluid dynamics principles, particularly Navier-Stokes equations.
  • Familiarity with the Darcy friction equation for calculating pressure loss.
  • Knowledge of thermodynamics, specifically gas behavior under varying pressures and temperatures.
  • Basic understanding of rocket propulsion systems and mass flow rates.
NEXT STEPS
  • Research the application of the Darcy friction equation in fluid flow calculations.
  • Study the Navier-Stokes equations and their relevance to incompressible flow.
  • Explore the properties of Nitrous Oxide under different temperature and pressure conditions.
  • Investigate safety protocols and mentorship roles in rocket engineering projects.
USEFUL FOR

This discussion is beneficial for undergraduate engineering students, particularly those involved in rocket design and propulsion systems, as well as mentors and safety officers overseeing such projects.

Kevin
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Hello everyone,

I am currently working on an undergraduate club team for the Intercollegiate Rocket Engineering Competition. I am attempting to do a calculation to determine the pressure needed in a vessel leading to another pressurized combustion chamber to achieve a desired mass flow rate.

These are my requirements:

Mass flow rate of Nitrous Oxide: 2 [lbs/sec]
Down stream pressure: 800 [psi]
Tank pressure: ?
Temperature: 308.15 [K]
Tubing Length: 1.3 meters
Tubing Type: Steel Woven PTFE, 3/8" Diameter (but this can change)

Unfortunately my courses have not given my adequate knowledge of fluid flow from one pressurized vessel to another to determine the pressure required. Also if there are any other changes that may thought to be helpful I am very open to suggestions

Thanks for you help!
 
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Have you already learned Navier stokes? It’s the key to equation this problem if you know how the friction is. Besides, if you consider the friction to be fully developed, steady and incompressible, the pressure loss can be obtained from de Darcy friction equation:
Pressure loss = ##\lambda (l/d_h) \rho v^2/2 ##
 
Kevin said:
Hello everyone,

I am currently working on an undergraduate club team for the Intercollegiate Rocket Engineering Competition. I am attempting to do a calculation to determine the pressure needed in a vessel leading to another pressurized combustion chamber to achieve a desired mass flow rate.

These are my requirements:

Mass flow rate of Nitrous Oxide: 2 [lbs/sec]
Down stream pressure: 800 [psi]
Tank pressure: ?
Temperature: 308.15 [K]
Tubing Length: 1.3 meters
Tubing Type: Steel Woven PTFE, 3/8" Diameter (but this can change)

Unfortunately my courses have not given my adequate knowledge of fluid flow from one pressurized vessel to another to determine the pressure required. Also if there are any other changes that may thought to be helpful I am very open to suggestions

Thanks for you help!
Sounds like a fun project.

Do you have a Mentor and Safety Officer for this rocket project? Will they be checking your calculations and the responses from the PF? :smile:
 
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