Skip to main content

ROCKET PROPULSION RESEARCH

Search This Blog

Social media

Get link
Facebook
X
Pinterest
Email
Other Apps

INSTAGRAM

https://www.instagram.com/rocketpropulsionr/

YOUTUBE

https://www.youtube.com/channel/UCl8PrczGgg0LmSMnYFxLGtQ

PATREON

https://www.patreon.com/rocketpropulsionresearch?fan_landing=true

EMAIL

lpreresearch@gmail.com

Get link
Facebook
X
Pinterest
Email
Other Apps

Comments

Post a Comment

Popular Posts

USING CFTURBO PART 2

Last week we edited the meridonal contour and today we're going to continue designing our pump by editing the blades. We click blade properties button and in this window we can set the number of blades and spans. Spans will be used to curve the inlet and outlet of the blade at different heights. Then we can edit the blade lines and its angles. We could even design a Barske type impeller combining some parameters. Click OK and we can go on editing the blade profiles. To add rounded edges go to Freeform and select LE rounded to round the leading edge and TE rounded to round the trailing edge. With the following window you can set the edge position but just click OK and go to the next step. In this window we are not going to make any changes, so just click OK. Now we are going to create a volute. Click the sum sign on the outlet, then click New volute. A window will appear. There you can choose wether you want a single or

Pump CFD Analysis

Once a design is finished it is exported to Simerics. The process is very simple just click export , select all the components required and click open exported files . The model will load into Simerics, just select the nomber of iterations and start the simulation. In order to see the results, make sure that volumes are selected on the top right corner, then click view and display the desired variables. Below you can see the pressure along the pump. This is the model to be used in our engine and it will produce around 1000 psi. Simerics can also predict if there's cavitation at any point.

Cooling channels

In order to keep the wall temperature below the material melting point it is required to use some sort of cooling, for this reason various methods for cooling thrust chambers have been used in the past decades. Surely, regenerative cooling is the most extended method. Regenerative cooling uses a stream of propellant flowing through small channels or tubes around the combustion chamber to cool it down, then the heated propellant is fed into the combustion chamber to be burned. The diagram below shows how the temperature is reduced at different points. The notation used for the temperatures at those points is the following: Tc = Combustion temperature Taw = Adiabatic wall temperature Twg = Wall temperature at the gas side Twc = Wall temperature at the coolant side Tbc = Coolant bulk temperature Simulation results More than 15 designs with their respective simulations have been made in order to provide the engine with an efficient cooling system. The first image shows the temperature alo

Powered by Blogger