Vortex Rocket Engine
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- Опубликовано: 4 окт 2024
- A small polymer 3D printed demonstrator rocket engine using a combination of vortex cooling and a regeneratively oxidiser cooled nozzle. The engine can be run continuously and runs at below ambient temperature.
A) This is awesome! B) I thought i was listening to Nexpo there at the end.
this guy literally stole nexpo's intro LMAO unless it's royalty free, they're STUPID similar
Beautiful but i wonder how much thrust it can make. I imagine there's alot of wasted energy from the change in velocity caused by the vortex and the exhaust cone being so wide. (The more parallel the cone the more powerful)
Une superbe autonomie , franchement cela me travaille depuis longtemps, un filtre athmosphérique , pareil à un simple entonoir pouvant capturer de l'argon , du xenon ou du krypton dans l'atmosphère...plus simplement de l'hydrogène...
It's fun playing with fire!
Philip Drew gonna be devo when he sees this
Are you able to release the CAD files for this? Seems like something I gotta try. Thanks!
yes, I would also like CAD files
I also!!
Ill try to disign a "Replica" of this engine and put it on Thingiverse
Integza made one and he normally puts his cad files online so
@@Volt64bolt yeah but Integza always ends up burning his stuff, better keep a fire extinguisher at hand.
SRB
that was wild 😜 // ... / I'm looking into it
Plz show us to make this vortex engine step by step as we can do this as our college project plz
Hi, I'll try to put together a more in-depth video soon. What's your project?
nice editing video looks phenomenal what camera?
I've never seen anything like this being used for engine cooling. Do you have any references I can go to to read more into this concept? Thanks.
Lewis Jones Research ‘vortex cooling’. It’s harder to find information on than standard regenerative cooling methods but the information is out there. What’s your project?
I'm a student at Caltech and we are in the process of starting a club and building our first engine. This concept of using vortex cooling is very cool! We might pursue a project in the future using this method.
Did you encounter issues with controlling the flow? I see you went through several iterations to get to the one highlighted in the video.
Lewis Jones Sounds good. I might be out in California later this year. Controlling the flow isn’t so much of an issue, it’s maintaining the optimum oxidiser/fuel mixture. A feed from a high pressure gas bottle for fuel and oxidiser should be fine for short burns. If you have low pressure injection of the propellant you get the chuffing/stalling issue. High pressure source > check valve > regulator > combustion chamber should suffice for a good demonstrator project. You could include variable regulators (rather than on/off) to experiment with different oxidiser/fuel ratios. Or use manual variable regulators in series with an on/off regulator and adjust the mixture between firing. Are you able to send me a direct message? Thanks.
First off, thats really neat, and interesting concept.
out of curiosity (and totally wanting to try this technique), how did you generate the vortex? Did you angle the oxy injector, make ridges on the chamber walls, and inject oxy on those? Or is it really simple and im just not thinking of it?
Edit: I think i see how you did it, with those 3 pipes near the end of nozzle
He has more videos explaining if you are still interested
@@ronwesilen4536 lol 2 years later
@@crocogile2352 i put still because of that, so i don't see the point of your comment
Dear Mr. Rogers.
I would please like to know what type of fuel you used.
Can you please tell me?
Thanks.
propane and oxigen , he showed it ina different video i think
@@thechargedone169 I think the propane was used to dial in the air fuel ratio.
Music?
Is that 3d printed ... How there is to much heat inside the nozzle
you may now get your answer in his newest video
song used?
Ross Bugden - Black Heat
Have you done the math to see if you're getting choked flow in the nozzle [ en.wikipedia.org/wiki/Choked_flow ]?
I've been looking at getting choked flow using self-pressurized Butane. The room-temperature vapor pressure of Butane is about 200 kPa; with a 20% pressure drop across injectors, that means a chamber pressure of about 160 kPa with a nozzle throat diameter of about 1.3 cm. To get choked flow in the nozzle at that pressure means that you'll need a total mass flow of about 0.013 kg/s. With an OF ratio of 15, that means that you need about 0.0052 kg/s of Air and 0.0008 kg/s of butane.
@@elebouthillier he'll ya man I hope ur doing something cool and helpfull with ur brain ya seem very intelligent
Could you also build a turbine?
where can we download the build file for this so we can print ourselves, you havent been active in a year
I noticed you used CampingGaz for the propellant (Isobutane). It's a great propellant but I would think that the pressure is a bit low (7 bar). Generally you want 20% drop across the injector to isolate feed pressure from chamber pressure (so chamber pressure should be about 5.5 bar). This will eliminate a lot of the chuffing. Are you just using a PLA nozzle? That's a neat idea. How long does a nozzle last? Minutes?
Ed LeBouthillier Exactly right the fuel inlet pressure is too low to sustain itself once chamber pressure builds sufficiently. All PLA, nozzle can be continuously fired, no time limit, as long as oxidiser vortex cooling is sustained.
Neat. Pretty impressive. I'm going to try it...it looks like fun.
There are off-the-shelf orifices/flow restrictors at McMaster-Carr. Search "flow control" or "flow control orifice." They're just like threaded plugs. This could give you pressure isolation.
What was the designed chamber pressure?
What was the designed thrust?
I played around with RPA (rocket propulsion analysis) and it says that the proper mixture ratio for air-butane is about 15:1 by mass.
I put up a similar design on thingiverse: thing 2941197
Ed LeBouthillier sure that number is correct?
Yeah, sorry. Thingiverse said it will take 24 hours before it becomes available. If you want, I can send you my STL file. Send me an email codemonky AT earthlink.net
Appliquer cela aux réacteurs électriques ?...serait-ce possible ?.
This is cooll.
What materials did you use for the printing ?
le raisonnement par l'absurde , une simple dynamo appliquée a une roue de bicyclette et des accumulateurs obtiennent des stockages électriques.le système grande autonomie. velo -électrique.
Is there any chance at all you can release the files for this? Regardless of how bad you may think it is, id love to try this out myself!
I believe under ITAR he cant't
@@zacharyj6465 i dont think this is a weapon
@@rawhidelamp Rockets and their engines are considered advanced weapons technology due to the fact that they can be used as ICBM's. Im not sure if this would be kept under ITAR but if I had to assume, I'd say yes
Hey dude I made one too
What do you use for your fuel mixture?
are you using a high-velocity stream of rotating oxidizer inside the combustion chamber and nozzle to prevent heat from causing damage while eliminating the need for chamber plumbing and removing the risk of laminar flow combustion of fuel against the structure because of the high ratio of oxidizer to fuel the closer to the walls the combustion gets?
Yes
@@SamRogers what oxidizer was used?
Would this work with a solid fuel?
Matthew Ferrie i don’t think so
You can’t use solid fuel in regen cooling as it is not a liquid or gas
what is fuel and oxider?
성민준 Gaseous butane and oxygen. Planning on building one?
Sam Rogers butane is kinda succ for rockets. It will freeze and stop pressuring the gas when large volumes of gas are being used at once. I prefer methane or propane
Des accumulateurs d'énergie pour avions...le cas du thorium...
Could we see more of these? Don’t worry about being too technical, I’m told I have an above average IQ and take to science very naturally.