Boost

           B o o s t           
                  2 June 2018
 
   Introducing a theoretical configuration for thrust engines
 

The following images are free to view on the internet and are being used here to illustrate the talking point in this presentation. These are images from SpaceX and Blue Origin specifically because they represent the pinnacle of courageous private enterprise.

 

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 Tremendous energy expelled to create the reaction forces for lift off
      teq flame 1       teq flame 2
Booster engines are of the most powerful and at the most critical edge of material application and engineering

 

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The reaction engine expels all the combustion energy in a very short time span. A vast amount of potential chemical and kinetic energy is discarded in the process of accelerating the combustion components away from the vehicle.

   

TeqniCraft is proposing a “pressure” engine instead of a “reaction” device. Kinetic energy from the combustion is recirculated to form a positive pressure pocket.  

The ideal is to expend all kinetic energy inside the engine aligned towards the desired vector and then allow the combustion components to float out the exhaust.    

 

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The TeqniCraft thruster does not rely (so much) on the separation velocity of combustion components from the vehicle but rather, the kinetic energy from combustion is forced into a pressure pocket where the energy is depleted (or drastically reduced) before it is expelled from the device

Theoretically our configuration promises to approach the ideal pressure engine to a considerable degree.

The configuration is also scalable to many thousands of tons of thrust. 

 
 The thrust capability of the TeqniCraft pressure engine can be symbolically compared to existing engines.
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The simplicity of the configuration will allow thrust engines into many thousands of tons of thrust per engine. 

 

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Idealised artistic impression of pressure engine at lift off showing the reduced blast effect around the launch facility

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  Of course the engine can be throttled to a reasonable degree but this engine is specifically configured for lifting to orbit or other locomotive type applications.

 

   

Here is another beautiful example of the energy expulsion of the rocket principle from Blue Origin test facility. See Blue Origin website.

      energy loss 1

This is not to disparage the excellence and quality of any of the designers and engineers working on rocket engines at Blue Origin, SpaceX or anywhere else.

 

The process of theoretically reconfiguring the thrust engine to optimise the chemical and kinetic energy went on for many decades but in the end the eventual configuration turned out to be very simple in principle.   

         energy loss 3 

 
   Fabrication of a functioning demonstration model is now the priority.
 

The pressure pocket principle is also directly compatible to turbine thrust engines

 

 

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During the periods of contemplating the pressure engine we have also explored various other theoretical possibilities to increase the thrust capacity of kinetic energy from the combustion chamber.

Here is an example that we include for the sake of interest. Because we are not really combustion specialists this may turn out to be totally impractical. However it will take a very good debunking process to convince us that this concept is not viable.

 

The stepped expansion chamber

 

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The idea is to apply vortex energy in the expansion flow. The vortex is induced to form a ring at the step and would then have two functions.

One is to draw the flow onto the wider expansion surface and another is to add pressure onto the surface of the step as the vortex rotates.

 

                       teq booster 14 1

 

 The steps could be quite a bit wider than shown in these representations thereby creating very powerful vortex rings but optimum ratios would be studied by flow specialists.
 Reliable induction of the vortex rings will obviously be imperative. A method must be incorporated to force vortex continuance throughout every burn period. In the case of loss of vortex one can expect total loss of all thrust of the engine.
 
  Forced vortex induction could possibly be as simple as scrambling the laminar flow at the edge of the step and then reinstating it after the step. There are more direct intervention methods that could be explored and in our opinion the effort would be very valuable if the thrust yield is significantly increased.
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Question is: Could a vortex be sustained in the hypersonic flow?

 

 

    step expan 1    step expan 2

An option for reliable vortex induction. Injection of counter flow into the step.

                 step expan 3

      Here is a crude projection of vortex function

The counter flow (blue) could be exhaust from turbopumps. With this system there will be powerful vacuum on the turbine exhaust increasing turbine efficiency.

Will this stepped expander increase specific impulse to a degree which makes it worthwhile to pursue? 

 

 

  For discussion of these concepts please use comment section below

or directly to Doug at This email address is being protected from spambots. You need JavaScript enabled to view it.  or   This email address is being protected from spambots. You need JavaScript enabled to view it.