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Old November 16th, 2007, 11:50 AM
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Re: In search of water ... Moon and the Mars

Quote:
Originally Posted by rahulpsharma
Just happen to recollect a bit of technical info about this, if anyone cares to read....

The combustion instability arose due to the desire of the Russians to use the exhaust flue gases from the Gas Turbine to be used again in the main combustion chamber of the exhuast nozzle.... This would have raised the combustion pressures and hence higher exit velocity and improved thrust.... It was a technology that was never tried before.... In doing so, the temperatures and pressures would reach levels never achieved before....

Conventional Rocket designs allowed the Flue Gases from the Gas Turbine to Exhaust into the atmosphere at a very high temp.... (A simple but wasteful design : an open cycle design)... Russians wanted to use this exahust from Gas Turbine to be fed back to the main combustion chamber instead of venting to the atmosphere..... This was needed because they were incapable of making a Rocket design as powerful as the Saturn V design that used only 5 boosters.... The Russian equivalent, N1, was to use 30 boosters...!!! By using a closed cycle design they could have attained 25% higher efficiency for each of those 30 engines....!!!

However, as is known, N1 programme was scrapped because US had already reached the moon..... But the closed cycle design was perfected in NK-33, successor of N1, and RD180 Rocket designs that recently powered the Atlas Rockets during it's initial 180 seconds in the flight....

I am afraid I have no idea what you are talking about. How does gas turbine come into picture? Are you talking of the turbine driving the cryogenic pump?
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