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Steam Jet vaccum ejector


Posted by: seminar class
Created at: Saturday 12th of March 2011 05:23:25 AM
Last Edited Or Replied at :Tuesday 05th of April 2011 06:35:58 AM
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d. Multi-stage with both condensing and non-condensing stages.
3. EQUIPMENT ARRANGEMENT
Ejectors:

An ejector is a type of vacuum pump or compressor. Since an ejector has no valves, rotors, pistons or other moving parts, it is a relatively low-cost component is easy to operate and requires relatively little maintenance.
In a steam-jet ejector, the suction chamber is connected to the vessel or pipeline that is to be evacuated under vacuum. The gas that is to be induced into the suction chamber can be any fluid that is compatible with the steam and the components materials of const..................[:=> Show Contents <=:]



Vortex refrigeration


Posted by: summer project pal
Created at: Sunday 09th of January 2011 07:07:54 PM
Last Edited Or Replied at :Sunday 09th of January 2011 07:07:54 PM
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Way is of this type
Some other examples .
• Rankine vortex
• Cyclonic separation
• Eddy
• Helmholtz's theorems
• Horseshoe vortex
• Viktor Schauberger
• Shower-curtain effect
• Strouhal number
• Vile Vortices
• Von Kármán vortex street
• Vortex engine
• Vortex ring
• Vortex tube
• Vortex cooler
• Vortex shedding
• Vortex Induced Vibration
• Vorticity
• Wingtip vortices
• Quantum vortex
• Wormhole

CHAPTER-VI
• REFERWeather Glossary' The Weather Channel Interactive, Inc.. 2004.
• Glossary and..................[:=> Show Contents <=:]



TURBOFAN ENGINES


Posted by: summer project pal
Created at: Saturday 08th of January 2011 12:40:23 PM
Last Edited Or Replied at :Tuesday 26th of April 2011 05:58:55 AM
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change of momentum),

f = d (MV) / dt.
The nozzle of the turbojet is usually designed to take the exhaust pressure back to free stream pressure. The thrust equation for a turbojet is then given by the general thrust equation with the pressure-area term set to zero. If the free stream conditions are denoted by a 0 subscript and the exit conditions by an e subscript, the thrust F is equal to the mass flow rate m times the velocity V at the exit minus the free stream mass flow rate times the velocity.
F = e - 0
This equation contains two terms. Aerodynamicists ..................[:=> Show Contents <=:]



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