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Re: The Jet propulsion with closed combustion type
Calculate the temperature before the turbine:
Pls see below figure 4:
The method also is used to calculate the temperature of each course. Under some condition, when the pressure after compression is pretty high, reducing the pressure by combustion in some extent, the efficiency reduce a little, meanwhile the temperature before turbine reduce much, I state a example:
Set the temperature of outside air: 300K, k=1.4, set the pressure after compression/before compression α=7, the pressure after combustion/before combustion β=7.5, thus the temperature turbine 2206K; theory efficiency: η=60.2%; k=1.4, α=7, β=7, the temperature turbine 2100K, η=59.6%; k=1.4, α=7, β=6.5, the temperature turbine 1992K, η=58.9%; k=1.4, α=7, β=6, the temperature turbine1881K, η=58.2%; I change β by change in the volume proportion of fresh gas in each time or change of the concentration of fuel a little. In this example, η is reduced by 3%, the temperature before turbine decrease 400K.
This example just reminds a phenomenon. The data to some parameters may not precise; actually they change in normal and very high temperature. Here I assume them unvaried. After all it is a good reference for you.
Last edited by qumf; 03-13-2009 at 07:18 AM..
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