You have already done problem 5.5 – not too complicated – No power turbine, only four states. #1 – Assume the compressor

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You have already done problem 5.5 – not too complicated – No
power turbine, only four states.
#1 – Assume the compressor inlet mass flow rate is 100 lbm/sec.
Since this incoming air is an ideal gas, calculate the incoming
specific volume (v1) and then the involving volumetric flow rate
(V’1 ft3/sec) since V’1 = m’1 *v1. Also, using the Lower Heating
Value method, calculate the required fuel flow.
Now calculate the compressor power, the turbine power, and the
Q’a in the combustion chamber (all Btu/sec). Find W’net and the
system efficiency.
#2 – Assume that the compressor in #1 is already running at its
maximum speed (rpm or rps) – it cannot run any faster.
The compressor is basically an air pump – its output (V’1)
varies with the operating speed and the density (and specific
volume) of the incoming air. Since the compressor is already
turning at maximum speed, it cannot run any faster. And since you
want the maximum power (W’net) possible from the gas turbine, you
do not want it running any slower.
If the inlet air temperature changes, v1 changes. The compressor
volumetric flow rate remains constant, but the mass flow rate (m’1)
changes. This changes the amount of fuel (m’f) which you can
burn.
Repeat part #1 with inlet air temperatures of 540 R and also 570
R.
Tabulate your results to show the effect of T1 on m’1, mf’,
W’net, and cycle efficiency.
(Problem 5.5 - Bathie)