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Scilla [17]
3 years ago
12

A turboprop engine consists of a diffuser, compressor, combustor, turbine, and nozzle. The turbine drives a propeller as well as

the compressor. Air enters the diffuser with a volumetric flow rate of 83.7 m^3/s at 40 kPa, 240 K, and a velocity of 180 m/s, and decelerates essentially to zero velocity. The compressor pressure ratio is 10 and the compressor has an isentropic efficiency of 85%. The turbine inlet temperature is 11140 K, and its isentropic efficiency is 85%. The turbine exit pressure is 50 kPa. Flow through the diffuser and nozzle is isentropic. Using an air-standard analysis, determine the power delivered to the propeller, in MW. the velocity at the nozzle exit, in m/s.

Engineering
1 answer:
Yuri [45]3 years ago
7 0

Answer:

Power =10004.57kw

Velocity = 296.4m/s

Explanation:

Please see attachment

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Answer:

\eta =\dfrac{(h_3-h_4)-(h_2-h_1)}{(h_3-h_5)}

Explanation:

generally regeneration of cycle is used in the case of gas turbine. due to regeneration efficiency of turbine is increased but there is no effect on the on the net work out put of turbine.Actually in regeneration net heta input is decreases that is why total efficiency  increase.

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    W_{net}=W_{out}-W_{in}

   W_{net}=(h_3-h_4)-(h_2-h_1)

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So efficiency of cycle \eta =\frac{W_{net}}{Q_{in}}

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Effectiveness of re-generator

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2 years ago
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