In n1 and n2 are the indices of compression for the first and second stage of compression, then the ratio of work-done on the first and second stages $$\left( {\frac{{{{\text{W}}_1}}}{{{{\text{W}}_2}}}} \right)$$ with perfect intercooling is given by
A. $$\frac{{{{\text{W}}_1}}}{{{{\text{W}}_2}}} = \frac{{{{\text{n}}_2}\left( {{{\text{n}}_1} - 1} \right)}}{{{{\text{n}}_1}\left( {{{\text{n}}_2} - 1} \right)}}$$
B. $$\frac{{{{\text{W}}_1}}}{{{{\text{W}}_2}}} = \frac{{{{\text{n}}_1}\left( {{{\text{n}}_2} - 1} \right)}}{{{{\text{n}}_2}\left( {{{\text{n}}_1} - 1} \right)}}$$
C. $$\frac{{{{\text{W}}_1}}}{{{{\text{W}}_2}}} = \frac{{{{\text{n}}_1}}}{{{{\text{n}}_2}}}$$
D. $$\frac{{{{\text{W}}_1}}}{{{{\text{W}}_2}}} = \frac{{{{\text{n}}_2}}}{{{{\text{n}}_1}}}$$
Answer: Option B
Solution(By Examveda Team)
In n1 and n2 are the indices of compression for the first and second stage of compression, then the ratio of work-done on the first and second stages $$\left( {\frac{{{{\text{W}}_1}}}{{{{\text{W}}_2}}}} \right)$$ with perfect intercooling is given by $$\frac{{{{\text{W}}_1}}}{{{{\text{W}}_2}}} = \frac{{{{\text{n}}_1}\left( {{{\text{n}}_2} - 1} \right)}}{{{{\text{n}}_2}\left( {{{\text{n}}_1} - 1} \right)}}$$This Question Belongs to Mechanical Engineering >> Compressors, Gas Turbines And Jet Engines
The compression ratio for the compressor is always _________ unity.
A. Equal to
B. Less than
C. More than
D. None of these
The hottest point in a gas turbine is
A. At the base
B. At the tip
C. In the center
D. Between ~ to i of the blade height
Temperature of gases at end of compression as compared to exhaust gases in a gas turbine is
A. Higher
B. Lower
C. Equal
D. Can't be compared
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