Compressors, Gas Turbines and Jet Engines
In the axial flow gas turbine, the work ratio is the ratio of

Compressor work and turbine work
Actual total head temperature drop to the isentropic total head drop from total head inlet to static head outlet
Output and input
Actual compressor work and theoretical compressor work

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Compressors, Gas Turbines and Jet Engines
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 (W₁/W₂) with perfect intercooling is given by

W₁/W₂ = n₁(n₂ - 1)/n₂(n₁ - 1)
W₁/W₂ = n₁/n₂
W₁/W₂ = n₂(n₁ - 1)/n₁(n₂ - 1)
W₁/W₂ = n₂/n₁

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Compressors, Gas Turbines and Jet Engines
Intercooling in gas turbines

Increases net output but decreases thermal efficiency
Decreases net output and thermal efficiency both
Increases net output and thermal efficiency both
Decreases net output but increases thermal efficiency

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