Question

A gas turbine power plant working on brayton cycle operates between the temperature limits of 300k and 1200k and pressure limits of 101 kpa and 505 kpa

Answer 1

Answer:

In aeronautical engineering, overall pressure ratio, or overall compression ratio, is the ratio of the stagnation pressure as measured at the front and rear of the compressor of a gas turbine engine.

Answer 2

Answer:

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Explanation:

In aeronautical engineering, overall pressure ratio, or overall compression ratio, is the ratio of the stagnation pressure as measured at the front and rear of the compressor of a gas turbine engine.

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