Which outcome occurs when adiabatic expansion rapidly decreases temperature in a jet engine's turbine stage?

💡 Explanation

When adiabatic expansion causes a sudden temperature drop, the boundary layer thickens due to the increased viscosity of the colder, slower-moving air near the turbine blades, increasing the risk of boundary layer separation which can cause compressor stall. Therefore compressor stall happens, rather than detonation, creep, or enhanced catalysis, which depend on pressure or temperature increase instead.

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