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Consider a gas turbine engine. The diffuser of a centrifugal-flow compressor stage creates a
  • A
    convergent area at the impeller inlet to increase both the air velocity and the air pressure.
  • B
    divergent area at the impeller exit to reduce the air velocity and increase the air pressure.
  • C
    convergent area at the impeller exit to reduce the air velocity and increase the air pressure.
  • D
    divergent area at the impeller exit to increase both the air velocity and the air pressure.
Refer to figure.
The compressor forces the airflow through the engine increasing its pressure. The mechanical energy the turbine provides to the compressor shaft is transmitted to the airflow with the compressor blades. In the stator, the airflow is compressed and has its temperature increased progressively. Before entering the combustion chamber, the last stator vanes must redirect the airflow and the diffuser, a divergent compartment at the impeller exit reduces the airflow’s velocity and increases air pressure for optimal combustion.

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