reverse flow turboprop engines

difficulty in designing

Simple ,Low weight & cost and High pressure rise per stage

Large frontal area and limited number of stages

is a raw of rotor and a raw of stator

increase pressure and control the direction of airflow.

increase air velocity

axial velocity through the compressor

is the ratio between compressor outlet pressure to compressor inlet pressure.

is number of stages in the compressor.

compressor outlet

is lowest stagger angle at the root.

blade tip speed.

multiply inlet pressure with compression ratio

small gas turbine engines with reverse flow combustion.

it is based on cruise speed and altitude (air density).

flexibility of operation and greater resistance to surge

lower RPM than high pressure compressor

less efficient

avoid surge

keeping clearance between the impeller and casing As small as possible to preventing excessive air leakage