These engines are equipped with a dynamic counter weight system
and are operated accordingly. These are 6 cylinder, direct drive,
horizontally opposed and air cooled engines.
2'nd Stage Turbine Rotor of fighter aircraft engine, WP-13.
The 2nd stage turbine rotor consists of an inner shaft, a disk
and seventy five rotor blades. The rotor includes two supports:
the front support is a radial thrust ball bearing installed
in the compressor; the rear support is a roller bearing.
The function of the plunger-type fuel pump is to supply fuel
with a certain pressure to the main combustion chamber of the
engine. It consists of housing.
This system has been incorporated to control the aircraft in
rolling movement and to enhance lateral controllability of the
aircraft. It uses the physical movement from the control stick
and converts it into hydraulic force for movement of the ailerons.
The accessory driving device is located at the bottom of the
engine. It ensures the working of various accessories within
their operational limits by providing different gear driving
ratio to individual accessories.
The accessory driving device is located at the bottom of the
engine. It ensures the working of various accessories within
their operational limits by providing different gear driving
ratio to individual accessories.
