· The BR710 engine is designed
to have a thrust range between 62 kN and 76 kN. It is a suitable power plant
for a Gulfstream 5 twin jet.
·
The
Fan is a 48-inch wide-chord fan of Titanium.
· The Compressor is a 10 stage axial flow unit with
the first 4 stages being variable.
·
The
Combustion Chambers are full annular axial flow with 20 fuel injectors.
· The high-pressure Turbine
has two stages followed by a two-stage low pressure turbine.
· Thrust reversal is provided by a two-door
unit integrated into the nacelle.
What
materials issues need to be addressed in designing such an engine?
|
