Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay 21
Lect-36
Exercise problem # 1
A small inward radial flow gas turbine,
comprising a ring of nozzle blades, a radial-
vaned rotor and an axial diffuser, operates at the
nominal design point with a total-to-total
efficiency of 0.90. At turbine entry the
stagnation pressure and temperature of the gas
is 400 kPa and 1140 K. The flow leaving the
turbine is diffused to a pressure of 100 kPa and
has negligible final velocity. Given that the flow
is just choked at nozzle exit, determine the
impeller peripheral speed and the flow outlet
angle from the nozzles.
Ans: 586 m/s, 73.75o
