1
answer
1
watching
604
views

A turboprop engine consists of a diffuser,
compressor, combustor, turbine, and nozzle. The
turbine drives a propeller as well as the
compressor. Air enters the diffuser with a
volumetric flow rate of 83.7 m3
/s at 40 kPa, 240 K,
and a velocity of 180 m/s, and decelerates
essentially to zero velocity. The compressor
pressure ratio is 10 and the compressor has an
isentropic efficiency of 85%. The turbine inlet
temperature is 1140 K, and its isentropic efficiency
is 85%. The turbine exit pressure is 50 kPa. Flow
through the diffuser and nozzle is isentropic. Using
an air-standard analysis, determine: (a) the power
delivered to the propeller, in MW. (b) the velocity at
the nozzle exit, in m/s. Neglect kinetic energy
except at the diffuser inlet and the nozzle exit

For unlimited access to Homework Help, a Homework+ subscription is required.

Unlock all answers

Get 1 free homework help answer.
Already have an account? Log in

Weekly leaderboard

Start filling in the gaps now
Log in