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 m^3/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 11140 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 the power delivered to the propeller, in MW. the velocity at the nozzle exit, in m/s.
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Answer:
F=989.6 N
Explanation:
Given that
Diameter of shaft = 70 mm
Diameter of bearing sleeve =70.2 mm
So clearance h=0.1 mm
Speed V= 400 mm/s
Length of shaft = 250 mm
We know that
μ= 900 x 0.005 Pa-s
μ= 4.5 Pa-s
As we know that
From Newton's law of viscosity ,the shear stress given as follows
We also know that
Force = shear stress x area
Now by putting the values
So force
F= 18,000 x π x 0.07 x 0.25
F=988.6 N