Question
1. A cheap radial-vaned centrifugal fan is required to provide a supply of pressurised air to a furnace. The specification requires that the fan produce
1. A cheap radial-vaned centrifugal fan is required to provide a supply of pressurised air to a furnace.
The specification requires that the fan produce a total pressure rise equivalent to 7.5 cm of water at a
volume flow rate of 0.2 m3
/s. The fan impeller is fabricated from 30 thin sheet metal vanes, the ratio
of the passage width to circumferential pitch at the impeller exit being specified as 0.5, and the ratio
of the radial velocity to blade tip speed as 0.1. Assuming that the overall isentropic efficiency of the
fan is 0.75 and that the slip can be estimated from Stanitz's expression, eqn. (7.34b), determine
(i) the vane tip speed;
(ii) the rotational speed and diameter of the impeller;
(iii) the power required to drive the fan if the mechanical efficiency is 0.95;
(iv) the specific speed.
For air assume the pressure is 105 Pa and the temperature is 20C.
2. The air entering the impeller of a centrifugal compressor has an absolute axial velocity of 100 m/s.
At rotor exit the relative air angle measured from the radial direction is 26360
, the radial component of velocity is 120 m/s, and the tip speed of the radial vanes is 500 m/s. Determine the power
required to drive the compressor when the air flow rate is 2.5 kg/s and the mechanical efficiency is
95%. If the radius ratio of the impeller eye is 0.3, calculate a suitable inlet diameter assuming the
inlet flow is incompressible. Determine the overall total pressure ratio of the compressor when the
total-to-total efficiency is 80%, assuming the velocity at exit from the diffuser is negligible.
3. A centrifugal compressor has an impeller tip speed of 366 m/s. Determine the absolute Mach number of the flow leaving the radial vanes of the impeller when the radial component of velocity at
impeller exit is 30.5 m/s and the slip factor is 0.90. Given that the flow area at impeller exit is 0.1 m2
and the total-to-total efficiency of the impeller is 90%, determine the mass flow rate.
Gas leaves an untwisted turbine nozzle at an angle ? to the axial direction and in radial equilibrium. Show that the variation in axial velocity from root to tip, assuming total pressure is constant, is given by
cxrsin2? constant.
Determine the axial velocity at a radius of 0.6 m when the axial velocity is 100 m/s at a radius of
0.3 m. The outlet angle ? is 45.
5. The flow at the entrance and exit of an axial-flow compressor rotor is in radial equilibrium. The
distributions of the tangential components of absolute velocity with radius are
c?1 ar b=r, before the rotor,
c?2 ar b=r, after the rotor,
where a and b are constants. What is the variation of work done with radius? Deduce expressions
for the axial velocity distributions before and after the rotor, assuming incompressible flow theory and that the radial gradient of stagnation pressure is zero. At the mean radius, r 0.3 m, the
stage loading coefficient, ? ?W/U2
t is 0.3, the reaction ratio is 0.5, and the mean axial velocity
is 150 m/s. The rotor speed is 7640 rev/min. Determine the rotor flow inlet and outlet angles at a
radius of 0.24 m given that the hub-tip ratio is 0.5. Assume that at the mean radius the axial
velocity remained unchanged (cx1 cx2 at r 0.3 m). (Note: ?W is the specific work and Ut
the blade tip speed.)
6. An axial-flow turbine stage is to be designed for free-vortex conditions at exit from the nozzle
row and for zero swirl at exit from the rotor. The gas entering the stage has a stagnation temperature of 1000 K, the mass flow rate is 32 kg/s, the root and tip diameters are 0.56 m and 0.76 m,
respectively, and the rotor speed is 8000 rev/min. At the rotor tip the stage reaction is 50% and
the axial velocity is constant at 183 m/s. The velocity of the gas entering the stage is equal to that
leaving. Determine
(i) the maximum velocity leaving the nozzles;
(ii) the maximum absolute Mach number in the stage;
(iii) the root section reaction;
(vi) the power output of the stage;
(v) the stagnation and static temperatures at stage exit.
Take R 0.287 kJ/(kg K) and Cp 1.147 kJ/(kg K).
7. The rotor blades of an axial-flow turbine stage are 100 mm long and are designed to receive gas
at an incidence of 3 deg from a nozzle row. A free-vortex whirl distribution is to be maintained
between nozzle exit and rotor entry. At rotor exit the absolute velocity is 150 m/s in the axial
direction at all radii. The deviation is 5 deg for the rotor blades and zero for the nozzle blades
at all radii. At the hub, radius 200 mm, the conditions are as follows:
Nozzle outlet angle 70
Rotor blade speed 180 m/s
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