Axial and Radial Flow Turbines Solved Problems Ragaza
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Transcript of Axial and Radial Flow Turbines Solved Problems Ragaza
8/19/2019 Axial and Radial Flow Turbines Solved Problems Ragaza
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Margarito Ragaza II
Axial Flow Turbines
1. Consider an impulse gas turbine in which gas enters at pressure = .! bar and lea"es at
1.#$ bar. The turbine inlet temperature is 1###% and isentropic e&&icienc' o& the turbine is#.((. I& mass &low rate o& air is !( )g*s+ nozzle angle at outlet is , o+ and absolute "elocit'
o& gas at inlet is 1-# m*s+ determine the gas "elocit' at nozzle outlet+ whirl component at
rotor inlet and turbine wor) output. Ta)e+ γ =1.$$+ and Cpg =1.1-, )*)g%
T ' 02
T 01
=( p 02
p01
)( y−1)
y
T ' 02=T
01( p02
p01
)( y−1 ) y =1000(
1.03
5.2)0.248
=669 K
T 02=T 01−ŋt (T 01−T ' 02)=1000−0.88 (100−669 )=708.72 K
1
2 (C 2
2−C 1
2 )=C p(T 01−T 02)
C 2=√ [(2 ) (1147 ) (1000−708.72 )+19600 ] = (!/.$$ m*s
C w2=829.33sin57 °
=0/. m*s
W t =mC pg (T 01−T 02)=(28 ) (1.147 ) (1000−708.72 )=9354.8 KW
!. In a singlestage gas turbine+ gas enters and lea"es in axial direction. The nozzle e&&lux
angle is 0(2+ the stagnation temperature and stagnation pressure at stage inlet are (##2C
and - bar+ respecti"el'. The exhaust static pressure is 1 bar+ totaltostatic e&&icienc' is
#.(+ and mean blade speed is -(# m*s+ determine the wor) done and the axial "elocit'
which is constant through the stage Assume γ =1.$$+ and Cpg = 1.1-, )*)g%.
8/19/2019 Axial and Radial Flow Turbines Solved Problems Ragaza
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$. In a singlestage gas turbine+ gas enters and lea"es in axial direction. The nozzle e&&lux
angle is 0(2+ the stagnation temperature and stagnation pressure at stage inlet are (##2C
and - bar+ respecti"el'. The exhaust static pressure is 1 bar+ totaltostatic e&&icienc' is
#.(+ and mean blade speed is -(# m*s+ determine the total to total e&&icienc' and the
degree o& reaction.
-. A singlestage axial &low gas turbine with e3ual stage inlet and outlet "elocities has the
&ollowing design data based on the mean diameter4
8/19/2019 Axial and Radial Flow Turbines Solved Problems Ragaza
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Calculate the rotorblade gas angles+ the degree o& reaction+ blade loading coe&&icient+ and
power output.
. From the pre"ious problem+ determine the total nozzle throat area i& the throat is situated
at the nozzle outlet and the nozzle loss coe&&icient is #.#.
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