{
"metadata": {
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"worksheets": [
{
"cells": [
{
"cell_type": "heading",
"level": 1,
"metadata": {},
"source": [
"Chapter1 - Basic Concepts of Turbo Machines"
]
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex-1.1 Page 18"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"from __future__ import division\n",
"#input data\n",
"P01=1#initial pressure of a fluid in bar\n",
"P02=10#final pressure of a fliud in bar\n",
"T01=283#initial total temperature in K\n",
"ntt=0.75#total-to-total efficiency\n",
"d=1000#density of water in kg/m**3\n",
"r=1.4#ratio of specific heats for air\n",
"Cp=1.005#specific at heat at constant pressure in kJ/kg.K\n",
"\n",
"#calculations\n",
"h0s1=(1/d)*(P02-P01)*10**2#enthalpy in kJ/kg\n",
"h01=(h0s1/ntt)#enthalpy in kJ/kg\n",
"T02s=T01*(P02/P01)**((r-1)/r)#temperature in K\n",
"h0s2=(Cp*(T02s-T01))#enthalpy in kJ/kg\n",
"h02=(h0s2/ntt)#enthalpy in kJ/kg\n",
"\n",
"#output\n",
"print '''The work of compression for adiabatic steady flow per kg of fliud if - \n",
"(a)The fliud is liquid water is %3.1f kJ/kg\n",
"(b)The fliud is air as a perfect gas is %3.2f kJ/kg'''%(h01,h02)"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"The work of compression for adiabatic steady flow per kg of fliud if - \n",
"(a)The fliud is liquid water is 1.2 kJ/kg\n",
"(b)The fliud is air as a perfect gas is 352.94 kJ/kg\n"
]
}
],
"prompt_number": 1
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex 1.2 Page 19"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"\n",
"#input data\n",
"P01=7#Total initial pressure of gases at entry in bar\n",
"T01=1100#Total initial temperature in K\n",
"P02=1.5#Total final pressure of gases at exit in bar\n",
"T02=830#Total final temperature in K\n",
"C2=250#Exit velocity in m/s\n",
"r=1.3#Ratio of specific heats of gases\n",
"M=28.7#Molecular weight of gases\n",
"R1=8.314#Gas constant of air in kJ/kg.K\n",
"\n",
"#calculations\n",
"T02s=T01*(P02/P01)**((r-1)/r)#Final temperature in K\n",
"ntt=((T01-T02)/(T01-T02s))#Total-to-total efficiency\n",
"R=(R1/M)#Gas constant of given gas in kJ/kg.K\n",
"Cp=((r*R)/(r-1))#Specific heat of given gas at constant pressure in kJ/kg.K\n",
"T2s=(T02s-((C2**2)/(2*Cp*1000)))#Temperature in isentropic process at exit in K\n",
"nts=((T01-T02)/(T01-T2s))#Total-to-static efficiency\n",
"\n",
"#output\n",
"print '''The total-to-total efficiency of gases is %0.2f %%\n",
"The total-to-static efficiency of gases is %0.1f %%'''%(ntt*100,nts*100)"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"The total-to-total efficiency of gases is 82.05 %\n",
"The total-to-static efficiency of gases is 76.3 %\n"
]
}
],
"prompt_number": 2
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex 1.3 Page 20"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"#input data\n",
"h0=6#Change in total enthalpy in kJ/kg\n",
"T01=303#Total inlet temperature of fluid in K\n",
"P01=1#Total inlet pressure of fliud in bar\n",
"Cp=1.005#specific at heat at constant pressure in kJ/kg.K\n",
"ntt=0.75#Adiabatic total-to-total efficiency\n",
"r=1.4#ratio of specific heats for air\n",
"\n",
"#calculations\n",
"T02=T01+(h0/Cp)#Exit total termperature of fliud in K\n",
"P1=(1+((ntt*h0)/(Cp*T01)))**(r/(r-1))#Total pressure ratio of fluid \n",
"h0s=ntt*h0#Change in enthalpy of process in kJ/kg\n",
"P0=((h0s*1000)/100)#Change in pressure in bar\n",
"P02=P0+P01#Total outlet pressure of fliud in bar\n",
"P2=(P02/P01)#Total pressure ratio of fliud\n",
"\n",
"#output\n",
"print '''(a)The exit total temperature of fliud is %3.2f K\n",
"(b)The total pressure ratio if:\n",
"(1)The fliud is air is %3.3f\n",
"(2)The fliud is liquid water is %3.0i'''%(T02,P1,P2)"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"(a)The exit total temperature of fliud is 308.97 K\n",
"(b)The total pressure ratio if:\n",
"(1)The fliud is air is 1.053\n",
"(2)The fliud is liquid water is 46\n"
]
}
],
"prompt_number": 3
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex 1.4 Page 22"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"#input data\n",
"W=100#Output power developed in kW\n",
"Q=0.1#Flow through device in m**3/s\n",
"d=800#Density of oil in kg/m**3\n",
"ntt=0.75#Total-to-total efficiency\n",
"C1=3#inlet flow velocity of oil in m/s\n",
"C2=10#outlet flow velocity of oil in m/s\n",
"\n",
"#calculations\n",
"m=d*Q#Mass flow rate of oil in kg/s\n",
"h0=-(W/m)#Change in total enthalpy in kJ/kg\n",
"h0s=(h0/ntt)#Isentropic change in total enthalpy in kJ/kg\n",
"P0=((d*h0s)*(1/100))#Change in total pressure of oil in bar\n",
"P=P0-((d/(2000*100))*(C2**2-C1**2))#Change in static pressure in bar\n",
"\n",
"#output\n",
"print '''The change in total pressure of oil is %3.1f bar\n",
"The change in static presure is %3.1f bar'''%(P0,P)"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"The change in total pressure of oil is -13.3 bar\n",
"The change in static presure is -13.7 bar\n"
]
}
],
"prompt_number": 4
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex 1.5 Page 22"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"#input data\n",
"N=4#Number of stages in turbine handling\n",
"P=0.4#Stagnation presure ratio between exit and inlet of each stage\n",
"ns1=0.86#Stage efficiency of first and second stages\n",
"ns2=0.84#Stage efficiency of third and fourth stages\n",
"r=1.4#ratio of specific heats for air\n",
"\n",
"#calculations\n",
"u=1-(P)**((r-1)/r)#constant\n",
"T03=(1-(u*ns1))**2#Temperature after the end of first two stages in (K*Cp*T01) where Cp is specific at heat at constant pressure in kJ/kg.K and T01 is initial temperature at entry of stage 1 in K\n",
"W12=u*(1+(1-(u*ns1)))*ns1#Actual work output from first two stages in (kW*Cp*T01)\n",
"W34=T03*u*(1+(1-(u*ns2)))*ns2#Actual work output from last two stages in (kW*Cp*T01)\n",
"W=(W12+W34)#Total actual work output from turbine in (kW*Cp*T01)\n",
"Ws=1-(1-u)**N#Total isentropic work due to single stage compressor in (kW*Cp*T01)\n",
"n=(W/Ws)#Overall turbine efficiency\n",
"\n",
"#output\n",
"print 'the overall efficiency of the turbine is %.1f %%'%(n*100)"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"the overall efficiency of the turbine is 89.6 %\n"
]
}
],
"prompt_number": 5
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex 1.6 Page 24"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"\n",
"from __future__ import division\n",
"from math import log10\n",
"#input data\n",
"P=1400#Pressure developed by compressor in mm W.G\n",
"P1=1.01#Initial pressure of air in bar\n",
"T1=305#Initial temperature of air in K\n",
"T2=320#Final temperature of air in K\n",
"P=1400*9.81*10**-5#Pressure developed by compressor in bar\n",
"r=1.4#ratio of specific heats for air\n",
"\n",
"#calculations\n",
"P2=P1+P#Final pressure of air in bar\n",
"T2s=T1*(P2/P1)**((r-1)/r)#Isentropic temperature at exit in K\n",
"nc=((T2s-T1)/(T2-T1))#compressor efficiency\n",
"np=((r-1)/r)*((log10(P2/P1))/(log10(T2/T1)))#Infinitesimal stage efficiency\n",
"\n",
"#output\n",
"print '''(a)The compressor efficiency is %0.2f %%\n",
"(b)The infinitesimal stage efficiency is %0.2f %%'''%(nc*100,np*100)"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"(a)The compressor efficiency is 75.43 %\n",
"(b)The infinitesimal stage efficiency is 75.88 %\n"
]
}
],
"prompt_number": 6
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex 1.7 Page 24"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"#input data\n",
"P1=1.01#Input pressure to compressor in bar\n",
"T1=305#Input temperature to compressor in K\n",
"P2=3#Output pressure from compressor in bar\n",
"r=1.4#ratio of specific heats for air\n",
"nc=0.75#compressor efficiency\n",
"\n",
"#calculations\n",
"T2s=T1*(P2/P1)**((r-1)/r)#Isentropic output temperature from compressor in K\n",
"T2=T1+((T2s-T1)/nc)#Actual output temperature from compressor in K\n",
"np=((r-1)/r)*((log10(P2/P1))/(log10(T2/T1)))#Infinitesimal efficiency of compressor\n",
"\n",
"#output\n",
"print 'The infinitesimal efficiency of the compressor is %0.1f %%'%(np*100)"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"The infinitesimal efficiency of the compressor is 78.5 %\n"
]
}
],
"prompt_number": 7
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex 1.8 Page 25"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"#input data\n",
"P=2.2#Pressure ratio across a gas turbine\n",
"n=0.88#Efficiency of a gas turbine\n",
"T1=1500#Inlet temperature of the gas in K\n",
"r=1.4#ratio of specific heats for air\n",
"\n",
"#calculations\n",
"T2s=T1*(1/P)**((r-1)/r)#Isentropic output temperature from gas turbine in K\n",
"T2=T1-(n*(T1-T2s))#actual output temperature from gas turbine in K\n",
"np=(r/(r-1))*((log10(T1/T2))/(log10(P)))#Polytropic efficiency of the turbine\n",
"\n",
"\n",
"#output\n",
"print 'The polytropic efficiency of the turbine is %0.1f %%'%(np*100)"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"The polytropic efficiency of the turbine is 86.7 %\n"
]
}
],
"prompt_number": 8
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex 1.9 Page 26"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"# input data\n",
"P=1.3#Pressure ratio of stages\n",
"N=8#Number of stages\n",
"m =45#The flow rate through compressor in kg/s\n",
"nc=0.8#Overall efficiency of the compressor\n",
"P1=1#Initial pressure of the air at entry in bar\n",
"T1=308#Initial temperature of the air at entry in K\n",
"r=1.4#ratio of specific heats for air\n",
"\n",
"#calculations\n",
"PN=(P)**8#Overall pressure ratio of all 8 stages\n",
"TN=PN**((r-1)/r)#Overall temperature ratio of all 8 stages\n",
"TN1s=TN*T1#Ideal exit temperature in K\n",
"TN1=((TN1s-T1)/nc)+T1#Actual exit temperature in K\n",
"PN1=PN*P1#Actual exit pressure in bar\n",
"np=((r-1)/r)*((log10(PN1/P1))/(log10(TN1/T1)))#Polytropic efficiency of the cycle\n",
"ns=((((P)**((r-1)/r))-1)/(((P)**((r-1)/(r*np)))-1))#The stage efficiency of the cycle\n",
"\n",
"#output\n",
"print '''(a)The state of air at compressor exit are-\n",
"(1)actual temperature is %3.1f K\n",
"(2)actual pressure is %3.2f bar\n",
"(b)The polytropic efficiency of the cycle is %0.f %%\n",
"(c)The stage efficiency of the cycle is %0.2f %%'''%(TN1,PN1,np*100,ns*100)"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"(a)The state of air at compressor exit are-\n",
"(1)actual temperature is 624.3 K\n",
"(2)actual pressure is 8.16 bar\n",
"(b)The polytropic efficiency of the cycle is 85 %\n",
"(c)The stage efficiency of the cycle is 84.31 %\n"
]
}
],
"prompt_number": 9
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex - 1.10 Page 27"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"from math import log10\n",
"#input data\n",
"P=11#Overall pressure ratio in three stages of a gas turbine\n",
"nt=0.88#Overall efficiency in three stages of a gas turbine\n",
"T1=1500#Temperature at inlet of a gas turbine in K\n",
"r=1.4#ratio of specific heats for air\n",
"\n",
"#calculations\n",
"T0=nt*T1*(1-(1/P)**((r-1)/r))#Overall change in temperature in all stages in K\n",
"TN1=T1-T0#Temperature at final stage of a gas turbine in K\n",
"np=((r/(r-1))*log10(T1/TN1))/(log10(P))#Overall polytropic efficiency of the gas turbine\n",
"Ts=T0/3#Individual stage change in temperature in K\n",
"T2=T1-Ts#Exit temperature at the end of first stage in K\n",
"P1=(T1/T2)**(r/(np*(r-1)))#Pressure ratio at first stage of gas turbine \n",
"ns1=((1-(1/P1)**((np*(r-1))/r))/(1-(1/P1)**((r-1)/r)))#Stage efficiency of first stage \n",
"T3=T2-Ts#Exit temperature at the end of second stage in K\n",
"P2=(T2/T3)**(r/(np*(r-1)))#Pressure ratio at second stage of gas turbine\n",
"ns2=((1-(1/P2)**((np*(r-1))/r))/(1-(1/P2)**((r-1)/r)))#Stage efficiency of second stage\n",
"T4=T3-Ts#Exit temperature at the end of third stage in K\n",
"P3=(T3/T4)**(r/(np*(r-1)))#Pressure ratio at the third stage of gas turbine\n",
"ns3=((1-(1/P3)**((np*(r-1))/r))/(1-(1/P3)**((r-1)/r)))#Stage efficiency of third stage\n",
"\n",
"#output\n",
"print '''(a)The values for first stage are -\n",
"(1)Pressure ratio is %3.2f\n",
"(2)stage efficiency is %0.2f %%\n",
"(b)The values of second stage are -\n",
"(1)Pressure ratio is %3.3f\n",
"(2)Stage efficiency is %0.1f %%\n",
"(c)The values of third stage are -\n",
"(1)Pressure ratio is %3.2f\n",
"(2)Stage efficiency is %0.2f'''%(P1,ns1*100,P2,ns2*100,P3,ns3*100)"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"(a)The values for first stage are -\n",
"(1)Pressure ratio is 1.93\n",
"(2)stage efficiency is 84.96 %\n",
"(b)The values of second stage are -\n",
"(1)Pressure ratio is 2.182\n",
"(2)Stage efficiency is 85.2 %\n",
"(c)The values of third stage are -\n",
"(1)Pressure ratio is 2.61\n",
"(2)Stage efficiency is 85.52\n"
]
}
],
"prompt_number": 10
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex 1.11 Page 29 "
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"#input data\n",
"N=4#Number of stages in compressor\n",
"m=45#mass flow rate of air delivered by compressor in kg/s\n",
"P1=1.2#Pressure ratio at first stage\n",
"ns=0.65#Stage efficiency of first stage\n",
"r=1.4#ratio of specific heats for air\n",
"Cp=1.005#specific at heat at constant pressure in kJ/kg.K\n",
"T1=293#Temperature of air at inlet in K\n",
"\n",
"#calculations\n",
"P=(P1)**N#Overall pressure in all 4 stages\n",
"np=((r-1)/r)*((log10(P1))/(log10((((P1**((r-1)/r))-1)/ns)+1)))#Polytropic efficiency of the cycle\n",
"nc=(((P1**(N*((r-1)/r)))-1)/((P1**(N*((r-1)/(r*np))))-1))#Overall efficiency of the cycle\n",
"TN1=T1*((P1**(N))**((r-1)/(r*np)))#Final temperature at the exit of the compressor at final stage in K\n",
"W=m*Cp*(TN1-T1)#Power required to drive the compressor in kW\n",
"\n",
"#output\n",
"\n",
"print '''(a)The overall pressure ratio of the process is %3.1f\n",
"(b)The overall efficiency of the process is %0.2f %%\n",
"(c)The power required to drive the compressor is %3.2f kW'''%(P,nc*100,W)\n",
"# the answer in the textbook is not correct."
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"(a)The overall pressure ratio of the process is 2.1\n",
"(b)The overall efficiency of the process is 62.29 %\n",
"(c)The power required to drive the compressor is 4928.55 kW\n"
]
}
],
"prompt_number": 11
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex 1.12 Page 31 "
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"#input data\n",
"P0=0.2*9.81*(10**3)*(10**-5)#Total increase in pressure in bar\n",
"P01=1.04#Total inlet pressure of air in bar\n",
"T01=291#Total inlet temperature of air in K\n",
"ntt=0.72#Total-to-total efficiency of the process\n",
"r=1.4#ratio of specific heats for air\n",
"Cp=1.005#specific at heat at constant pressure in kJ/kg.K\n",
"\n",
"#calculations\n",
"P2=P0+P01#The total exit pressure in bar\n",
"T02=((((P2/P01)**((r-1)/r)-1)*T01)/ntt)+T01#Total temperature at the outlet in K\n",
"h0=Cp*(T02-T01)#Actual change in total enthalpy in kJ/kg\n",
"h0s=h0*ntt#Isentropic change in total enthalpy in kJ/kg\n",
"\n",
"#output\n",
"print '''(a)The total exit pressure is %3.4f bar\n",
"and the total exit temperature is %3.2f K\n",
"(b)The actual change in total enthalpy is %3.3f kJ/kg\n",
"and the isentropic change in total enthalpy is %3.3f kJ/kg'''%(P2,T02,h0,h0s)"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"(a)The total exit pressure is 1.0596 bar\n",
"and the total exit temperature is 293.16 K\n",
"(b)The actual change in total enthalpy is 2.175 kJ/kg\n",
"and the isentropic change in total enthalpy is 1.566 kJ/kg\n"
]
}
],
"prompt_number": 12
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex 1.13 Page 31"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"#input data\n",
"P=5#Pressure ratio in the process\n",
"ntt=0.8#Total-to-total efficiency of the process\n",
"m=5#Air flow rate through turbine in kg/s\n",
"W=500#Total power output from the turbine in kW\n",
"r=1.4#ratio of specific heats for air\n",
"Cp=1.005*10**3#specific at heat at constant pressure in J/kg.K\n",
"C2=100#Flow velocity of air in m/s\n",
"\n",
"#calculations\n",
"T=(W*10**3)/(m*Cp)#Total change in temperature in the process in K\n",
"T02s=(1/P)**((r-1)/r)#Isentropic temperature at the outlet from turvine in (K*T01)\n",
"T01=(T/ntt)*(1/(1-0.631))#Inlet total temperature in K\n",
"T02=T01-T#Actual exit total temperature in K\n",
"T2=T02-((C2**2)/(2*Cp))#Actual exit static temperature in K\n",
"T02s1=T02s*T01#Isentropic temperature at the outlet from turbine in K\n",
"T2s=T02s1-((C2**2)/(2*Cp))#Actual isentropic temperature in K\n",
"nts=(T/(T01-T2s))#Total-to-static efficiency\n",
"\n",
"#output\n",
"print '''(a)The inlet total temperature is %i K\n",
"(b)The actual exit total temperature is %3.1f K\n",
"(c)The actual exit static temperature is %3.1f K\n",
"(d)The total-to-static efficiency is %0.2f %%'''%(T01,T02,T2,nts*100)"
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"(a)The inlet total temperature is 337 K\n",
"(b)The actual exit total temperature is 237.6 K\n",
"(c)The actual exit static temperature is 232.6 K\n",
"(d)The total-to-static efficiency is 77.00 %\n"
]
}
],
"prompt_number": 13
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Ex 1.14 Page 33 "
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"from math import log\n",
"#input data\n",
"N=3#Number of stages in turbine\n",
"P=2#Pressure ratio of each stage\n",
"ns=0.75#Stage efficiency of each stage\n",
"T1=873#Initial temperature of air in K\n",
"m=25#Flow rate of air in kg/s\n",
"r=1.4#ratio of specific heats for air\n",
"Cp=1.005#specific at heat at constant pressure in J/kg.K\n",
"\n",
"#calculations\n",
"np=(r/(r-1))*((log(1-(ns*(1-(1/P)**((r-1)/r)))))/(log(1/P)))#Polytropic efficiency of the process\n",
"nt=((1-(1/P)**(N*np*((r-1)/r)))/(1-(1/P)**(N*((r-1)/r))))#Overall efficiency of the turbine\n",
"W=m*Cp*T1*(1-(1/P)**(N*np*((r-1)/r)))#Power developed by the turbine in kW\n",
"RF=nt/ns#Reheat factor of the process\n",
"\n",
"#output\n",
"print '''(a)The overall efficiency of the turbine is %0.2f %%\n",
"(b)The power developed by the turbine is %i kW\n",
"(c)The reheat factor of the process is %3.2f'''%(nt*100,W,RF)\n",
"\n",
"#comments\n",
"# the answer in the textbook is not correct."
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"(a)The overall efficiency of the turbine is 78.63 %\n",
"(b)The power developed by the turbine is 7725 kW\n",
"(c)The reheat factor of the process is 1.05\n"
]
}
],
"prompt_number": 14
}
],
"metadata": {}
}
]
}