From d36fc3b8f88cc3108ffff6151e376b619b9abb01 Mon Sep 17 00:00:00 2001 From: kinitrupti Date: Fri, 12 May 2017 18:40:35 +0530 Subject: Revised list of TBCs --- .../Chapter_11__Impulse_and_Reaction.ipynb | 345 +++++++++++++++++++++ ...Chapter_11__Impulse_and_Reaction_Turbines.ipynb | 345 --------------------- ...Chapter_8_FREQUENCY_EFFECTS_IN_AMPLIFIERS.ipynb | 120 ------- .../Chapter_8_FREQUENCY_EFFECTS_IN.ipynb | 120 +++++++ 4 files changed, 465 insertions(+), 465 deletions(-) create mode 100755 sample_notebooks/KavinkumarD/Chapter_11__Impulse_and_Reaction.ipynb delete mode 100755 sample_notebooks/KavinkumarD/Chapter_11__Impulse_and_Reaction_Turbines.ipynb delete mode 100755 sample_notebooks/KavinkumarD/Chapter_8_FREQUENCY_EFFECTS_IN_AMPLIFIERS.ipynb create mode 100755 sample_notebooks/KavinkumarD/KavinkumarD_version_backup/Chapter_8_FREQUENCY_EFFECTS_IN.ipynb (limited to 'sample_notebooks/KavinkumarD') diff --git a/sample_notebooks/KavinkumarD/Chapter_11__Impulse_and_Reaction.ipynb b/sample_notebooks/KavinkumarD/Chapter_11__Impulse_and_Reaction.ipynb new file mode 100755 index 00000000..5415ad01 --- /dev/null +++ b/sample_notebooks/KavinkumarD/Chapter_11__Impulse_and_Reaction.ipynb @@ -0,0 +1,345 @@ +{ + "metadata": { + "name": "", + "signature": "sha256:38f9fe4fd8a5c174c9e1dd9b5dc21976f4cdd814f7eb8fcfe0c266e278f9a77b" + }, + "nbformat": 3, + "nbformat_minor": 0, + "worksheets": [ + { + "cells": [ + { + "cell_type": "heading", + "level": 1, + "metadata": {}, + "source": [ + "Chapter 11 : Impulse and Reaction Turbines" + ] + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 11.1 and Page No:454" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "import math\n", + "from __future__ import division\n", + "\n", + "#Variable declaration\n", + "p02=6; # Inlet pressure in bar\n", + "T02=900; # Inlet temperature in kelvin\n", + "p0fs=1; # Outlet pressure in bar\n", + "eff_isenT=0.85; # insentropic efficiency of turbine\n", + "alpha_2=math.radians(75); # Nozzle outlet angle in degree and conversion to radians\n", + "u=250; # Mean blade velocity in m/s\n", + "Cp=1.15*10**3; # Specific heat in J/ kg K\n", + "r=1.333; # Specific heat ratio\n", + "\n", + "#Calculations\n", + "T0fs=T02/(p02/p0fs)**((r-1)/r); # Isentropic temperature at the exit of the final stage\n", + "Del_Toverall=eff_isenT*(T02-T0fs); # Actual overall temperature drop\n", + "c2=2*u/math.sin (alpha_2); # absolute velocity\n", + "c3= c2*math.cos (alpha_2);# absolute velocity\n", + "c1=c3; # From velocity triangles\n", + "Del_Tstage=(c2**2-c1**2)/(2*Cp); # Stage temperature drop\n", + "n=Del_Toverall/Del_Tstage; # Number of stages\n", + "\n", + "#Results\n", + "print \"Number of stages n =\",round (n,0);\n", + "\n" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "Number of stages n = 3.0\n" + ] + } + ], + "prompt_number": 1 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 11.2 and Page No:455" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "import math\n", + "from __future__ import division\n", + "\n", + "#Variable declaration\n", + "N=10000; # Speed of gas turbine in rpm\n", + "T01=700+273.15; # Total head temperature at nozzle entry in kelvin\n", + "P01=4.5; #Total head pressure at nozzle entry in bar\n", + "P02=2.6; # Outlet pressure from nozzle in bar\n", + "p3=1.5;# Pressure at trbine outlet annulus in bar\n", + "M=0.5; # Mach number at outlet\n", + "alpha_2=math.radians(70); # outlet nozzle angle in degrees and conversion to radians\n", + "D=64; # Blade mean diameter in cm\n", + "m=22.5; # Mass flow rate in kg/s\n", + "eff_T=0.99; # turbine mechanical efficiency\n", + "Cp=1.147; # Specific heat in kJ/kg K\n", + "r=1.33; # Specific heat ratio\n", + "fl=0.03; # frictional loss\n", + "R=284.6; # characteristic gas constant in J/kg K\n", + "\n", + "#Calculations\n", + "eff_N=1-fl; # Nozzle efficiency\n", + "T_02=(P02/P01)**((r-1)/r)*T01; # Isentropic temperature after expansion\n", + "T02=T01-eff_N*(T01-T_02); # Actual temperature after expansion\n", + "c2=math.sqrt (2*Cp*10**3*(T01-T02)); # Absolute velocity\n", + "u=(3.14*D*10**-2*N)/60; # Mean blade velocity\n", + "# From velocity triangles\n", + "wt2=c2*math.sin( (alpha_2))-u;\n", + "ca=c2*math.cos( (alpha_2));\n", + "beta_2=(math.atan((wt2)/ca));\n", + "T3=T02/(P02/p3)**((r-1)/r); # Assuming rotor losses are negligible\n", + "c3=M*math.sqrt (r*R*T3); # Absolute velocity\n", + "beta_3=(math.atan(u/c3));\n", + "ct2=c2*math.sin((alpha_2));\n", + "P=eff_T*m*(ct2)*u/1000; # Power developed\n", + "\n", + "#Results\n", + "print \"(i).\"\n", + "print \"\\tGas angle at entry = \",round (math.degrees(beta_2),3),\"degree\"\n", + "print \"\\tGas angle at exit = \",round (math.degrees(beta_3),3),\"degree\"\n", + "print \"(ii).\"\n", + "print \"\\tPower developed = \",round(P,3),\"kW (roundoff error)\"\n" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "(i).\n", + "\tGas angle at entry = 41.411 degree\n", + "\tGas angle at exit = 51.609 degree\n", + "(ii).\n", + "\tPower developed = 3680.184 kW (roundoff error)\n" + ] + } + ], + "prompt_number": 2 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 11.3 and Page No:457" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "import math\n", + "from __future__ import division\n", + "\n", + "#Variable declaration\n", + "alpha_2=math.radians(65); # Nozzle discharge angle in degree and conversion to radians\n", + "c3=300; # Absolute velocity in m/s\n", + "alpha_3=math.radians(30); # in degrees and conversion to radians\n", + "\n", + "#Calculations\n", + "ca2=c3*math.cos (alpha_3); # Axial velocity\n", + "c2=ca2/math.cos(alpha_2); # Absolute velocity\n", + "# ca3=ca2=ca and equal blade angles then\n", + "ca=ca2;\n", + "beta_2=math.atan((c2*math.sin(alpha_2)+c3*math.sin(alpha_3))/(2*ca)); # Blade angle\n", + "beta_3=beta_2; # equal blade angles\n", + "u=c2*math.sin(alpha_2)-ca2*math.tan(beta_2); # Mean blade velocity\n", + "# From velocity triangles\n", + "ct2=c2*math.sin(alpha_2);\n", + "ct3=c3*math.sin(alpha_3);\n", + "WT=u*(ct2+ct3)/1000; # Work done\n", + "sigma=u/c2; # optimum speed ratio\n", + "eff_B=4*(sigma*math.sin(alpha_2)-sigma**2);\n", + "\n", + "#Results\n", + "print \"Blade angle = beta_2= beta_3 = \",round (math.degrees(beta_2),3),\"degree\"\n", + "print \"Power Produced = \",round(WT,3),\"kJ/kg (roundoff error)\"\n", + "print \"Blade efficiency = \",round(eff_B*100,2),\"%\"" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "Blade angle = beta_2= beta_3 = 53.692 degree\n", + "Power Produced = 143.963 kJ/kg (roundoff error)\n", + "Blade efficiency = 76.19 %\n" + ] + } + ], + "prompt_number": 3 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 11.4 and Page No:458" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "import math\n", + "from __future__ import division\n", + "\n", + "#Variable declaration\n", + "P01=7; # Pressure at inlet in bar\n", + "T01=300+273.15; # Temperature at inlet in kelvin\n", + "P02=3; # Pressure at outlet in bar\n", + "alpha_2=math.radians(70); # Nozzle angle in degree and conversion to radians\n", + "eff_N=0.9; # Isentropic efficiency of nozzle\n", + "WT=75; # Power Produced in kW\n", + "Cp=1.15; # Specific heat in kJ/kg K\n", + "r=1.33; # Specific heat ratio\n", + "\n", + "#Calculations\n", + "T_02=T01*(P02/P01)**((r-1)/r); # Isentropic temperature after expansion\n", + "T02=T01-eff_N*(T01-T_02); # Actual temperature after expansion\n", + "c2=math.sqrt (2*Cp*10**3*(T01-T02)); # Absolute velocity\n", + "# For optimum blade speed ratio\n", + "u=(c2*math.sin (alpha_2)/2); # Mean blade velocity\n", + "beta_2=math.atan((c2*math.sin(alpha_2)-u)/(c2*math.cos(alpha_2))); # Blade angle\n", + "# From velocity triangles\n", + "ct2=c2*math.sin(alpha_2);\n", + "w2=c2*math.cos(alpha_2)/math.cos(beta_2);\n", + "w3=w2; # Equal inlet and outlet angles\n", + "beta_3=54; # in degrees\n", + "ct3=w3*math.sin(beta_3)-u;\n", + "m=(WT*10**3)/(u*(ct2+ct3)); # Gas mass flow rate\n", + "\n", + "#Results\n", + "print \"Blade angle = \",round(math.degrees(beta_2),3),\"degree\"\n", + "print \"Gas Mass Flow Rate = \",round(m,3),\"kg/s\"" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "Blade angle = 53.948 degree\n", + "Gas Mass Flow Rate = 4.89 kg/s\n" + ] + } + ], + "prompt_number": 4 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 11.5 and Page No:460" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "import math\n", + "from __future__ import division\n", + "\n", + "#Variable declaration\n", + "P01=4.6; # Total head inlet pressure in bar\n", + "T01=700+273.15; # Total head inlet temperature in kelvin\n", + "P2=1.6; # Static head pressure at mean radius in bar\n", + "Dm_h=10; # Mean blade diameter/blade height\n", + "lc=0.1; # Nozzle losses coefficient\n", + "alpha_2=math.radians(60); # Nozzle outlet angle in degree and conversion to radians\n", + "Cp=1.147; # Specific heat in kJ/kg K\n", + "r=1.33; # Specific heat ratio\n", + "m=20; # Mass flow rate in kg/s\n", + "R=284.6; # characteristic gas constant in J/kg K\n", + "\n", + "#Calculations\n", + "T_2=T01*(P2/P01)**((r-1)/r); # Isentropic temperature after expansion\n", + "T2=(lc*T01+T_2)/(1+lc); # Actual temperature after expansion\n", + "c2=math.sqrt(2*Cp*10**3*(T01-T2)); # Absolute velocity\n", + "# From velocity triangles\n", + "ca=c2*math.cos(alpha_2);\n", + "row=P2*10**5/(R*T2); # Density of gas\n", + "A=m/(ca*row); # Area\n", + "Dm=math.sqrt (A*Dm_h/3.14); # Mean Diameter\n", + "h=Dm/10; # Blade height\n", + "rm=Dm/2; # Mean radius\n", + "# At root\n", + "r_root=(Dm-h)/2;\n", + "#At the tip\n", + "r_tip=(Dm+h)/2;\n", + "# Free vorte flow\n", + "ct_mean=c2*math.sin (alpha_2);\n", + "# At the root\n", + "ct2_root=(ct_mean*rm)/r_root;\n", + "alpha2_root=math.atan(ct2_root/ca);\n", + "c2_root=ct2_root/math.sin (alpha2_root);\n", + "T2_root=T01-c2_root**2/(2*Cp*10**3);\n", + "# At the tip\n", + "ct2_tip=ct_mean*rm/r_tip;\n", + "alpha2_tip = math.atan (ct2_tip/ca);\n", + "c2_tip=ct2_tip/math.sin(alpha2_tip);\n", + "T2_tip=T01-c2_tip**2/(2*Cp*10**3);\n", + "\n", + "#Results\n", + "print \"A the Root\"\n", + "print \"\\tGas Temperature at the root = \",round(T2_root,3),\"K\"\n", + "print \"\\tGas velocity at the root = \",round(c2_root,3),\"m/s\"\n", + "print \"\\tDischarge angle at the root = \",round(math.degrees(alpha2_root),3),\"degree\"\n", + "print \"\\nA the Tip\"\n", + "print \"\\tGas Temperature at the tip = \",round(T2_tip,3),\"K\"\n", + "print \"\\tGas velocity at the tip = \",round(c2_tip,3),\"m/s\"\n", + "print \"\\tDischarge angle at the tip = \",round(math.degrees(alpha2_tip),3),\"degree\"\n", + "\n" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "A the Root\n", + "\tGas Temperature at the root = 733.345 K\n", + "\tGas velocity at the root = 741.696 m/s\n", + "\tDischarge angle at the root = 62.543 degree\n", + "\n", + "A the Tip\n", + "\tGas Temperature at the tip = 795.766 K\n", + "\tGas velocity at the tip = 637.902 m/s\n", + "\tDischarge angle at the tip = 57.581 degree\n" + ] + } + ], + "prompt_number": 5 + } + ], + "metadata": {} + } + ] +} \ No newline at end of file diff --git a/sample_notebooks/KavinkumarD/Chapter_11__Impulse_and_Reaction_Turbines.ipynb b/sample_notebooks/KavinkumarD/Chapter_11__Impulse_and_Reaction_Turbines.ipynb deleted file mode 100755 index 5415ad01..00000000 --- a/sample_notebooks/KavinkumarD/Chapter_11__Impulse_and_Reaction_Turbines.ipynb +++ /dev/null @@ -1,345 +0,0 @@ -{ - "metadata": { - "name": "", - "signature": "sha256:38f9fe4fd8a5c174c9e1dd9b5dc21976f4cdd814f7eb8fcfe0c266e278f9a77b" - }, - "nbformat": 3, - "nbformat_minor": 0, - "worksheets": [ - { - "cells": [ - { - "cell_type": "heading", - "level": 1, - "metadata": {}, - "source": [ - "Chapter 11 : Impulse and Reaction Turbines" - ] - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 11.1 and Page No:454" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "import math\n", - "from __future__ import division\n", - "\n", - "#Variable declaration\n", - "p02=6; # Inlet pressure in bar\n", - "T02=900; # Inlet temperature in kelvin\n", - "p0fs=1; # Outlet pressure in bar\n", - "eff_isenT=0.85; # insentropic efficiency of turbine\n", - "alpha_2=math.radians(75); # Nozzle outlet angle in degree and conversion to radians\n", - "u=250; # Mean blade velocity in m/s\n", - "Cp=1.15*10**3; # Specific heat in J/ kg K\n", - "r=1.333; # Specific heat ratio\n", - "\n", - "#Calculations\n", - "T0fs=T02/(p02/p0fs)**((r-1)/r); # Isentropic temperature at the exit of the final stage\n", - "Del_Toverall=eff_isenT*(T02-T0fs); # Actual overall temperature drop\n", - "c2=2*u/math.sin (alpha_2); # absolute velocity\n", - "c3= c2*math.cos (alpha_2);# absolute velocity\n", - "c1=c3; # From velocity triangles\n", - "Del_Tstage=(c2**2-c1**2)/(2*Cp); # Stage temperature drop\n", - "n=Del_Toverall/Del_Tstage; # Number of stages\n", - "\n", - "#Results\n", - "print \"Number of stages n =\",round (n,0);\n", - "\n" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Number of stages n = 3.0\n" - ] - } - ], - "prompt_number": 1 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 11.2 and Page No:455" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "import math\n", - "from __future__ import division\n", - "\n", - "#Variable declaration\n", - "N=10000; # Speed of gas turbine in rpm\n", - "T01=700+273.15; # Total head temperature at nozzle entry in kelvin\n", - "P01=4.5; #Total head pressure at nozzle entry in bar\n", - "P02=2.6; # Outlet pressure from nozzle in bar\n", - "p3=1.5;# Pressure at trbine outlet annulus in bar\n", - "M=0.5; # Mach number at outlet\n", - "alpha_2=math.radians(70); # outlet nozzle angle in degrees and conversion to radians\n", - "D=64; # Blade mean diameter in cm\n", - "m=22.5; # Mass flow rate in kg/s\n", - "eff_T=0.99; # turbine mechanical efficiency\n", - "Cp=1.147; # Specific heat in kJ/kg K\n", - "r=1.33; # Specific heat ratio\n", - "fl=0.03; # frictional loss\n", - "R=284.6; # characteristic gas constant in J/kg K\n", - "\n", - "#Calculations\n", - "eff_N=1-fl; # Nozzle efficiency\n", - "T_02=(P02/P01)**((r-1)/r)*T01; # Isentropic temperature after expansion\n", - "T02=T01-eff_N*(T01-T_02); # Actual temperature after expansion\n", - "c2=math.sqrt (2*Cp*10**3*(T01-T02)); # Absolute velocity\n", - "u=(3.14*D*10**-2*N)/60; # Mean blade velocity\n", - "# From velocity triangles\n", - "wt2=c2*math.sin( (alpha_2))-u;\n", - "ca=c2*math.cos( (alpha_2));\n", - "beta_2=(math.atan((wt2)/ca));\n", - "T3=T02/(P02/p3)**((r-1)/r); # Assuming rotor losses are negligible\n", - "c3=M*math.sqrt (r*R*T3); # Absolute velocity\n", - "beta_3=(math.atan(u/c3));\n", - "ct2=c2*math.sin((alpha_2));\n", - "P=eff_T*m*(ct2)*u/1000; # Power developed\n", - "\n", - "#Results\n", - "print \"(i).\"\n", - "print \"\\tGas angle at entry = \",round (math.degrees(beta_2),3),\"degree\"\n", - "print \"\\tGas angle at exit = \",round (math.degrees(beta_3),3),\"degree\"\n", - "print \"(ii).\"\n", - "print \"\\tPower developed = \",round(P,3),\"kW (roundoff error)\"\n" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "(i).\n", - "\tGas angle at entry = 41.411 degree\n", - "\tGas angle at exit = 51.609 degree\n", - "(ii).\n", - "\tPower developed = 3680.184 kW (roundoff error)\n" - ] - } - ], - "prompt_number": 2 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 11.3 and Page No:457" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "import math\n", - "from __future__ import division\n", - "\n", - "#Variable declaration\n", - "alpha_2=math.radians(65); # Nozzle discharge angle in degree and conversion to radians\n", - "c3=300; # Absolute velocity in m/s\n", - "alpha_3=math.radians(30); # in degrees and conversion to radians\n", - "\n", - "#Calculations\n", - "ca2=c3*math.cos (alpha_3); # Axial velocity\n", - "c2=ca2/math.cos(alpha_2); # Absolute velocity\n", - "# ca3=ca2=ca and equal blade angles then\n", - "ca=ca2;\n", - "beta_2=math.atan((c2*math.sin(alpha_2)+c3*math.sin(alpha_3))/(2*ca)); # Blade angle\n", - "beta_3=beta_2; # equal blade angles\n", - "u=c2*math.sin(alpha_2)-ca2*math.tan(beta_2); # Mean blade velocity\n", - "# From velocity triangles\n", - "ct2=c2*math.sin(alpha_2);\n", - "ct3=c3*math.sin(alpha_3);\n", - "WT=u*(ct2+ct3)/1000; # Work done\n", - "sigma=u/c2; # optimum speed ratio\n", - "eff_B=4*(sigma*math.sin(alpha_2)-sigma**2);\n", - "\n", - "#Results\n", - "print \"Blade angle = beta_2= beta_3 = \",round (math.degrees(beta_2),3),\"degree\"\n", - "print \"Power Produced = \",round(WT,3),\"kJ/kg (roundoff error)\"\n", - "print \"Blade efficiency = \",round(eff_B*100,2),\"%\"" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Blade angle = beta_2= beta_3 = 53.692 degree\n", - "Power Produced = 143.963 kJ/kg (roundoff error)\n", - "Blade efficiency = 76.19 %\n" - ] - } - ], - "prompt_number": 3 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 11.4 and Page No:458" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "import math\n", - "from __future__ import division\n", - "\n", - "#Variable declaration\n", - "P01=7; # Pressure at inlet in bar\n", - "T01=300+273.15; # Temperature at inlet in kelvin\n", - "P02=3; # Pressure at outlet in bar\n", - "alpha_2=math.radians(70); # Nozzle angle in degree and conversion to radians\n", - "eff_N=0.9; # Isentropic efficiency of nozzle\n", - "WT=75; # Power Produced in kW\n", - "Cp=1.15; # Specific heat in kJ/kg K\n", - "r=1.33; # Specific heat ratio\n", - "\n", - "#Calculations\n", - "T_02=T01*(P02/P01)**((r-1)/r); # Isentropic temperature after expansion\n", - "T02=T01-eff_N*(T01-T_02); # Actual temperature after expansion\n", - "c2=math.sqrt (2*Cp*10**3*(T01-T02)); # Absolute velocity\n", - "# For optimum blade speed ratio\n", - "u=(c2*math.sin (alpha_2)/2); # Mean blade velocity\n", - "beta_2=math.atan((c2*math.sin(alpha_2)-u)/(c2*math.cos(alpha_2))); # Blade angle\n", - "# From velocity triangles\n", - "ct2=c2*math.sin(alpha_2);\n", - "w2=c2*math.cos(alpha_2)/math.cos(beta_2);\n", - "w3=w2; # Equal inlet and outlet angles\n", - "beta_3=54; # in degrees\n", - "ct3=w3*math.sin(beta_3)-u;\n", - "m=(WT*10**3)/(u*(ct2+ct3)); # Gas mass flow rate\n", - "\n", - "#Results\n", - "print \"Blade angle = \",round(math.degrees(beta_2),3),\"degree\"\n", - "print \"Gas Mass Flow Rate = \",round(m,3),\"kg/s\"" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "Blade angle = 53.948 degree\n", - "Gas Mass Flow Rate = 4.89 kg/s\n" - ] - } - ], - "prompt_number": 4 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 11.5 and Page No:460" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "import math\n", - "from __future__ import division\n", - "\n", - "#Variable declaration\n", - "P01=4.6; # Total head inlet pressure in bar\n", - "T01=700+273.15; # Total head inlet temperature in kelvin\n", - "P2=1.6; # Static head pressure at mean radius in bar\n", - "Dm_h=10; # Mean blade diameter/blade height\n", - "lc=0.1; # Nozzle losses coefficient\n", - "alpha_2=math.radians(60); # Nozzle outlet angle in degree and conversion to radians\n", - "Cp=1.147; # Specific heat in kJ/kg K\n", - "r=1.33; # Specific heat ratio\n", - "m=20; # Mass flow rate in kg/s\n", - "R=284.6; # characteristic gas constant in J/kg K\n", - "\n", - "#Calculations\n", - "T_2=T01*(P2/P01)**((r-1)/r); # Isentropic temperature after expansion\n", - "T2=(lc*T01+T_2)/(1+lc); # Actual temperature after expansion\n", - "c2=math.sqrt(2*Cp*10**3*(T01-T2)); # Absolute velocity\n", - "# From velocity triangles\n", - "ca=c2*math.cos(alpha_2);\n", - "row=P2*10**5/(R*T2); # Density of gas\n", - "A=m/(ca*row); # Area\n", - "Dm=math.sqrt (A*Dm_h/3.14); # Mean Diameter\n", - "h=Dm/10; # Blade height\n", - "rm=Dm/2; # Mean radius\n", - "# At root\n", - "r_root=(Dm-h)/2;\n", - "#At the tip\n", - "r_tip=(Dm+h)/2;\n", - "# Free vorte flow\n", - "ct_mean=c2*math.sin (alpha_2);\n", - "# At the root\n", - "ct2_root=(ct_mean*rm)/r_root;\n", - "alpha2_root=math.atan(ct2_root/ca);\n", - "c2_root=ct2_root/math.sin (alpha2_root);\n", - "T2_root=T01-c2_root**2/(2*Cp*10**3);\n", - "# At the tip\n", - "ct2_tip=ct_mean*rm/r_tip;\n", - "alpha2_tip = math.atan (ct2_tip/ca);\n", - "c2_tip=ct2_tip/math.sin(alpha2_tip);\n", - "T2_tip=T01-c2_tip**2/(2*Cp*10**3);\n", - "\n", - "#Results\n", - "print \"A the Root\"\n", - "print \"\\tGas Temperature at the root = \",round(T2_root,3),\"K\"\n", - "print \"\\tGas velocity at the root = \",round(c2_root,3),\"m/s\"\n", - "print \"\\tDischarge angle at the root = \",round(math.degrees(alpha2_root),3),\"degree\"\n", - "print \"\\nA the Tip\"\n", - "print \"\\tGas Temperature at the tip = \",round(T2_tip,3),\"K\"\n", - "print \"\\tGas velocity at the tip = \",round(c2_tip,3),\"m/s\"\n", - "print \"\\tDischarge angle at the tip = \",round(math.degrees(alpha2_tip),3),\"degree\"\n", - "\n" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "A the Root\n", - "\tGas Temperature at the root = 733.345 K\n", - "\tGas velocity at the root = 741.696 m/s\n", - "\tDischarge angle at the root = 62.543 degree\n", - "\n", - "A the Tip\n", - "\tGas Temperature at the tip = 795.766 K\n", - "\tGas velocity at the tip = 637.902 m/s\n", - "\tDischarge angle at the tip = 57.581 degree\n" - ] - } - ], - "prompt_number": 5 - } - ], - "metadata": {} - } - ] -} \ No newline at end of file diff --git a/sample_notebooks/KavinkumarD/Chapter_8_FREQUENCY_EFFECTS_IN_AMPLIFIERS.ipynb b/sample_notebooks/KavinkumarD/Chapter_8_FREQUENCY_EFFECTS_IN_AMPLIFIERS.ipynb deleted file mode 100755 index 60448e3c..00000000 --- a/sample_notebooks/KavinkumarD/Chapter_8_FREQUENCY_EFFECTS_IN_AMPLIFIERS.ipynb +++ /dev/null @@ -1,120 +0,0 @@ -{ - "metadata": { - "name": "", - "signature": "sha256:8ef023228932ba7c44f0f72b79793f31a32f8ea67eae875510cf71ee015fc22c" - }, - "nbformat": 3, - "nbformat_minor": 0, - "worksheets": [ - { - "cells": [ - { - "cell_type": "heading", - "level": 1, - "metadata": {}, - "source": [ - "Chapter 8 FREQUENCY EFFECTS IN AMPLIFIERS" - ] - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 8.6 , Page no:242" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "import math\n", - "from __future__ import division\n", - "\n", - "#initialisation of variables\n", - "hie=1000 #\u2126\n", - "hfe=75 #\u2126\n", - "Av=50\n", - "Rl=10000 #k\u2126\n", - "hie2=300 #\u2126\n", - "hfe2=100 #\u2126\n", - "Re=1000 #k\u2126\n", - "\n", - "#CALCULATIONS\n", - "Req=Av*(hie/hfe) #\u2126\n", - "Rc=Req*Rl/(Rl-Req) #k\u2126\n", - "wL=2*3.14*200\n", - "Ce=(hie2+(hfe2+1)*Re)/(wL*Re*hie2)*10**6\n", - "Av1=(hfe*Req)/(hie+(hfe+1)*Re)\n", - "\n", - "#RESULTS\n", - "print\"The value of Req=\",round(Req,3),\"Ohm\";\n", - "print\"The value of Rc=\",round(Rc,3),\"Ohm\";\n", - "print\"The value of Ce=\",round(Ce,3),\"mF\";\n", - "print\"The value of Av=\",round(Av1,3);" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "The value of Req= 666.667 Ohm\n", - "The value of Rc= 714.286 Ohm\n", - "The value of Ce= 268.843 mF\n", - "The value of Av= 0.649\n" - ] - } - ], - "prompt_number": 1 - }, - { - "cell_type": "heading", - "level": 2, - "metadata": {}, - "source": [ - "Example 8.8 , Page no:244" - ] - }, - { - "cell_type": "code", - "collapsed": false, - "input": [ - "import math\n", - "from __future__ import division\n", - "\n", - "#initialisation of variables\n", - "hie2=1500 #\u2126\n", - "Rb2=5000 #k\u2126\n", - "Z01=10\n", - "Av=7881.3\n", - "\n", - "#CALCULATIONS\n", - "C2=1*10**-6 \n", - "Zin2=(hie2*Rb2/(hie2+Rb2))\n", - "fl=1/(2*3.14*C2*(Zin2+Z01*10**3))\n", - "\n", - "#RESULTS\n", - "print\"The value of Zin2=\",round(Zin2,3),\"Ohm\";\n", - "print\"The value of fl=\",round(fl,3),\"Hz\";" - ], - "language": "python", - "metadata": {}, - "outputs": [ - { - "output_type": "stream", - "stream": "stdout", - "text": [ - "The value of Zin2= 1153.846 Ohm\n", - "The value of fl= 14.276 Hz\n" - ] - } - ], - "prompt_number": 2 - } - ], - "metadata": {} - } - ] -} \ No newline at end of file diff --git a/sample_notebooks/KavinkumarD/KavinkumarD_version_backup/Chapter_8_FREQUENCY_EFFECTS_IN.ipynb b/sample_notebooks/KavinkumarD/KavinkumarD_version_backup/Chapter_8_FREQUENCY_EFFECTS_IN.ipynb new file mode 100755 index 00000000..60448e3c --- /dev/null +++ b/sample_notebooks/KavinkumarD/KavinkumarD_version_backup/Chapter_8_FREQUENCY_EFFECTS_IN.ipynb @@ -0,0 +1,120 @@ +{ + "metadata": { + "name": "", + "signature": "sha256:8ef023228932ba7c44f0f72b79793f31a32f8ea67eae875510cf71ee015fc22c" + }, + "nbformat": 3, + "nbformat_minor": 0, + "worksheets": [ + { + "cells": [ + { + "cell_type": "heading", + "level": 1, + "metadata": {}, + "source": [ + "Chapter 8 FREQUENCY EFFECTS IN AMPLIFIERS" + ] + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 8.6 , Page no:242" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "import math\n", + "from __future__ import division\n", + "\n", + "#initialisation of variables\n", + "hie=1000 #\u2126\n", + "hfe=75 #\u2126\n", + "Av=50\n", + "Rl=10000 #k\u2126\n", + "hie2=300 #\u2126\n", + "hfe2=100 #\u2126\n", + "Re=1000 #k\u2126\n", + "\n", + "#CALCULATIONS\n", + "Req=Av*(hie/hfe) #\u2126\n", + "Rc=Req*Rl/(Rl-Req) #k\u2126\n", + "wL=2*3.14*200\n", + "Ce=(hie2+(hfe2+1)*Re)/(wL*Re*hie2)*10**6\n", + "Av1=(hfe*Req)/(hie+(hfe+1)*Re)\n", + "\n", + "#RESULTS\n", + "print\"The value of Req=\",round(Req,3),\"Ohm\";\n", + "print\"The value of Rc=\",round(Rc,3),\"Ohm\";\n", + "print\"The value of Ce=\",round(Ce,3),\"mF\";\n", + "print\"The value of Av=\",round(Av1,3);" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "The value of Req= 666.667 Ohm\n", + "The value of Rc= 714.286 Ohm\n", + "The value of Ce= 268.843 mF\n", + "The value of Av= 0.649\n" + ] + } + ], + "prompt_number": 1 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 8.8 , Page no:244" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "import math\n", + "from __future__ import division\n", + "\n", + "#initialisation of variables\n", + "hie2=1500 #\u2126\n", + "Rb2=5000 #k\u2126\n", + "Z01=10\n", + "Av=7881.3\n", + "\n", + "#CALCULATIONS\n", + "C2=1*10**-6 \n", + "Zin2=(hie2*Rb2/(hie2+Rb2))\n", + "fl=1/(2*3.14*C2*(Zin2+Z01*10**3))\n", + "\n", + "#RESULTS\n", + "print\"The value of Zin2=\",round(Zin2,3),\"Ohm\";\n", + "print\"The value of fl=\",round(fl,3),\"Hz\";" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "The value of Zin2= 1153.846 Ohm\n", + "The value of fl= 14.276 Hz\n" + ] + } + ], + "prompt_number": 2 + } + ], + "metadata": {} + } + ] +} \ No newline at end of file -- cgit