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diff --git a/Basic_Engineering_Thermodynamics_by_R_Joel/12-Nozzle.ipynb b/Basic_Engineering_Thermodynamics_by_R_Joel/12-Nozzle.ipynb new file mode 100644 index 0000000..094eaa5 --- /dev/null +++ b/Basic_Engineering_Thermodynamics_by_R_Joel/12-Nozzle.ipynb @@ -0,0 +1,274 @@ +{ +"cells": [ + { + "cell_type": "markdown", + "metadata": {}, + "source": [ + "# Chapter 12: Nozzle" + ] + }, +{ + "cell_type": "markdown", + "metadata": {}, + "source": [ + "## Example 12.1: area_and_Mach_number.sce" + ] + }, + { +"cell_type": "code", + "execution_count": null, + "metadata": { + "collapsed": true + }, + "outputs": [], +"source": [ +"clear;\n", +"clc;\n", +"disp('Example 12.1');\n", +"\n", +"// aim : To determine the\n", +"// (a) throat area\n", +"// (b) exit area\n", +"// (c) Mach number at exit\n", +"\n", +"// Given values\n", +"P1 = 3.5;// inlet pressure of air, [MN/m^2]\n", +"T1 = 273+500;// inlet temperature of air, [MN/m^2]\n", +"P2 = .7;// exit pressure, [MN/m^2]\n", +"m_dot = 1.3;// flow rate of air, [kg/s]\n", +"Gamma = 1.4;// heat capacity ratio\n", +"R = .287;// [kJ/kg K]\n", +"\n", +"// solution\n", +"// given expansion may be considered to be adiabatic and to follow the law PV^Gamma=constant\n", +"// using ideal gas law\n", +"v1 = R*T1/P1*10^-3;// [m^3/kg]\n", +"Pt = P1*(2/(Gamma+1))^(Gamma/(Gamma-1));// critical pressure, [MN/m^2]\n", +"\n", +"// velocity at throat is\n", +"Ct = sqrt(2*Gamma/(Gamma-1)*P1*10^6*v1*(1-(Pt/P1)^(((Gamma-1)/Gamma))));// [m/s]\n", +"vt = v1*(P1/Pt)^(1/Gamma);// [m^3/kg]\n", +"// using m_dot/At=Ct/vt\n", +"At = m_dot*vt/Ct*10^6;// throat area, [mm^2]\n", +"mprintf('\n (a) The throat area is = %f mm^2\n',At);\n", +"\n", +"// (b)\n", +"// at exit\n", +"C2 = sqrt(2*Gamma/(Gamma-1)*P1*10^6*v1*(1-(P2/P1)^(((Gamma-1)/Gamma))));// [m/s]\n", +"v2 = v1*(P1/P2)^(1/Gamma);// [m^3/kg]\n", +"A2 = m_dot*v2/C2*10^6;// exit area, [mm^2]\n", +"\n", +"mprintf('\n (b) The exit area is = %f mm^2\n',A2);\n", +"\n", +"// (c)\n", +"M = C2/Ct;\n", +"mprintf('\n (c) The Mach number at exit is = %f\n',M);\n", +"\n", +"// End" + ] + } +, +{ + "cell_type": "markdown", + "metadata": {}, + "source": [ + "## Example 12.2: increases_in_pressure_temperature_and_internal_energy.sce" + ] + }, + { +"cell_type": "code", + "execution_count": null, + "metadata": { + "collapsed": true + }, + "outputs": [], +"source": [ +"clear;\n", +"clc;\n", +"disp('Example 12.2');\n", +"\n", +"// aim : To determine the increases in pressure, temperature and internal energy per kg of air\n", +"\n", +"// Given values\n", +"T1 = 273;// [K]\n", +"P1 = 140;// [kN/m^2]\n", +"C1 = 900;// [m/s]\n", +"C2 = 300;// [m/s]\n", +"cp = 1.006;// [kJ/kg K]\n", +"cv =.717;// [kJ/kg K]\n", +"\n", +"// solution\n", +"R = cp-cv;// [kJ/kg K]\n", +"Gamma = cp/cv;// heat capacity ratio\n", +"// for frictionless adiabatic flow, (C2^2-C1^2)/2=Gamma/(Gamma-1)*R*(T1-T2)\n", +"\n", +"T2 =T1-((C2^2-C1^2)*(Gamma-1)/(2*Gamma*R))*10^-3; // [K]\n", +"T_inc = T2-T1;// increase in temperature [K]\n", +"\n", +"P2 = P1*(T2/T1)^(Gamma/(Gamma-1));// [MN/m^2]\n", +"P_inc = (P2-P1)*10^-3;// increase in pressure,[MN/m^2]\n", +"\n", +"U_inc = cv*(T2-T1);// Increase in internal energy per kg,[kJ/kg]\n", +"mprintf('\n The increase in pressure is = %f MN/m^2\n',P_inc);\n", +"mprintf('\n Increase in temperature is = %f K\n',T_inc);\n", +"mprintf('\n Increase in internal energy is = %f kJ/kg\n',U_inc);\n", +"\n", +"// there is minor variation in result\n", +"\n", +"// End" + ] + } +, +{ + "cell_type": "markdown", + "metadata": {}, + "source": [ + "## Example 12.3: throat_area_and_degree_of_undercooling.sce" + ] + }, + { +"cell_type": "code", + "execution_count": null, + "metadata": { + "collapsed": true + }, + "outputs": [], +"source": [ +"clear;\n", +"clc;\n", +"disp('Example 12.3');\n", +"\n", +"// aim : To determine the \n", +"// (a) throat and exit areas\n", +"// (b) degree of undercooling at exit\n", +"// Given values\n", +"P1 = 2;// inlet pressure of air, [MN/m^2]\n", +"T1 = 273+325;// inlet temperature of air, [MN/m^2]\n", +"P2 = .36;// exit pressure, [MN/m^2]\n", +"m_dot = 7.5;// flow rate of air, [kg/s]\n", +"n = 1.3;// polytropic index\n", +"\n", +"// solution\n", +"// (a)\n", +"// using steam table\n", +"v1 = .132;// [m^3/kg]\n", +"// given expansion following law PV^n=constant\n", +"\n", +"Pt = P1*(2/(n+1))^(n/(n-1));// critical pressure, [MN/m^2]\n", +"\n", +"//velocity at throat is\n", +"Ct = sqrt(2*n/(n-1)*P1*10^6*v1*(1-(Pt/P1)^(((n-1)/n))));// [m/s]\n", +"vt = v1*(P1/Pt)^(1/n);// [m^3/kg]\n", +"// using m_dot/At=Ct/vt\n", +"At = m_dot*vt/Ct*10^6;// throat area, [mm^2]\n", +"mprintf('\n (a) The throat area is = %f mm^2\n',At);\n", +"\n", +"// at exit\n", +"C2 = sqrt(2*n/(n-1)*P1*10^6*v1*(1-(P2/P1)^(((n-1)/n))));// [m/s]\n", +"v2 = v1*(P1/P2)^(1/n);// [m^3/kg]\n", +"A2 = m_dot*v2/C2*10^6;// exit area, [mm^2]\n", +"\n", +"mprintf('\n The exit area is = %f mm^2\n',A2);\n", +"\n", +"// (b)\n", +"T2 = T1*(P2/P1)^((n-1)/n);//outlet temperature, [K]\n", +"t2 = T2-273;//[C]\n", +"// at exit pressure saturation temperature is\n", +"ts = 139.9;// saturation temperature,[C]\n", +"Doc = ts-t2;// Degree of undercooling,[C]\n", +"mprintf('\n (b) The Degree of undercooling at exit is = %f C\n',Doc);\n", +"\n", +"// There is some calculation mistake in the book so answer is not matching\n", +"\n", +"// End" + ] + } +, +{ + "cell_type": "markdown", + "metadata": {}, + "source": [ + "## Example 12.4: velocities_and_areas.sce" + ] + }, + { +"cell_type": "code", + "execution_count": null, + "metadata": { + "collapsed": true + }, + "outputs": [], +"source": [ +"clear;\n", +"clc;\n", +"disp('Example 12.4');\n", +"\n", +"// aim : To determine the \n", +"// (a) throat and exit velocities\n", +"// (b) throat and exit areas\n", +"\n", +"// Given values\n", +"P1 = 2.2;// inlet pressure, [MN/m^2]\n", +"T1 = 273+260;// inlet temperature, [K]\n", +"P2 = .4;// exit pressure,[MN/m^2]\n", +"eff = .85;// efficiency of the nozzle after throat\n", +"m_dot = 11;// steam flow rate in the nozzle, [kg/s]\n", +"\n", +"// solution\n", +"// (a)\n", +"// assuming steam is following same law as previous question 12.3\n", +"Pt = .546*P1;// critical pressure,[MN/m^2]\n", +"// from Fig. 12.6\n", +"h1 = 2940;// [kJ/kg]\n", +"ht = 2790;// [kJ/kg]\n", +"\n", +"Ct = sqrt(2*(h1-ht)*10^3);// [m/s]\n", +"\n", +"// again from Fig. 12.6\n", +"h2_prime = 2590;// [kJ/kg]\n", +"// using eff = (ht-h2)/(ht-h2_prime)\n", +"\n", +"h2 = ht-eff*(ht-h2_prime); // [kJ/kg]\n", +"\n", +"C2 = sqrt(2*(h1-h2)*10^3);// [m/s]\n", +"\n", +"// (b)\n", +"// from chart\n", +"vt = .16;// [m^3/kg]\n", +"v2 = .44;// [m^3/kg]\n", +"// using m_dot*v=A*C\n", +"At = m_dot*vt/Ct*10^6;// throat area, [mm^2]\n", +"\n", +"A2 = m_dot*v2/C2*10^6;// throat area, [mm^2]\n", +"\n", +"mprintf('\n (a) The throat velocity is = %f m/s\n',Ct);\n", +"mprintf('\n The exit velocity is = %f m/s\n',C2);\n", +"mprintf('\n (b) The throat area is = %f mm^2\n',At);\n", +"mprintf('\n The throat area is = %f mm^2\n',A2);\n", +"\n", +"// End" + ] + } +], +"metadata": { + "kernelspec": { + "display_name": "Scilab", + "language": "scilab", + "name": "scilab" + }, + "language_info": { + "file_extension": ".sce", + "help_links": [ + { + "text": "MetaKernel Magics", + "url": "https://github.com/calysto/metakernel/blob/master/metakernel/magics/README.md" + } + ], + "mimetype": "text/x-octave", + "name": "scilab", + "version": "0.7.1" + } + }, + "nbformat": 4, + "nbformat_minor": 0 +} |