From 4d1ca7b1df442eecbfa848f57406a6991d93e617 Mon Sep 17 00:00:00 2001 From: Trupti Kini Date: Thu, 1 Dec 2016 23:30:29 +0600 Subject: Added(A)/Deleted(D) following books A Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/Chapter10.ipynb A Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/Chapter2.ipynb A Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/Chapter3.ipynb A Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/Chapter4.ipynb A Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/Chapter5.ipynb A Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/Chapter6.ipynb A Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/Chapter7.ipynb A Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/Chapter8.ipynb A Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/Chapter9.ipynb A Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/screenshots/chapter6.png A Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/screenshots/chapter7.png A Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/screenshots/chapter8.png A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_2UiB4Er.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_5OAJDoI.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_5vybg0X.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_BKMHuy0.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_EqCg1Kp.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_Gtv6wpV.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_KZMvfEM.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_LWZh6RX.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_QQNAaYJ.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_RzQ3h7U.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_UPQ0l86.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_ZfwEJOD.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_e8evOCy.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_hEvrWua.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_m2RHxZQ.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_n4gN723.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_nq61Omj.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_oRPLRB9.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_oZwf58k.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_ocmC4MO.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_rP0FHeX.ipynb A Physics_For_Students_Of_Science_And_Engineering_Part_2_by_D_Halliday_and_R_Resnick/Cha_ynorwrj.ipynb --- .../Chapter5.ipynb | 167 +++++++++++++++++++++ 1 file changed, 167 insertions(+) create mode 100644 Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/Chapter5.ipynb (limited to 'Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/Chapter5.ipynb') diff --git a/Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/Chapter5.ipynb b/Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/Chapter5.ipynb new file mode 100644 index 00000000..62ce6439 --- /dev/null +++ b/Fluid_Mechanics,Thermodynamics_of_Turbomachinery_by_S.L.Dixon/Chapter5.ipynb @@ -0,0 +1,167 @@ +{ + "metadata": { + "name": "", + "signature": "sha256:58be2ba5e7552ab96c774dd3b25145aaa3c2ce840367ab463ac8e75c36ccb849" + }, + "nbformat": 3, + "nbformat_minor": 0, + "worksheets": [ + { + "cells": [ + { + "cell_type": "heading", + "level": 1, + "metadata": {}, + "source": [ + "Chapter5-Axial-flow Compressors and Fans" + ] + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Ex1-pg156" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "import math\n", + "#calculate the\n", + "\n", + "##given data\n", + "T01 = 293.;##in K\n", + "pi = 5.;##pressure ratio\n", + "R = 0.5;##stage reaction\n", + "Um = 275.;##in m/s\n", + "phi = 0.5;##flow coefficient\n", + "psi = 0.3;##stage loading factor\n", + "eff_stage = 0.888;##stage efficiency\n", + "Cp = 1005.;##J/(kgC)\n", + "gamma = 1.4;\n", + "\n", + "##Calculations\n", + "beta1 = (180./math.pi)*math.atan((R + 0.5*psi)/phi);\n", + "beta2 = (180./math.pi)*math.atan((R - 0.5*psi)/phi);\n", + "alpha2 = beta1;\n", + "alpha1 = beta2;\n", + "delT0 = psi*(Um**2)/Cp;\n", + "N = (T01/delT0)*((pi**((gamma-1.)/(eff_stage*gamma))) - 1.);\n", + "N = math.ceil(N);\n", + "eff_ov = ((pi**((gamma-1.)/gamma)) - 1.)/((pi**((gamma-1.)/(eff_stage*gamma))) - 1.);\n", + "print'%s %.2f %s %.2f %s'%('The flow angles are: beta1 = alpha2 = ',beta1,' deg' and 'beta2 = alpha1 = ',math.ceil(beta2),' deg.');\n", + "print'%s %.2f %s '%('\\n The number of stages required = ',N,'');\n", + "print'%s %.2f %s'%('\\n The overall efficiency = ',eff_ov*100,' percentage');\n", + "\n", + "##there is a small error in the answer given in textbook\n" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "The flow angles are: beta1 = alpha2 = 52.43 beta2 = alpha1 = 35.00 deg.\n", + "\n", + " The number of stages required = 9.00 \n", + "\n", + " The overall efficiency = 86.06 percentage\n" + ] + } + ], + "prompt_number": 1 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Ex2-pg160" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "import math\n", + "#calculate the\n", + "\n", + "##given data\n", + "R = 0.5;##stage reaction\n", + "s_c = 0.9;##space-chord ratio\n", + "beta1_ = 44.5;##in deg\n", + "beta2_ = -0.5;##in deg\n", + "h_c = 2.0;##height-chord ratio\n", + "lamda = 0.86;##work done factor\n", + "i = 0.4;##mean radius relative incidence\n", + "rho = 3.5;##density in kg/m^3\n", + "Um = 242.;##in m/s\n", + "eps_max = 37.5;##in deg\n", + "eps = 37.5;##in deg\n", + "delp0 = 0.032;##the profile total pressure loss coefficient\n", + "##Calculations\n", + "theta = beta1_ - beta2_;\n", + "deltaN = (0.229*theta*(s_c**0.5))/(1 - (theta*(s_c**0.5)/500.));\n", + "beta2N = deltaN + beta2_;\n", + "eps_ = 0.8*eps_max;\n", + "i_ = beta2N + eps_ - beta1_;\n", + "i = 0.4*eps_ + i_;\n", + "beta1 = beta1_ + i;\n", + "beta2 = beta1 - eps;\n", + "alpha2 = beta1;\n", + "alpha1 = beta2;\n", + "phi = 1/(math.tan(alpha1*math.pi/180.) + math.tan(beta1*math.pi/180.));\n", + "psi = lamda*phi*(math.tan(alpha2*math.pi/180.) - math.tan(alpha1*math.pi/180.));\n", + "betam = (180./math.pi)*math.atan(0.5*(math.tan(beta1*math.pi/180.) + math.tan(beta2*math.pi/180.)));\n", + "CL = 2*s_c*math.cos(betam*math.pi/180.)*(math.tan(beta1*math.pi/180.) - math.tan(beta2*math.pi/180.));\n", + "CDp = s_c*(delp0)*((math.cos(betam*math.pi/180.))**3)/((math.cos(beta1*math.pi/180.))**2);\n", + "CDa = 0.02*s_c/h_c;\n", + "CDx = 0.018*CL**2;\n", + "CD = CDp + CDa + CDx;\n", + "eff_tt = 1. - (CD*phi**2)/(psi*s_c*((math.cos(betam*math.pi/180.))**3));\n", + "delp = eff_tt*psi*rho*Um**2;\n", + "\n", + "##Results\n", + "print'%s %.2f %s %.2f %s'%('(i)The nominal deflection= ',eps_,' deg'and '.\\n the nominal incidence = ',i_,' deg.');\n", + "print'%s %.2f %s %.2f %s '%('\\n (ii)The inlet flow angle, beta1 = alpha2 = ',beta1,' deg'and '\\n outlet flow angle beta2 = alpha1 = ',beta2,' deg.');\n", + "print'%s %.2f %s %.2f %s '%('\\n (iii)The flow coefficient = ',phi,''and '\\nThe stage loading factor = ',psi,'');\n", + "print'%s %.2f %s'%('\\n (iv) The rotor lift coefficient = ',CL,'');\n", + "print'%s %.2f %s '%('\\n (v) The overall drag coefficient of each row = ',CD,'');\n", + "print'%s %.2f %s %.2f %s'%('\\n (vi) The total-to-total stage efficiency = ',eff_tt,''and '\\n The pressure rise across the stage =',delp/1000,' kPa');\n", + "\n", + "\n", + "##there are small errors in the answers given in textbook\n" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "(i)The nominal deflection= 30.00 .\n", + " the nominal incidence = -4.31 deg.\n", + "\n", + " (ii)The inlet flow angle, beta1 = alpha2 = 52.19 \n", + " outlet flow angle beta2 = alpha1 = 14.69 deg. \n", + "\n", + " (iii)The flow coefficient = 0.64 0.57 \n", + "\n", + " (iv) The rotor lift coefficient = 1.46 \n", + "\n", + " (v) The overall drag coefficient of each row = 0.09 \n", + "\n", + " (vi) The total-to-total stage efficiency = 0.86 100.34 kPa\n" + ] + } + ], + "prompt_number": 2 + } + ], + "metadata": {} + } + ] +} \ No newline at end of file -- cgit