initial commit / add all books

6 files changed, 220 insertions, 0 deletions

diff --git a/3407/CH8/EX8.1/Ex8_1.sce b/3407/CH8/EX8.1/Ex8_1.sce
new file mode 100644
index 000000000..d7262a175
--- /dev/null
+++ b/3407/CH8/EX8.1/Ex8_1.sce
@@ -0,0 +1,26 @@
+clear;

+clc;

+funcprot(0);

+

+//given data

+D2 = 23.76;//diameter of rotor in cm

+N = 38140;//rotational speed in rev/min

+alpha2 = 72;//absolute flow angle in deg

+d = 0.5*D2;//rotor mean exit diameter

+

+//Calcultaions

+U2 = %pi*N*D2/(100*60);

+w2 = U2/tan(alpha2*%pi/180);

+c2 = U2*sin(alpha2*%pi/180);

+w3 = 2*w2;

+U3 = 0.5*U2;

+c3 = sqrt(w3^2 - U3^2);

+delW = 0.5*((U2^2 - U3^2)+(w3^2 - w2^2)+(c2^2 - c3^2));

+inp_U2 =  0.5*(U2^2 - U3^2)/delW;

+inp_w2 = 0.5*(w3^2 - w2^2)/delW;

+inp_c2 = 0.5*(c2^2 - c3^2)/delW;

+

+//Results

+printf('The fractional inputs from the three terms are, for the U^2 terms, %.3f; \n for the w^2 terms, %.3f; for the c^2 terms, %.3f.',inp_U2,inp_w2,inp_c2);

+

+//there are errors in the answers given in textbook

diff --git a/3407/CH8/EX8.2/Ex8_2.sce b/3407/CH8/EX8.2/Ex8_2.sce
new file mode 100644
index 000000000..52959b6f2
--- /dev/null
+++ b/3407/CH8/EX8.2/Ex8_2.sce
@@ -0,0 +1,40 @@
+clear;

+clc;

+funcprot(0);

+

+//given data

+r = 1.5;//operating pressure ratio

+K1 = 1.44*10^-5;

+K2 = 2410;

+K3 = 4.59*10^-6;

+T01 = 400;//in K

+D2 = 72.5;//rotor inlet diamete in mm

+D3_av = 34.4;//rotor meaan outlet diameter in mm

+b = 20.1;//rotor outlet annulus width in mm

+zetaN = 0.065;//enthalpy loss coefficient

+alpha2 = 71;//in deg

+beta3_av = 53;//in deg

+Cp = 1005;//inJ/(kg.K)

+gamma = 1.4;

+

+//Calculations

+N = K2*sqrt(T01);

+U2 = %pi*N*D2/(60*1000)

+delW = U2^2;

+delh = Cp*T01*(1-(1/r)^((gamma-1)/gamma));

+eff_ts = delW/(delh);

+delW_act = K3*K2*%pi*T01/(30*K1);

+eff_ov = delW_act/delh;

+zetaR = (2*((1/eff_ts)-1) - (zetaN/sin(alpha2*%pi/180)))*((D2/D3_av)^2)*(sin(beta3_av*%pi/180))^2 - (cos(beta3_av*%pi/180))^2;

+r3 = 0.5*(D3_av-b)*10^-3;

+w3_w2av_min = (D3_av/D2)*tan(alpha2*%pi/180)*((2*r3/D3_av)^2 + (1/tan(beta3_av*%pi/180))^2)^0.5;

+w3_w2av = (D3_av/D2)*tan(alpha2*%pi/180)*(1+((1/tan(beta3_av*%pi/180))^2))^0.5;

+

+//Results

+printf('The total-to-static efficiency = %.2f percentage.',eff_ts*100);

+printf('\n The overall efficiency = %.2f percentage.',eff_ov*100);

+printf('\n The rotor enthalpy loss coefficient = %.3f',zetaR);

+printf('\n The rotor relative velocity ratio = %.2f',w3_w2av);

+

+

+//there are small errors in the answers given in textbook

diff --git a/3407/CH8/EX8.3/Ex8_3.sce b/3407/CH8/EX8.3/Ex8_3.sce
new file mode 100644
index 000000000..e2f102cc9
--- /dev/null
+++ b/3407/CH8/EX8.3/Ex8_3.sce
@@ -0,0 +1,30 @@
+clear;

+clc;

+funcprot(0);

+

+//given data

+Z = 12;//number of vanes

+delW = 230;//in kW

+T01 = 1050;//stagnation temperature in K

+mdot = 1;//flow rate in kg/s

+eff_ts = 0.81;//total-to-static efficiency

+Cp = 1.1502;//in kJ/(kg.K)

+gamma = 1.333;

+R = 287;//gas constant

+

+//Calculations

+S = delW/(Cp*T01);

+alpha2 = (180/%pi)*acos(sqrt(1/Z));

+beta2 = 2*(90-alpha2);

+p3_p01 = (1-(S/eff_ts))^(gamma/(1-gamma));

+M02 = sqrt((S/(gamma-1))*((2*cos(beta2*%pi/180))/(1+cos(beta2*%pi/180))));

+M2 = sqrt((M02^2)/(1-0.5*(gamma-1)*(M02^2)));

+U2 = sqrt((gamma*R*T01)*(1/cos(beta2*%pi/180))*(S/(gamma-1)));

+

+//Results

+printf('(i) The absolut and relative flow angles:\n alpha2 = %.2f deg\n beta2 = %.2f deg',alpha2,beta2);

+printf('\n (ii) The overall pressure ratio = %.3f',p3_p01);

+printf('\n (iii) The rotor rip speed = %.1f m/s\n The inlet absolute Mach number = %.3f',U2,M2);

+

+

+//there are small errors in the answers given in textbook

diff --git a/3407/CH8/EX8.4/Ex8_4.sce b/3407/CH8/EX8.4/Ex8_4.sce
new file mode 100644
index 000000000..3c9d29c9b
--- /dev/null
+++ b/3407/CH8/EX8.4/Ex8_4.sce
@@ -0,0 +1,19 @@
+clear;

+clc;

+funcprot(0);

+

+//given data

+cm3_U2 = 0.25;

+nu = 0.4;

+r3s_r2 = 0.7;

+w3av_w2 = 2.0;

+

+//Calculations

+r3av_r3s = 0.5*(1+nu);

+r3av_r2 = r3av_r3s*r3s_r2;

+beta3_av = (180/%pi)*atan(r3av_r2/cm3_U2);

+beta3s = (180/%pi)*atan(r3s_r2/cm3_U2);

+w3s_w2 = 2*cos(beta3_av*%pi/180)/cos(beta3s*%pi/180);

+

+//Results

+printf('The relative velocity ratio = %.3f.',w3s_w2);

diff --git a/3407/CH8/EX8.5/Ex8_5.sce b/3407/CH8/EX8.5/Ex8_5.sce
new file mode 100644
index 000000000..d1379c60d
--- /dev/null
+++ b/3407/CH8/EX8.5/Ex8_5.sce
@@ -0,0 +1,43 @@
+clear;

+clc;

+funcprot(0);

+

+//given data

+Z = 12;//number of vanes

+delW = 230;//in kW

+T01 = 1050;//stagnation temperature in K

+mdot = 1;//flow rate in kg/s

+eff_ts = 0.81;//total-to-static efficiency

+Cp = 1.1502;//in kJ/(kg.K)

+gamma = 1.333;

+R = 287;//gas constant

+cm3_U2 = 0.25;

+nu = 0.4;

+r3s_r2 = 0.7;

+w3av_w2 = 2.0;

+p3 = 100;//static pressure at rotor exit in kPa

+zetaN = 0.06;//nozzle enthalpy loss coefficient

+U2 = 538.1;//in m/s

+p01 = 3.109*10^5;//in Pa

+

+//Calculations

+S = delW/(Cp*T01);

+T03 = T01*(1-S);

+T3 = T03 - (cm3_U2^2)*(U2^2)/(2*Cp*1000);

+r2 = sqrt(mdot/((p3*1000/(R*T3))*(cm3_U2)*U2*%pi*(r3s_r2^2)*(1-nu^2)));

+D2 = 2*r2;

+omega = U2/r2;

+N = omega*30/%pi;

+ctheta2 = S*Cp*1000*T01/U2;

+alpha2 = (180/%pi)*acos(sqrt(1/Z));

+cm2 = ctheta2/tan(alpha2*%pi/180);

+c2 = ctheta2/sin(alpha2*%pi/180);

+T2 = T01 - (c2^2)/(2*Cp*1000);

+p2 = p01*(1-(((c2^2)*(1+zetaN))/(2*Cp*1000*T01)))^(gamma/(gamma-1));

+b2_D2 = (0.25/%pi)*(R*T2/p2)*(mdot/(cm2*r2^2));

+

+//Results

+printf('(i) The diamaeter of the rotor = %.4f m\n its speed of rotation = %.1f rad/s (N = %d rev/min)',D2,omega,N);

+printf('\n(ii) The vane width to diameter ratio at rotor inlet = %.4f',b2_D2);

+

+//there are some errors in the answers given in textbook

diff --git a/3407/CH8/EX8.6/Ex8_6.sce b/3407/CH8/EX8.6/Ex8_6.sce
new file mode 100644
index 000000000..35e8dbd75
--- /dev/null
+++ b/3407/CH8/EX8.6/Ex8_6.sce
@@ -0,0 +1,62 @@
+clear;

+clc;

+funcprot(0);

+

+//given data

+Z = 12;//number of vanes

+delW = 230;//in kW

+T01 = 1050;//stagnation temperature in K

+mdot = 1;//flow rate in kg/s

+eff_ts = 0.81;//total-to-static efficiency

+Cp = 1.1502;//in kJ/(kg.K)

+gamma = 1.333;

+R = 287;//gas constant

+cm3_U2 = 0.25;

+nu = 0.4;

+r3s_r2 = 0.7;

+w3av_w2 = 2.0;

+p3 = 100;//static pressure at rotor exit in kPa

+zetaN = 0.06;//nozzle enthalpy loss coefficient

+U2 = 538.1;//in m/s

+p01 = 3.109*10^5;//in Pa

+

+//results of Example 8.4 and Example 8.5

+r3av_r3s = 0.5*(1+nu);

+r3av_r2 = r3av_r3s*r3s_r2;

+alpha2 = (180/%pi)*acos(sqrt(1/Z));

+beta2 = 2*(90-alpha2);

+beta3_av = (180/%pi)*atan(r3av_r2/cm3_U2);

+beta3s = (180/%pi)*atan(r3s_r2/cm3_U2);

+w3s_w2 = 2*cos(beta3_av*%pi/180)/cos(beta3s*%pi/180);

+S = delW/(Cp*T01);

+T03 = T01*(1-S);

+T3 = T03 - (cm3_U2^2)*(U2^2)/(2*Cp*1000);

+r2 = sqrt(mdot/((p3*1000/(R*T3))*(cm3_U2)*U2*%pi*(r3s_r2^2)*(1-nu^2)));

+D2 = 2*r2;

+omega = U2/r2;

+N = omega*30/%pi;

+ctheta2 = S*Cp*1000*T01/U2;

+alpha2 = (180/%pi)*acos(sqrt(1/Z));

+cm2 = ctheta2/tan(alpha2*%pi/180);

+c2 = ctheta2/sin(alpha2*%pi/180);

+T2 = T01 - (c2^2)/(2*Cp*1000);

+p2 = p01*(1-(((c2^2)*(1+zetaN))/(2*Cp*1000*T01)))^(gamma/(gamma-1));

+b2_D2 = (0.25/%pi)*(R*T2/p2)*(mdot/(cm2*r2^2));

+

+//Calculations

+c3 = cm3_U2*U2;

+cm3 = c3;

+w3_av = 2*cm3/(cos(beta2*%pi/180));

+w2 = w3_av/2;

+c0 = sqrt(2*delW*1000/eff_ts);

+zetaR = (c0^2 *(1-eff_ts)- (c3^2)- zetaN*(c2^2))/(w3_av^2); 

+i = beta2;

+n = 1.75;

+eff_ts_new = 1-((c3^2)+zetaN*(c2^2)+zetaR*(w3_av^2)+(1-(cos(i*%pi/180))^n)*(w2^2))/(c0^2);

+

+//Results

+printf('(a)The rotor enthalpy loss coefficient = %.4f',zetaR);

+printf('\n(b) The total-to-static efficiency of the turbine = %.3f',eff_ts_new);

+

+

+//there are some errors in the answers given in textbook