diff options
Diffstat (limited to '2223/CH9/EX9.4/Ex9_4.sce')
-rwxr-xr-x | 2223/CH9/EX9.4/Ex9_4.sce | 32 |
1 files changed, 32 insertions, 0 deletions
diff --git a/2223/CH9/EX9.4/Ex9_4.sce b/2223/CH9/EX9.4/Ex9_4.sce new file mode 100755 index 000000000..1ae4688bc --- /dev/null +++ b/2223/CH9/EX9.4/Ex9_4.sce @@ -0,0 +1,32 @@ +// scilab Code Exa 9.4 axial turbine stage 3000 rpm
+
+d=1; // mean diameter of the impeller blade in m
+r=d/2;
+N=3e3; // rotor Speed in RPM
+a_r(1)=1; // aspect ratio
+a_r(2)=2;
+a_r(3)=3;
+alpha2=70; // air angle at nozzle exit
+alpha3=0;
+beta_2=54; // air angle at rotor entry
+sigma=0.5*(sind(alpha2)); // blade to gas speed ratio
+u=%pi*d*N/60;
+c2=u/sigma;
+cx=c2*(cosd(alpha2));
+beta_3=beta_2; // air angle at rotor exit
+phi=cx/u;
+e_R=beta_2+beta_3; // Rotor deflection angle
+zeeta_p_N=0.025*(1+((alpha2/90)^2)); // profile loss coefficient for nozzle
+zeeta_p_R=0.025*(1+((e_R/90)^2)); // profile loss coefficient for rotor
+for i=1:3
+disp(a_r(i),"when Aspect ratio=")
+zeeta_N=(1+(3.2/a_r(i)))*zeeta_p_N; // total loss coefficient for nozzle
+zeeta_R=(1+(3.2/a_r(i)))*zeeta_p_R; // total loss coefficient for rotor
+a=(zeeta_R*(secd(beta_3)^2))+(zeeta_N*(secd(alpha2)^2));
+b=phi*(tand(alpha2)+tand(beta_3))-1;
+c=(zeeta_R*(secd(beta_3)^2))+(zeeta_N*(secd(alpha2)^2))+(secd(alpha3)^2);
+n_tt=inv(1+(0.5*(phi^2)*(a/b)));
+disp("%",n_tt*1e2,"total-to-total efficiency is")
+n_ts=inv(1+(0.5*(phi^2)*(c/b)));
+disp("%",n_ts*1e2,"total-to-static efficiency is")
+end
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