From b1f5c3f8d6671b4331cef1dcebdf63b7a43a3a2b Mon Sep 17 00:00:00 2001
From: priyanka
Date: Wed, 24 Jun 2015 15:03:17 +0530
Subject: initial commit / add all books

---
 2223/CH18/EX18.29/Ex18_29.sce | 61 +++++++++++++++++++++++++++++++++++++++++++
 1 file changed, 61 insertions(+)
 create mode 100755 2223/CH18/EX18.29/Ex18_29.sce

(limited to '2223/CH18/EX18.29/Ex18_29.sce')

diff --git a/2223/CH18/EX18.29/Ex18_29.sce b/2223/CH18/EX18.29/Ex18_29.sce
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+// scilab Code Exa 18.29 Centrifugal compressor with vaned diffuser 
+T01=310;  // in Kelvin
+p01=1.103; //  Initial Pressure in bar
+dh=0.10; // hub diameter in m
+d2=0.55; // impeller diameter in m
+c1=100; // Velocity of air at the entry of inducer
+c3=c1; // Velocity of air at diffuser exit
+shi=1.035; // power input factor
+mu=0.9; // slip factor
+m=7.5; //  in kg/s
+gamma=1.4;
+N=15e3; // rotor Speed in RPM
+disp("(a)for radially tipped blades")
+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)
+R=287;
+n_tt=0.81; // total to total efficiency
+T1=T01-((c1^2)/(2*cp));
+p1=p01*((T1/T01)^(gamma/(gamma-1)));
+ro1=(p1*1e5)/(R*T1);
+A1=m/(ro1*c1);
+dt=sqrt((A1*4/(%pi))+(dh^2));
+disp("cm",dt*1e2,"(i)tip diameter of the inducer at entry is")
+d1=0.5*(dt+dh); // Mean Blade ring diameter
+u1=%pi*d1*N/60;
+w1=sqrt((u1^2)+(c1^2));
+a1=sqrt(gamma*R*T1);
+M1_rel=w1/a1;
+disp(M1_rel,"(ii)the Relative Mach number at inducer blade entry Mw1=")
+u2=%pi*d2*N/60;
+w_st=shi*mu*(u2^2);
+T02=T01+(w_st/cp);
+T02s=T01+(n_tt*(T02-T01));
+pr_0=(T02s/T01)^(gamma/(gamma-1));
+disp(pr_0,"(iii)stagnation pressure ratio developed is")
+P=m*cp*(T02-T01);
+disp("kW",P*1e-3,"(iv)the power required is")
+disp("(b)for vaned diffuser")
+c_theta2=mu*u2; // velocity of whirl(swirl component) at the impeller exit
+// vaneless space between the impeller exit and the vaned diffuser entry=0.1*impeller radius
+//r2s=r2*1.1;
+// width of the casing after the impeller exit=1.4*impeller passage width
+c_theta2s=c_theta2/(1.1*1.4);
+cr2=c1;
+cr2s=cr2/(1.1*1.4);
+c2s=sqrt((cr2s^2)+(c_theta2s^2));
+alpha2s=atand(cr2s/c_theta2s);
+disp("degree",alpha2s,"(i)the direction of flow at the diffuser entry is alpha2s=")
+T2s=T02-((c2s^2)/(2*cp));
+a2s=sqrt(gamma*R*T2s);
+M2s=c2s/a2s;
+disp(M2s,"(ii)the Mach number at the diffuser entry is")
+Ar=c2s/c3;
+d3_2s=1.16; // d3/d2s from last trial given in the book
+alpha3=acosd(cosd(alpha2s)/d3_2s);
+Ar_v=d3_2s*sind(alpha3)/(sind(alpha2s));
+disp(Ar_v,"(iii)Area ratio of the vaned diffuser is")
+T03=T02;
+T3=T03-((c3^2)/(2*cp));
+pr3_1=(((T3*T01)/(T1*T03))^(gamma/(gamma-1)))*pr_0;
+disp(pr3_1,"(iv)the static pressure ratio of the compressor is")
+disp("comment: Calculations in the book are wrong in the beginning itself for p1. so the values slightly differs here only for part(a)")
-- 
cgit