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/CH11/EX11.1/Ex11_1.sav | Bin 0 -> 45048 bytes
 2223/CH11/EX11.1/Ex11_1.sce |  56 ++++++++++++++++++++++++++++++++++++++++++++
 2 files changed, 56 insertions(+)
 create mode 100755 2223/CH11/EX11.1/Ex11_1.sav
 create mode 100755 2223/CH11/EX11.1/Ex11_1.sce

(limited to '2223/CH11/EX11.1')

diff --git a/2223/CH11/EX11.1/Ex11_1.sav b/2223/CH11/EX11.1/Ex11_1.sav
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diff --git a/2223/CH11/EX11.1/Ex11_1.sce b/2223/CH11/EX11.1/Ex11_1.sce
new file mode 100755
index 000000000..4fc5ae776
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+// scilab Code Exa 11.1 Calculation on an axial compressor stage 
+
+Rm=0.5; // Degree of reaction
+funcprot(0);
+T1=300;  // in Kelvin
+p1=1; //  Initial Pressure in bar
+gamma=1.4;
+N=18e3; // rotor Speed in RPM
+d=36/100; // Mean Blade ring diameter in m
+h=6/100; // blade height at entry in m
+cx=180; // Axial velocity in m/s
+alpha_1=25;  //  air angle at rotor and stator exit
+wdf=0.88; // work-done factor
+m=70; //  in kg/s
+pr=2; // Pressure Ratio
+n_st=0.85; // Stage Efficiency 
+n_m=0.967; // Mechanical Efficiency 
+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)
+R=287;
+u=%pi*d*N/60;
+n=(gamma-1)/gamma;
+
+// part(a) air angles at rotor and stator entry
+cy1=cx*tand(alpha_1);
+wy1=u-cy1;
+beta1=atand(wy1/cx);
+disp("degree",beta1,"air angles at rotor and stator entry are beta1=alpha2= ")
+phi=cx/u;
+
+// part(b) mass flow rate of the air
+ro1=(p1*1e5)/(R*T1);
+A1=%pi*d*h;
+m=ro1*cx*A1;
+disp("kg/s",m,"(b) mass flow rate of the air is")
+
+// part(c) Determining power required to drive the compressor
+beta2=alpha_1;
+w=wdf*u*cx*(tand(beta1)-tand(beta2))
+P=m*w/n_m;
+disp ("kW" ,P/1000,"(c)Power required to drive the compressor is")
+
+// part(d) Loading coefficient
+shi=w/(u^2);
+disp (shi,"(d)Loading coefficient is")
+
+// part(e) pressure ratio developed by the stage
+delTa=w/cp;
+delTs=n_st*delTa;
+pr=((1+(delTs/T1))^(1/n));
+disp(pr,"(e)pressure ratio developed by the stage is")
+
+// part(f) Mach number at the rotor entry
+w1=cx/(cosd(beta1));
+Mw1=w1/sqrt(gamma*R*T1);
+disp(Mw1,"(f)Mach number at the rotor entry is")
+
-- 
cgit