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/EX18.12/Ex18_12.sce | 35 +++++++++++++++++++++++++++++++++++
 1 file changed, 35 insertions(+)
 create mode 100755 2223/CH18/EX18.12/Ex18_12.sce

(limited to '2223/CH18/EX18.12/Ex18_12.sce')

diff --git a/2223/CH18/EX18.12/Ex18_12.sce b/2223/CH18/EX18.12/Ex18_12.sce
new file mode 100755
index 000000000..8645e5951
--- /dev/null
+++ b/2223/CH18/EX18.12/Ex18_12.sce
@@ -0,0 +1,35 @@
+// scilab Code Exa 18.12 turbo prop Gas Turbine Engine
+
+Ti=268.65; // in Kelvin
+n_C=0.8; // Compressor Efficiency
+c1=85; // entry velocity in m/s
+m=50; // mass flow rate of air in kg/s
+R=287;
+gamma=1.4; // Specific Heat Ratio
+cp=1.005; // Specific Heat at Constant Pressure in kJ/(kgK)
+u=500/3.6; // speed of a turbo prop aircraft in m/s
+delT=225; // temperature rise through the compressor(T02-T01) in K
+pi=.701; // Initial Pressure in bar
+n_D=0.88; // inlet diffuser efficiency
+a_i=sqrt(gamma*R*Ti);
+Mi=u/a_i;
+Toi_i=1/0.965; // (Toi/Ti)from isentropic flow gas tables at Mi and gamma values
+T01=Ti*Toi_i;
+T1=T01-(0.5*(c1^2)/(cp*1e3));
+
+//part(a)
+T1s_i=1+n_D*((T1/Ti)-1); // (T1s/Ti)isentropic temperature ratio through the diffuser
+p1_i=T1s_i^(gamma/(gamma-1)); // (p1s/pi)isentropic pressure ratio
+p1=p1_i*pi;
+delp_D=p1-pi;
+disp("bar",delp_D,"(a)isentropic pressure rise through the diffuser is")
+
+// part(b) compressor pressure ratio
+T02s=T01+(delT*n_C);
+r_oc=(T02s/T01)^(gamma/(gamma-1)); //compressor pressure ratio(p02/p01)
+disp(r_oc,"(b)compressor pressure ratio is")
+
+// part(c)
+P=m*cp*delT;
+disp("MW",P*1e-3,"(c)power required to drive the compressor is")
+
-- 
cgit