initial commit / add all books

1 files changed, 35 insertions, 0 deletions

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")

+