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Diffstat (limited to '3685/CH19/EX19.16/Ex19_16.sce')
| -rw-r--r-- | 3685/CH19/EX19.16/Ex19_16.sce | 23 |
1 files changed, 23 insertions, 0 deletions
diff --git a/3685/CH19/EX19.16/Ex19_16.sce b/3685/CH19/EX19.16/Ex19_16.sce new file mode 100644 index 000000000..de2ed5ca3 --- /dev/null +++ b/3685/CH19/EX19.16/Ex19_16.sce @@ -0,0 +1,23 @@ +clc
+// Given that
+r1 = 2.5 // Pressure ratio of compressor for first stage
+r2 = 2.1 // Pressure ratio of compressor for second stage
+m = 5 // Mass flow rate of air in kg/s
+t1 = 10 // Inlet temperature in degree centigrade
+p1 = 1.013 // Inlet pressure in bar
+td = 50 // Temperature drop in intercooler in degree centigreade
+n_iso = .85 // Isentropic efficiency
+cp = 1.005 // Heat capacity of air in kJ/kgK
+x = 0.7 // Reduction in pressure ratio and intake volume
+gama = 1.4 // Ratio of heat capacities for air
+printf("\n Example 19.16\n")
+T1 = t1+273
+T2s = T1*((r1)^((gama-1)/gama))
+T2 = T1 + (T2s-T1)/n_iso
+T3 = T2 - td
+T4s = T3*((r2)^((gama-1)/gama))
+T4 = T3 + (T4s-T3)/n_iso
+P = m*cp*((T2-T1)+(T4-T3))
+printf("\n Actual temperature at the end of first stage = %f K,\n Actual temperature at the end of second stage = %f K,\n The total compressor power = %f kW",T2,T4,P)
+// The answers given in the book vary due to round off error
+
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