research on small turbojet engines at the royal military academy of ...
research on small turbojet engines at the royal military academy of ... research on small turbojet engines at the royal military academy of ...
Stagnation and Static Inlet Temperature with and without Precooling 285 280 275 mass flow of nitrogen = 0,0105 kg/s Tt1 T1 270 Tt1' T ( K ) 265 T1' 260 255 250 245 45000 50000 55000 60000 65000 70000 75000 80000 85000 RPM ( 1/min ) fig. 11 Influence of LN2 Injection on Air Composition 8 increase mass N2 / unit mass of air ( % ) 7 6 5 4 3 2 1 0 45000 50000 55000 60000 65000 70000 75000 80000 85000 RPM ( 1/min ) fig. 12
TN = f(EGT,Tt1) 100 90 Ta = 280K with precooling 80 70 without precooling 60 TN ( N ) 50 40 30 20 10 0 600 620 640 660 680 700 720 740 760 780 EGT ( K ) fig.13 TN = f(TIT,Tt1) 100 90 80 70 Ta = 280 K with precooling without precooling 60 TN ( N ) 50 40 30 20 10 0 700 720 740 760 780 800 820 840 860 880 900 920 TIT ( K ) fig. 14
- Page 1 and 2: RESEARCH ON SMALL TURBOJET ENGINES
- Page 3 and 4: perturbed air in front of the inlet
- Page 5 and 6: This equation is very useful, since
- Page 7 and 8: Static and Stagnation Inlet Pressur
- Page 9: use the same engine in a larger UAV
- Page 13 and 14: TSFCN2 = f(EGT,TIT,Tt1) 14 13 12 TS
Stagn<strong>at</strong>i<strong>on</strong> and St<strong>at</strong>ic Inlet Temper<strong>at</strong>ure with and without Precooling<br />
285<br />
280<br />
275<br />
mass flow <strong>of</strong> nitrogen = 0,0105 kg/s<br />
Tt1<br />
T1<br />
270<br />
Tt1'<br />
T ( K )<br />
265<br />
T1'<br />
260<br />
255<br />
250<br />
245<br />
45000 50000 55000 60000 65000 70000 75000 80000 85000<br />
RPM ( 1/min )<br />
fig. 11<br />
Influence <strong>of</strong> LN2 Injecti<strong>on</strong> <strong>on</strong> Air Compositi<strong>on</strong><br />
8<br />
increase mass N2 / unit mass <strong>of</strong> air ( % )<br />
7<br />
6<br />
5<br />
4<br />
3<br />
2<br />
1<br />
0<br />
45000 50000 55000 60000 65000 70000 75000 80000 85000<br />
RPM ( 1/min )<br />
fig. 12
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