Question

W2 U = 150 m/s W1 C1 Z Ol1 2. (40 pts) A very light business jet is in flight at Mach 0.85 at a cruise altitude of 13.5 km (static temperature 216.7 K and static pressure 15.26 kPa). It is powered by two turbofans, each with two independent spools and a thrust rating of 1800 lbf. The low-pressure spool consists of a single-stage fan and a two-stage axial compressor, all powered by a two-stage axial turbine. The high-pressure spool consists of a single-stage centrifugal compressor with straight radial blades, powered by a single-stage impulse turbine with purely axial outflow. Assume standard air (29 g/mol and y = 7/5) throughout, and that fuel mass flow and bleed flow rates are negligible. (a) (10 pts) If the stagnation pressure at the compressor inlet is 23.73 kPa, calculate the diffuser efficiency.

Answer 1

question bata from the given al= 2 / 2 glalu mach numbeo Mi = 0.85 static pressude por= 15.26 kpa stagnation po Pt2 = 23.75kpa. (2) DIFPUSER Diffused efficiency. no P12) 8-1 r (Tito - and we have Tto To 1+1=')m? > (770-1) = (.) MA c 8-1 i. Mpa ဒီလို (9) 오 Mi 2

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