- include a diffuser at the beginning, and assume that the aircraft is flying at an altitude of 10000 meters and a speed of 200 m/s. Let state a be the atmospheric conditions, and state 1 be the conditions after the diffuser. Instead of a power turbine, include a nozzle, which returns the air to atmospheric pressure isentropically.

Determine the thrust through the equation T=m?(Ve?Vi), where Ve is the velocity exiting the nozzle, and Vi is the inlet velocity.

Question 6.5: In Example 6.4 we did an ideal thermodynamic analysis of the General Electric T700 helicopter gas turbine engine, shown in the following schematic diagram: Air Intake Annular Combustor Exhaust Axi-Centrifugal Compressor Gas Generator Turbine Power Turbine Air Intake Compressor Pressure ratio TI = 16'C P2/P1 = 15 1T47 PI = 101 kPa P47 Gas Gen Power WTF ? Tubine Turbine m = 4.6 ke/'s WTF ? Combustion chamber exhaust T2 7 T3 = 1000'C P3 = P2 P5 = P1 T5