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6) Below is a schematic of the compressor of an aircraft gas turbine. A portion of the air that enters at state is extracted at state 2 and then expanded in a turbine to be used for cabin pressurization. The balance of the air leaves at state 3 known properties (stagnation pressure and temperature) and other data are given with the diagram. The power (hp) required to drive the compressor is Ps654 psia P2 18.0 psa P691 p 150 bmiseca compressor of an aircraft gas turbine. A portion of the air that enters at state 1 is extracted at state 2 and then expanded in a turbine to be used for cabin pressurization. The balance of the air leaves at state 3 known properties (stagnation pressure and temperature) and other data are given with the diagram. The power (hp) required to drive the compressor is P1 = 6.91 psia T1 = 460°R m1 = 150 Ibm/Sec P2 = 18 psia T2 = 630°R m2 = 3 Ibm/Sec P3= 65.4 psia T3= 900°R

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