7. High pressure air at 1300 K flows into an aircraft gas turbine and undergoes a steady-state, steady-flow, adiabatic process to the turbine exit at 660 K. Calculate the work done per unit mass of air flowing through the turbine for the following scenarios: (a) Temperature dependent data are used: at T₁ =1300 K, at T2 = 660 K, h₁ = 1395.97 kJ/kg h₂ = 670.47 kJ/kg (b) CP,ave at the average temperature is used, 1.138 kJ/(kg·K). (c) Cp at 300K is used, 1.005 kJ/(kg·K).
7. High pressure air at 1300 K flows into an aircraft gas turbine and undergoes a steady-state, steady-flow, adiabatic process to the turbine exit at 660 K. Calculate the work done per unit mass of air flowing through the turbine for the following scenarios: (a) Temperature dependent data are used: at T₁ =1300 K, at T2 = 660 K, h₁ = 1395.97 kJ/kg h₂ = 670.47 kJ/kg (b) CP,ave at the average temperature is used, 1.138 kJ/(kg·K). (c) Cp at 300K is used, 1.005 kJ/(kg·K).
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Transcribed Image Text:7. High pressure air at 1300 K flows into an aircraft gas turbine and undergoes a steady-state,
steady-flow, adiabatic process to the turbine exit at 660 K. Calculate the work done per unit
mass of air flowing through the turbine for the following scenarios:
(a) Temperature dependent data are used:
at T₁ =1300 K,
at T2 = 660 K,
h₁ = 1395.97 kJ/kg
h₂ = 670.47 kJ/kg
(b) CP,ave at the average temperature is used, 1.138 kJ/(kg·K).
(c) Cp at 300K is used, 1.005 kJ/(kg·K).
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