The pressure ratio across a gas turbine for air- specific heat at constant pressure- cp-1040 J-kgK and ratio of specifc heats - -1-4 is 10- If the inlet temeprature to the turbine is 1200 K and te isentropic efficiency is 0-9- the gas temperature at turbine exist is

Given data: c_p=1040 J/kgK; γ =1.4; nbsp; r_p=10; T_3=1200 K; η_γ=0.9 T_3T_4s=(r_p)^γ 1γ 1200T_4s=(10)^(1.4 1)/1.4 or T_4s=621.53 K η_T=T_3 T_4T_3 T_4s 0. ...

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Standard XII

Chemistry

Heat Capacity at Constant Pressure

The pressure ...

Question

The pressure ratio across a gas turbine (for air, specific heat at constant pressure, $c_{p} = 1040 J / k g K$ and ratio of specifc heats $γ = 1.4$ is $10$ . If the inlet temeprature to the turbine is $1200 K$ and te isentropic efficiency is $0.9$ , the gas temperature at turbine exist is
679.4

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Solution

The correct option is A 679.4
Given data: $c_{p} = 1040 J / k g K; γ = 1.4; r_{p} = 10;$
$T_{3} = 1200 K; η_{γ} = 0.9$
$\frac{T_{3}}{T_{4 s}} = (r_{p})^{\frac{γ - 1}{γ}}$

$\frac{1200}{T_{4 s}} = (10)^{(1.4 - 1) / 1.4}$
or $T_{4 s} = 621.53 K$
$η_{T} = \frac{T_{3} - T_{4}}{T_{3} - T_{4 s}}$
$0.9 = \frac{1200 - T_{4}}{1200 - 621.53}$
or $T_{4} = 679.4 K$

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The pressure ratio across a gas turbine (for air, specific heat at constant pressure, cp=1040J/kgK and ratio of specifc heats γ=1.4 is 10. If the inlet temeprature to the turbine is 1200K and te isentropic efficiency is 0.9, the gas temperature at turbine exist is679.4

The correct option is A 679.4Given data: cp=1040J/kgK;γ=1.4;rp=10; T3=1200K;ηγ=0.9 T3T4s=(rp)γ−1γ 1200T4s=(10)(1.4−1)/1.4 or T4s=621.53K ηT=T3−T4T3−T4s 0.9=1200−T41200−621.53 or T4=679.4K

The pressure ratio across a gas turbine (for air, specific heat at constant pressure, $c_{p} = 1040 J / k g K$ and ratio of specifc heats $γ = 1.4$ is $10$ . If the inlet temeprature to the turbine is $1200 K$ and te isentropic efficiency is $0.9$ , the gas temperature at turbine exist is
679.4