Question

8.8 The absolute flow angle at the inlet of a stator blade in a compressor is $\alpha_2 = 45^\circ$, as shown. The absolute total pres- sure and temperature in station 2 are $p_{t2} = 150 \text{ kPa}$ and $T_2$ $= 300 \text{ K}$, respectively. The total pressure loss coefficient for this section of the stator blade is $\omega_s = 0.02$. Assuming the axial velocity remains constant and gas properties are $\gamma = 1.4$ and $c_p = 1.004 \text{ kJ/kg} \cdot \text{K}$, calculate (a) entrance Mach number $M_2$ (b) exit total pressure $p_{t3}$ (c) exit Mach number $M_3$ (d) static pressure rise, $\Delta p = p_3 - p_2$

          8.8
The absolute flow angle at the inlet of a stator blade in
a compressor is $\alpha_2 = 45^\circ$, as shown. The absolute total pres-
sure and temperature in station 2 are $p_{t2} = 150 \text{ kPa}$ and $T_2$
$= 300 \text{ K}$, respectively. The total pressure loss coefficient for
this section of the stator blade is $\omega_s = 0.02$. Assuming the
axial velocity remains constant and gas properties are $\gamma = 1.4$
and $c_p = 1.004 \text{ kJ/kg} \cdot \text{K}$, calculate
(a) entrance Mach number $M_2$
(b) exit total pressure $p_{t3}$
(c) exit Mach number $M_3$
(d) static pressure rise, $\Delta p = p_3 - p_2$

8.8
The absolute flow angle at the inlet of a stator blade in
a compressor is α2 = 45^∘, as shown. The absolute total pres-
sure and temperature in station 2 are pt2 = 150 kPa and T2
= 300 K, respectively. The total pressure loss coefficient for
this section of the stator blade is = 0.02. Assuming the
axial velocity remains constant and gas properties are γ = 1.4
and cp = 1.004 kJ/kg·K, calculate
(a) entrance Mach number M2
(b) exit total pressure pt3
(c) exit Mach number M3
(d) static pressure rise, Δ p = p3 - p2

Added by Joshua J.

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