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4.27 An advanced turboprop engine is flying at $M_0 = 0.75$ at 37 kft standard altitude. The component parameters are designated on the following engine drawing. $M_0 = 0.75$ $eta_{prop} = 0.75$ $eta_{gb} = 0.995$ Power turbine $e_{HPT} = 0.8$ $eta_{mHPT} = 0.99$ $pi_d = 0.95$ $pi_c = 35$ $e_c = 0.9$ $dot{m}_0 = 35 kg/s$ $T_{t4} = 1450 K$ $pi_b = 0.98$ $eta_b = 0.98$ $Q_R = 42,800 kJ/kg$ $eta_{mPT} = 0.99$ $eta_{tPT} = 0.90$ $eta_t = 0.90$ $eta_n = 0.98$ $p_9 = p_0$ Figure P4.27 Assuming an optimum power split $alpha_{opt}$ that leads to a maximum engine thrust, calculate: a. core thrust b. propeller thrust

          4.27 An advanced turboprop engine is flying at $M_0 = 0.75$ at 37 kft standard altitude. The component parameters are designated on the following engine drawing.

$M_0 = 0.75$
$eta_{prop} = 0.75$
$eta_{gb} = 0.995$
Power turbine
$e_{HPT} = 0.8$
$eta_{mHPT} = 0.99$
$pi_d = 0.95$
$pi_c = 35$
$e_c = 0.9$
$dot{m}_0 = 35 kg/s$
$T_{t4} = 1450 K$
$pi_b = 0.98$
$eta_b = 0.98$
$Q_R = 42,800 kJ/kg$
$eta_{mPT} = 0.99$
$eta_{tPT} = 0.90$
$eta_t = 0.90$
$eta_n = 0.98$
$p_9 = p_0$

Figure P4.27

Assuming an optimum power split $alpha_{opt}$ that leads to a maximum engine thrust, calculate:
a. core thrust
b. propeller thrust

4.27 An advanced turboprop engine is flying at M0 = 0.75 at 37 kft standard altitude. The component parameters are designated on the following engine drawing.

M0 = 0.75
etaprop = 0.75
etagb = 0.995
Power turbine
eHPT = 0.8
etamHPT = 0.99
pid = 0.95
pic = 35
ec = 0.9
dotm0 = 35 kg/s
Tt4 = 1450 K
pib = 0.98
etab = 0.98
QR = 42,800 kJ/kg
etamPT = 0.99
etatPT = 0.90
etat = 0.90
etan = 0.98
p9 = p0

Figure P4.27

Assuming an optimum power split alphaopt that leads to a maximum engine thrust, calculate:
a. core thrust
b. propeller thrust

Added by Francisca G.

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