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Problem 1 (10 mark) A Turbojet engine at SLS conditions ($P_o$ = 101 kpa, $T_o$ = 288 K). If the Engine pressure ratio EPR = $P_{t5}/P_{t2}$ = 3.14 and the Specific thrust ST = 700 m/s. At design condition calculate the following: a. Compressor pressure ratio $\pi_c$, b. Turbine inlet temperature $T_{t4}$, c. The type of nozzle and its condition for maximum thrust. Assume the following: • The compressor and turbine polyropic efficiencies $e_c$ = $e_t$ = 0.9. $\begin{cases} 1, & M < 1 \\ (1 - 0.075(M_o - 1))^{1.35}, & 1 < M < 5 \end{cases}$ • Intake pressure loss ($\pi_d$ = $\pi_{dmax}$ $\eta_r$), $\eta_r$ = • Intake, Burner and nozzle pressure loss ($\pi_{dmax}$, $\pi_b$, $\pi_{AB}$, $\pi_n$ = 0.97), $\eta_b$ = 0.97 • Specific heat ratio for compressor and turbine $\gamma_c$ = 1.4, $\gamma_t$ = 1.33 $\rightarrow$ $C_p$ = $\frac{\gamma R}{\gamma - 1}$ • The fuel heating value $h_{pR}$ = 47 MJ/kgf, $\eta_m$(1 + f) = 1

          Problem 1 (10 mark) A Turbojet engine at SLS conditions ($P_o$ = 101 kpa, $T_o$ = 
288 K). If the Engine pressure ratio EPR = $P_{t5}/P_{t2}$ = 3.14 and the Specific thrust
ST = 700 m/s. At design condition calculate the following:
a. Compressor pressure ratio $\pi_c$,
b. Turbine inlet temperature $T_{t4}$,
c. The type of nozzle and its condition for maximum thrust.
Assume the following:
• The compressor and turbine polyropic efficiencies $e_c$ = $e_t$ = 0.9.
$\begin{cases} 1, & M < 1 \\ (1 - 0.075(M_o - 1))^{1.35}, & 1 < M < 5 \end{cases}$
• Intake pressure loss ($\pi_d$ = $\pi_{dmax}$ $\eta_r$), $\eta_r$ =
• Intake, Burner and nozzle pressure loss ($\pi_{dmax}$, $\pi_b$, $\pi_{AB}$, $\pi_n$ = 0.97), $\eta_b$ = 0.97
• Specific heat ratio for compressor and turbine $\gamma_c$ = 1.4, $\gamma_t$ = 1.33 $\rightarrow$ $C_p$ = $\frac{\gamma R}{\gamma - 1}$
• The fuel heating value $h_{pR}$ = 47 MJ/kgf, $\eta_m$(1 + f) = 1

Problem 1 (10 mark) A Turbojet engine at SLS conditions (Po = 101 kpa, To =
288 K). If the Engine pressure ratio EPR = Pt5/Pt2 = 3.14 and the Specific thrust
ST = 700 m/s. At design condition calculate the following:
a. Compressor pressure ratio ,
b. Turbine inlet temperature Tt4,
c. The type of nozzle and its condition for maximum thrust.
Assume the following:
• The compressor and turbine polyropic efficiencies ec = et = 0.9.
1, M < 1
(1 - 0.075(Mo - 1))^1.35, 1 < M < 5
• Intake pressure loss ( = πdmax ), =
• Intake, Burner and nozzle pressure loss (πdmax, , πAB, = 0.97), = 0.97
• Specific heat ratio for compressor and turbine = 1.4, = 1.33 → Cp = (γ R)/(γ - 1)
• The fuel heating value hpR = 47 MJ/kgf, (1 + f) = 1

Added by Alan W.

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