GATE AE · 2021 · AE
Question 45: Engine Performance
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Question 45
AENAT2 marksNeeds review
A twin-spool turbofan engine is operated at sea level (Pₐ = 1 bar, Tₐ = 288 K). The engine has separate cold and hot nozzles. During static thrust test at sea level, the overall mass flow rate of air through the engine and the cold exhaust temperature are measured to be 100 kg/s and 288 K, respectively. The parameters for the engine are:
Fan pressure ratio = 1.6
Overall pressure ratio = 20
Bypass ratio = 3.0
Turbine entry temperature = 1800 K.
The specific heat at constant pressure (Cₚ) is 1.005 kJ/kg-K and the ratio of specific heats (γ) is 1.4 for air.
Assuming ideal fan and ideal expansion in the nozzle, the sea-level static thrust from the cold nozzle is ______________ kN (round off to two decimal places).
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2021AE
GATE AE 2021 · Paper 1
Aerospace Engineering · Original paper archive
- Section
- Aerospace Engineering
- Question type
- Numerical answer (NAT)
- Marks
- 2 marks
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