GATE AE · 2024 · AE
Question 19: Basics
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Question 19
AEMCQ1 markNeeds review
In an airbreathing gas turbine engine, the combustor inlet temperature is 600 K. The heating value of the fuel is 43.4 × 10⁶ J/kg. Assume Cₚ to be 1100 J/kg K for air and burned gases, and fuel-air ratio f<< 1.0. Neglect kinetic energy at the inlet and exit of the combustor and assume 100% burner efficiency. What is the fuel-air ratio required to achieve 1300 K temperature at the combustor exit?
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2024AE
GATE AE 2024 · Paper 1
Aerospace Engineering · Original paper archive
- Section
- Aerospace Engineering
- Question type
- Multiple choice (MCQ)
- Marks
- 1 mark
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