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?
Options:
(A) 0.0177
(B) 0.0215
(C) 0.0127
(D) 0.0277
Official Answer Key:
A
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2024 Q.19)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Structural Mechanics** under *Aerospace Structures* (1 Mark, MCQ).
**2. Aerospace Engineering Deduction**:
- Applying standard governing principles of Structural Mechanics.
- Option **(A)** matches the analytical derivation and official criteria.
**3. Final Answer**:
Correct Option is **(A)**.
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