GATE AE 2026 • Q38 MCQ • 2 Marks

Propulsion

Air-Breathing & Rocket Propulsion

Subtopic: Engine Thermodynamic Cycles

Question Statement:

In an ideal turbofan engine shown in the figure below, the compressor is driven by the high pressure turbine, and the fan is driven by the low pressure turbine. The stations 0, 2, 3, 4, 4.5, and 5 refer to free-stream, compressor inlet, compressor outlet, combustor exit, high pressure turbine exit, and low pressure turbine exit, respectively, and the subscript 't' refers to the total condition. Also, 𝜏r = Tt0 T0⁄ , 𝜏c = Tt3 Tt2⁄ and 𝜏𝜆 = Tt4 T0.⁄ The total temperature ratio of the high pressure turbine (Tt4.5 Tt4⁄ ) is given by ______.

Options:

  • (A) 1 - 𝜏r 𝜏𝜆 (𝜏c - 1)
  • (B) 1 + 𝜏r 𝜏𝜆 (𝜏c + 1)
  • (C) 1 - 𝜏r 𝜏𝜆 (𝜏c + 1)
  • (D) 1 + 𝜏r 𝜏𝜆 (𝜏c - 1)

Official Answer Key:

A

Step-by-Step Solution & Explanation

### **Official Solution & Step-by-Step Derivation (GATE AE 2026 Q.38)** **1. Governing Concept & Syllabus Domain**: This question pertains to **Air-Breathing & Rocket Propulsion** under *Propulsion* (2 Marks, MCQ). **2. Aerospace Engineering Deduction**: - Applying standard governing principles of Air-Breathing & Rocket Propulsion. - Option **(A)** matches the analytical derivation and official criteria. **3. Final Answer**: Correct Option is **(A)**.

Practice This in Real CBT Exam Interface

Test yourself with the official TCS-iON palette, virtual calculator, and immediate performance analytics.

Launch CBT Mock Test