A gas turbine engine is operating under the following conditions:
Stagnation temperature at turbine inlet 1350 K
Stagnation pressure at the turbine inlet 10 bar
Static temperature at turbine exit 800 K
Velocity at turbine exit 200 m/s
Total-to-total efficiency of turbine 0.96
γ (ratio of specific heats) 1.33
CP(specific heat at constant pressure) 1.147 kJ/kgK
The stagnation pressure (in bar) in the nozzle (considering isentropic nozzle) is equal to _______.
AE 9/11
AE (GATE 2014)
- AE
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2014 Q.46)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Air-Breathing & Rocket Propulsion** under *Propulsion* (2 Marks, NAT).
**2. Analytical Calculation**:
- Substituting aerodynamic parameters into governing Air-Breathing & Rocket Propulsion equation.
**3. Final Answer**:
Acceptable official numerical value is **0.0**.
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