A single-stage gas turbine operates with an axial absolute flow at the entry and exit from the stage.
The absolute flow angle at the nozzle exit is 70 o. The turbine stage generates a specific work of
228 kJ/kg when operating with a mean blade speed of 440 m/s. The absolute velocity at the rotor
entry is
(A) 275.7 m/s (B) 551.5 m/s (C) 1103.0 m/s (D) 1654.5 m/s
Official Answer Key:
0.0
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2016 Q.27)**
**1. Governing Concept & Syllabus Domain**:
This question pertains to **Air-Breathing & Rocket Propulsion** under *Propulsion* (1 Mark, 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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