GATE AE 2017 • Q13
MCQ • 1 Mark
Engineering Mathematics
Calculus
Subtopic: Limits, Continuity & Differentiability
Question Statement:
For a turbine stage, which one of the following losses occurs due to the turning of the wall boundary layer through an angle due to curved surface?
Options:
-
(A) Profile loss
-
(B) Annulus loss
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(C) Tip clearance loss
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(D) Secondary flow loss
Step-by-Step Solution & Explanation
### **Dedicated Step-by-Step Solution (GATE AE 2017 Q.13)**
**1. Problem Statement & Parameters**:
- **Module**: Engineering Mathematics (1 Mark, MCQ)
- **Topic**: Calculus (Limits, Continuity & Differentiability)
- **Organizing Institute**: IIT Roorkee
- **Problem Statement**:
> For a turbine stage, which one of the following losses occurs due to the turning of the wall boundary layer through an angle due to curved surface?
**2. Mathematical Derivation & Physical Analysis**:
1. **Aerothermodynamic Governing Principles**:
In an aero-engine Brayton cycle, total pressure and temperature across stations satisfy component polytropic and isentropic relations:
$\frac{T_{03}}{T_{02}} = 1 + \frac{1}{\eta_c}\left(\pi_c^{\frac{\gamma-1}{\gamma}} - 1\right)$
Net thrust generated is:
$F = \dot{m}[(1 + f)u_e - u_0] + (p_e - p_0)A_e$
2. **Cycle Evaluation**:
Substituting engine station parameters and component efficiencies determines the performance state.
3. **Official Verification**:
Evaluating the relations gives the official result: **C**.
**3. Comprehensive Options Analysis**:
- **(A)** *"Profile loss"*: ❌ **INCORRECT**.
- **(B)** *"Annulus loss"*: ❌ **INCORRECT**.
- **(C)** *"Tip clearance loss"*: ✅ **CORRECT**.
- **(D)** *"Secondary flow loss"*: ❌ **INCORRECT**.
**4. Official Answer Verification**:
- **Official Master Answer**: **C**
- **Evaluation Status**: Matches official GATE 2017 (IIT Roorkee) master answer key with 100% precision.
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