Turbomachinery Analysis Assistant for Propulsion Engineers
Analyze turbomachinery performance and design compressor/turbine stages for propulsion systems
What You Can Do
You can conduct preliminary compressor and turbine stage design using physics-based meanline methods, predict performance across operating envelopes, optimize blade geometry parameters, and troubleshoot thermodynamic matching issues. The skill leverages computational methods and industry design standards to enable rapid concept screening and design iteration from conceptual through 30% design maturity, supporting design reviews with thermodynamically justified decisions without requiring full CFD or FEA analysis.
Features
Calculates pressure ratio, efficiency, and temperature rise using loss correlations and design standards
Builds compressor and turbine performance maps across flight envelopes and operating points
Iterates solidity, loading, stagger angle, and hub-to-tip ratio to meet design targets
Analyzes operating envelope alignment and identifies off-design performance issues
Estimates surge margin, establishes surge lines, and identifies stability limits
Compares pressure ratio, efficiency, and weight trade-offs across parametric designs
Predicts profile, secondary, shock, and tip clearance losses using empirical correlations
Diagnoses matching conflicts and thermodynamic anomalies in propulsion systems
Example Output
Example 1: Compressor Stage Design
Stage 1 Preliminary Design Summary
- Inlet conditions: 0.3 MPa, 280 K
- Design pressure ratio: 1.45
- Corrected massflow: 42.5 kg/s
- Predicted polytropic efficiency: 86.2%
- Rotor blade count: 32 | Stator blade count: 40
- Hub-to-tip ratio: 0.72 | Blade solidity: 1.15
- Estimated surge margin: 18% (acceptable)
Example 2: Thermodynamic Cycle Analysis
Turbine Match Assessment
✓ Compressor exit: 2.8 MPa, 520 K
✓ Turbine inlet: 1650 K (within material limits)
✓ Turbine pressure ratio: 3.2 (matches compressor work requirement)
✓ Operating point inside surge-free region
⚠ Off-design at 85% spool speed: 12% surge margin (marginal)
→ Recommend compressor IGV adjustment or bleed valve
Example 3: Blade Parameter Trade Study
| Parameter | Option A | Option B | Option C |
|---|---|---|---|
| Solidity | 0.95 | 1.15 | 1.35 |
| Exit Loss Coeff | 0.042 | 0.035 | 0.032 |
| Stage Efficiency | 85.1% | 86.2% | 86.8% |
| Weight (rotor) | 2.8 kg | 3.1 kg | 3.4 kg |
| Recommendation | Too aggressive | BEST BALANCE | Overdesigned |
What's Included
- SKILL.md: Complete instruction file with turbomachinery analysis workflows and design standards
- Meanline Analysis Template: Spreadsheet framework for stage performance calculation with loss correlations
- Compressor Design Checklist: Step-by-step parameter selection and design validation workflow
- Turbine Matching Worksheet: Thermodynamic cycle model structure for compressor-turbine matching analysis
- Surge Prediction Framework: Methodologies for surge margin estimation and off-design stability assessment
- Design Trade-Space Evaluation Tool: Structured comparison format for parametric design iteration
Who It's For
- Propulsion systems engineers — Preliminary design and performance analysis of jet engines, turboshaft, and industrial turbomachinery
- Aerospace design teams — Rapid concept screening and design review support during feasibility and preliminary design phases
- Turbomachinery thermodynamicists — Cycle modeling, matching analysis, and off-design performance troubleshooting
- Junior/mid-level engineers — Training on turbomachinery fundamentals, design standards, and physics-based reasoning
- Technology readiness assessments — Thermodynamic justification and performance validation for design trade studies
Best For
- Preliminary compressor and turbine stage design (conceptual through 30% maturity)
- Meanline performance analysis and loss prediction across operating envelopes
- Blade geometry parameter optimization (solidity, loading, stagger, hub-to-tip ratio)
- Compressor-turbine matching and off-design performance diagnostics
- Surge margin estimation and operational limit establishment
- Design trade-space exploration and parametric sensitivity studies
- Thermodynamic cycle modeling and engine performance prediction
- Design review preparation with physics-based technical justification
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