Boundary Layer Transition Prediction on Planar Turbine Cascade Using Temperature-Sensitive Paint and Numerical Simulation
Abstract
:1. Introduction
2. Transitional Measurement Experiment on TSP
2.1. TSP Principle
2.2. Wind-Tunnel Test Device
2.3. Experimental Data Processing and Result Analysis
3. Numerical Prediction of Transition
3.1. Numerical Method and Validation
3.2. Numerical Results
3.2.1. Influence of Ma2
3.2.2. Influence of Attack Angle
3.2.3. Shock-Wave Influence
4. Conclusions
- (1)
- TSP transitional measurement results show that the transitional location was about 0.63 Lax at Ma2 = 0.4, Re1 = 3.1 × 105, and transition occurred at approximately 0.42 Lax at Ma2 = 1.03 Re1 = 8.6 × 105. As Re1 decreased, the transitional location moved backward, about 0.47 Lax at Ma2 = 1.03, Re1 = 3.1 × 105. The transitional location shifted backward with the increase in Ma2, occurring at about 0.49 Lax at Ma2 = 1.2, Re1 = 8.6 × 105.
- (2)
- The numerical calculations of the planar cascade with Ma2 < 1 (Ma2 = 0.56, 0.78, 0.98) and α (α = −10°, 0°, 10°) were completed. The boundary layer transition of the planar cascade moved forward with the increase in Ma2 and α.
- (3)
- Numerical calculations of the planar cascade with Ma2 > 1 (Ma2 = 1.1, 1.2, 1.4) were carried out. The transitional location of the boundary layer moved backward with the increase in Ma2, which was consistent with the experimental results. In addition, the generation of shock waves formed a large adverse pressure gradient that led to the onset of transition.
Author Contributions
Funding
Data Availability Statement
Acknowledgments
Conflicts of Interest
References
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Items | Value |
---|---|
Pressure sensitivity | 0.0%/kPa |
Pressure range | 1 kPa~10 MPa |
Temperature sensitivity | 1.4%/°C |
Temperature range | 10 °C to 80 °C |
Response time | 750 ms |
Excitation wavelength | 400 to 550 nm (peak, 470 nm) |
Emission wavelength | 600 to 750 nm (peak, 620 nm) |
Photodegradation rate | 1%/h |
Expiration date | 12 months |
Parameters | Value |
---|---|
Inlet flow angle (β) | 30° |
Blade angle relative to cascade axis (θ) | 33.3° |
Chord length (c) | 95 mm |
Ratio of chord length to grating pitch (σ) | 1.40845 |
Aspect ratio (h/c) | 2.0 |
Number of blades in the cascade (N) | 7 |
Test | pt1 | ps1 | Ma2 | Re1 | TIin |
---|---|---|---|---|---|
1 | 172 kPa | 86.7 kPa | 1.03 | 8.6 × 105 | 0.3% |
2 | 170 kPa | 72.1 kPa | 1.2 | 8.6 × 105 | 0.3% |
3 | 59.1 kPa | 53.1 kPa | 0.4 | 3.1 × 105 | 0.3% |
4 | 103 kPa | 51.1 kPa | 1.03 | 5.1 × 105 | 0.3% |
Item | Setting |
---|---|
Inlet boundary condition | Total pressure |
Inlet total temperature | 300 K |
Inlet turbulence intensity | 1% |
Outlet boundary condition | Static pressure |
Blade wall condition | No-slip wall |
Upper and lower surfaces | No-slip wall |
Advection scheme | High-resolution |
Turbulence numeric | High-resolution |
Residual convergence criterion | 1 × 10−5 |
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Ke, W.; Wang, H.; Zhang, W.; Huang, K.; Zhu, B. Boundary Layer Transition Prediction on Planar Turbine Cascade Using Temperature-Sensitive Paint and Numerical Simulation. Processes 2022, 10, 2078. https://doi.org/10.3390/pr10102078
Ke W, Wang H, Zhang W, Huang K, Zhu B. Boundary Layer Transition Prediction on Planar Turbine Cascade Using Temperature-Sensitive Paint and Numerical Simulation. Processes. 2022; 10(10):2078. https://doi.org/10.3390/pr10102078
Chicago/Turabian StyleKe, Wenliang, Hongbiao Wang, Wenwu Zhang, Kang Huang, and Baoshan Zhu. 2022. "Boundary Layer Transition Prediction on Planar Turbine Cascade Using Temperature-Sensitive Paint and Numerical Simulation" Processes 10, no. 10: 2078. https://doi.org/10.3390/pr10102078