Large-Eddy Simulation of Shaped Hole Film Cooling with the Influence of Cross Flow
-
Wang Qingsong
and
Xin Yuan
Abstract
In the highly-loaded turbine blade passage, cross flow is driven by the lateral gradient. It strongly influences the cooling performances in the endwall region. In this research, the effect of cross flow on the shaped film cooling hole is studied by Large Eddy Simulation (LES); modal analysis is conducted with an incremental POD (iPOD) approach, which makes the analysis of the large data sets from LES feasible. It is shown that the symmetry of the counter rotating vortex pair (CRVP) is destroyed. The large-scale vortex induced by end-wall cross flow plays an important role in both shape and convection of hairpin vortices and horseshoe vortices, which influences the coolant distribution. This study suggests that the effects of cross flow should be considered for the design of end-wall film cooling. It also indicates the high efficiency of the iPOD approach, which can be used to analyze large amounts of high-dimensional data.
Funding statement: This work is supported by the Open fund from State Key Laboratory of Aerodynamics and the National Natural Science Foundation of China (Project Grant No. 51876098). This work is also supported by the National Science and Technology Major Project (2017-III-0009-0035).
Nomenclature
- aw
-
adiabatic wall
- c
-
Coolant
- ∞
-
Mainstream
- M
-
blowing ratio
- PSD
-
power spectral density
- TKE
-
nondimensional turbulent kinetic energy
- SVD
-
singular value decomposition
- Re
-
Reynolds number
- POD
-
Proper Orthogonal Decomposition
- CRVP
-
counter-rotating vortex pair
-
-
y-direction free-stream velocity in cartesian coordinate system
- r
-
cylindrical coordinate (Radial)
- θ
-
cylindrical coordinate (Circumferential)
-
-
temperature variance
References
1. Bogard DG, Thole KA. Gas turbine film cooling. J Propul Power. 2006;22.2:249–70. ISSN: 0748-4658. DOI:10.2514/1.18034.Search in Google Scholar
2. Zhang H, Li Y, Chen Z, Su X, Yuan X. Multi-fidelity model based optimization of shaped film cooling hole and experimental validation. Int J Heat Mass Transf. 2019;132:118–29. ISSN: 0017-9310. DOI: 10.1016/j.ijheatmasstransfer.2018.11.156. URL:. http://www.sciencedirect.com/science/article/pii/S0017931018341024.Search in Google Scholar
3. Li G, Chen Y, Kou Z, Zhang W, Zhang G. Mechanism of film cooling with one inlet and double outlet hole injection at various turbulence intensities. Int J Turbo & Jet-Engines. 2018;35.1:1–9.10.1515/tjj-2016-0024Search in Google Scholar
4. Lutum E, von Wolfersdorf J, Semmler K, Dittmar J, Weigand B. An experimental investigation of film cooling on a convex surface subjected to favourable pressure gradient flow”. Int J Heat Mass Transf. 2001;44.5:939–51. ISSN: 0017-9310. DOI: 10.1016/S0017-9310(00)00158-7. URL: http://www.sciencedirect.com/science/article/pii/S0017931000001587.Search in Google Scholar
5. Li Y, Zhang Y, Su X, Yuan X. Experimental and numerical investigations of shaped hole film cooling with the influence of endwall cross flow. Int J Heat Mass Transf. 2018;120:42–55.10.1016/j.ijheatmasstransfer.2017.11.150Search in Google Scholar
6. Zhou Y, Zhang Y, Su X, Yuan X. Effect of inlet rotating swirl on endwall film cooling for two representative hole arrangements. Chin J Aeronaut. 2018;31.5:1095–108. ISSN: 1000-9361. DOI: 10.1016/j.cja.2018.03.008. URL: https://www.sciencedirect.com/science/article/pii/S1000936118301006.Search in Google Scholar
7. Zhang Y, Li Y, Bian X, Yuan X. Effects of inlet swirl on pressure side film cooling of neighboring vane surface. J Therm Sci Eng Appl. 2019;11.6. ISSN: 1948-5085. DOI: 10.1115/1.4043260. URL: https://doi.org/10.1115/1.4043260.Search in Google Scholar
8. McClintic JW, Wilkes EK, Bogard DG, Dees JE, Laskowski GM, Briggs R. Near-hole thermal field measurements for round compound angle film cooling holes fed by cross-flow. ASME Turbo Expo: Power for Land, Sea, and Air. 2015;5B:Heat Transfer: V05BT12A050.10.1115/GT2015-43949Search in Google Scholar
9. Zhai Y, Liu C, He Y, Zhou Z. Investigation on the film cooling performance of diffuser shaped holes with different inclination angles. Int J Turbo & Jet Engines. 2016;34.2:123–39.10.1515/tjj-2016-0026Search in Google Scholar
10. Zhong L, Zhou C, Chen S. Large-Eddy simulations of inclined jets in crossflow with different holes. J Propul Power. 2018;34.5. ISSN: 0748-4658. DOI:10.2514/1.B36594.Search in Google Scholar
11. Haydt S, Lynch S, Lewis S. The effect of area ratio change via increased hole length for shaped film cooling holes with constant expansion angles. J Turbomach. 2018;140.5. ISSN: 0889-504X. DOI:10.1115/1.4038871.Search in Google Scholar
12. Bidan G, Vézier C, Nikitopoulos DE. Study of unforced and modulated film-cooling jets using proper orthogonal decomposition—Part I: unforced jets. J Turbomach. 2012;135.2. ISSN: 0889-504X. DOI:10.1115/1.4006599.Search in Google Scholar
13. Sarkar, Babu H. Large Eddy simulation on the interactions of wake and film-cooling near a leading edge. J Turbomach. 2014;137.1. ISSN: 0889-504X. DOI:10.1115/1.4028219.Search in Google Scholar
14. Thompson L, et al. Planar laser induced fluorescence experiments and modeling study of jets in crossflow. J Fluids Eng. 2016;138.8:081201.10.1115/1.4032581Search in Google Scholar
15. Meng T, Zhu H, Liu C, Wei J. Investigation on the accuracy of superposition predictions of film cooling effectiveness. Int J Turbo & Jet-Engines. 2018;35.2:181–92.10.1515/tjj-2017-0029Search in Google Scholar
16. Zhou Z-Y, Li H-W, Wang H-C, Zhao G-Q, Han F, Wu M. Rotating film cooling performance of the hole near the leading edge on the suction side of theturbine blade. ASME Int Mech Eng Congr Exposition. 2019;8B: Heat Transfer and Thermal Engineering. DOI: 10.1115/IMECE2018-86929. eprint: https://asmedigitalcollection.asme.org/IMECE/proceedings-pdf/IMECE2018/52125/V08BT10A052/2503593/v08bt10a052-imece2018-86929.pdf. URL: https://doi.org/10.1115/IMECE2018-86929.Search in Google Scholar
17. Li Y, Zhang Y, Su X, Yuan X. Influence of mainstream cross flow on film cooling performance and jet flow field. ASME Turbo Expo: Power for Land, Sea, and Air. 2017; 5A: Heat Transfer: V05AT12A013. DOI:10.1115/GT2017-64234.Search in Google Scholar
18. Stratton ZT, Shih TI-P. Identifying weaknesses in eddy-viscosity models for predicting film cooling via Large-Eddy simulations”. J Propul Power. 2019:1–12. DOI:10.2514/1.B37314. URL: https://arc.aiaa.org/doi/10.2514/1.B37314.Search in Google Scholar
19. Rozati A, Tafti DK. Effect of coolant–mainstream blowing ratio on leading edge film cooling flow and heat transfer – LES investigation”. Int J Heat Fluid Flow. 2008;29.4:857–73. ISSN: 0142-727X. DOI: https://doi.org/10.1016/j.ijheatfluidflow.2008.02.007. URL: http://www.sciencedirect.com/science/article/pii/S0142727X08000234.Search in Google Scholar
20. Dong P, Amano RS. High-pressure gas turbine vane turbulent flows and heat transfer predicted by RANS/LES/DES. ASME Turbo Expo: Power for Land, Sea, and Air. 2017;5B. Heat Transfer: V05BT22A001. DOI:10.1115/GT2017-63032.Search in Google Scholar
21. Li W, Shi W, Li X, Ren J, Jiang H. Large Eddy simulation of axial and compound angle holes with varying hole length-to-diameter ratio. ASME Turbo Expo: Power for Land, Sea, and Air. 2017; 5A: Heat Transfer: V05AT12A004. DOI:10.1115/GT2017-63308.Search in Google Scholar
22. Roy S, Kapadia S, Heidmann JD. Film cooling analysis using DES turbulence model. Parts A and B Turbo Expo: Power for Land, Sea, and Air. 2003;6:1113–22. Turbo Expo 2003. DOI: 10.1115/GT2003-38140. URL: https://doi.org/10.1115/GT2003-38140.Search in Google Scholar
23. Martin P, Schulz A, Bauer HJ, Whitney CF. Detached eddy simulation of film cooling performance on the trailing edge cutback of gas turbine airfoils. J Turbomach. 2005;128.2:292–9. ISSN: 0889-504X. DOI: 10.1115/1.2137739. eprint: https://asmedigitalcollection.asme.org/turbomachinery/article-pdf/128/2/292/4819952/292\_1.pdf. URL: https://doi.org/10.1115/1.2137739.Search in Google Scholar
24. Takahashi T, Funazaki K, Salleh HB, Sakai E, Watanabe K. Assessment of URANS and DES for prediction of leading edge film cooling. J Turbomach. July 2011;134.3. ISSN: 0889-504X. DOI: 10.1115/1.4003054. eprint: https://asmedigitalcollection.asme.org/turbomachinery/article-pdf/134/3/031008/4852046/031008\_1.pdf. URL: https://doi.org/10.1115/1.4003054.Search in Google Scholar
25. Foroutan H, Yavuzkurt S. Numerical simulations of the near-field region of film cooling jets under high free stream turbulence: application of RANS and hybrid URANS/Large Eddy simulation models. J Heat Transfer. 2015;137.1. ISSN: 0022-1481. DOI:10.1115/1.4028646.Search in Google Scholar
26. Oliver TA, Anderson JB, Bogard DG, M.oser RD, Laskowski G. Implicit LES for shaped-hole film cooling flow. ASME Turbo Expo: Power for Land, Sea, and Air. 2017; 5A: Heat Transfer: V05AT12A005. DOI:10.1115/GT2017-63314.Search in Google Scholar
27. Laroche E, Fenot M, Dorignac E, Vuillerme JJ, Brizzi LE, Larroya JC. A combined experimental and numerical investigation of the flow and heat transfer inside a turbine vane cooled by jet impingement. J Turbomach. 2017;140.3. ISSN: 0889-504X. DOI:10.1115/1.4038411.Search in Google Scholar
28. Taira K, Brunton SL, Dawson STM, Rowley CW, Colonius T, Mckeon BJ, et al. Modal analysis of fluid flows: an overview. Aiaa J. 2017;55.12:4013–41.10.2514/1.J056060Search in Google Scholar
29. Schroeder RP, Thole KA. Adiabatic effectiveness measurements for a baseline shaped film cooling hole. Heat Transfer Turbo Expo: Power for Land, Sea, and Air. 2014;5B. Dusseldorf, Germany. DOI: 10.1115/GT2014-25992. URL: https://doi.org/10.1115/GT2014-25992.Search in Google Scholar
30. Schroeder RP, Thole KA. Adiabatic effectiveness measurements for a baseline shaped film cooling hole. Heat Transfer Turbo Expo: Power for Land, Sea, and Air. 2014;5B. DOI:10.1115/GT2014-25992. eprint: https://asmedigitalcollection.asme.org/GT/proceedings-pdf/GT2014/45721/V05BT13A036/2424686/v05bt13a036-gt2014-25992.pdf. URL: https://doi.org/10.1115/GT2014-25992.Search in Google Scholar
31. Chatterjee A. An introduction to the proper orthogonal decomposition. Curr Sci. 2000;78.7:171–4.Search in Google Scholar
32. Wilhelmus HA, Schilders HAVDV, Rommes J. Model order reduction: theory, research aspects and applications. Berlin Heidelberg: Springer, 2008. ISBN: 978-3-540-78840-9. DOI:10.1007/978-3-540-78841-6.Search in Google Scholar
33. Lin D, Xinrong S, Yuan X. The development and mechanisms of the high pressure turbine vane wake vortex. J Eng Gas Turbines Power. 2018;140.9. ISSN: 0742-4795. DOI:10.1115/1.4039802.Search in Google Scholar
34. Li H, Su X, Yuan X. Entropy analysis of the flat tip leakage flow with delayed detached eddy simulation. Entropy. 2019;21.1. ISSN: 1099-4300. DOI: 10.3390/e21010021. URL: http://www.mdpi.com/1099-4300/21/1/21.Search in Google Scholar PubMed PubMed Central
35. Brand M. Incremental singular value decomposition of uncertain data with missing values. Berlin Heidelberg: Springer; 2002. p. 707–72.10.1007/3-540-47969-4_47Search in Google Scholar
© 2020 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Novel Closed-Form Equation for Critical Pressure and Optimum Pressure Ratio for Turbojet Engines
- Development of Combustor for a Hybrid Turbofan Engine
- A Parametric Study of Hydrogen Fuel Effects on Exergetic, Exergoeconomic and Exergoenvironmental Cost Performances of an Aircraft Turbojet Engine
- A Model Reference Adaptive Sliding Mode Control Method for Aero-Engine
- Numerical Study of Mixing Enhancement in 2D Supersonic Ejector
- Flow Development Through An S-Shaped Diffusing Duct
- Nozzle Geometry Effect on Twin Jet Flow Characteristics
- Application of Proper Orthogonal Decomposition Method in Unsteady Flow Field Analysis of Axial High Bypass Fan
- A Research on Aero-engine Control Based on Deep Q Learning
- Blade Number Selection for a Splittered Mixed-Flow Compressor Impeller Using Improved Loss Model
- Study of Correctly Expanded Sonic Jet with Air Tabs
- Large-Eddy Simulation of Shaped Hole Film Cooling with the Influence of Cross Flow
- Modal Analysis of the Axial Compressor Blade: Advanced Time-Dependent Electronic Interferometry and Finite Element Method
- Exergy Analysis of a Turboprop Engine at Different Flight Altitude and Speeds Using Novel Consideration
- Thermal Optimization Design of Heat Exchanger in Supersonic Engine with Parameters’ Fluctuation
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Novel Closed-Form Equation for Critical Pressure and Optimum Pressure Ratio for Turbojet Engines
- Development of Combustor for a Hybrid Turbofan Engine
- A Parametric Study of Hydrogen Fuel Effects on Exergetic, Exergoeconomic and Exergoenvironmental Cost Performances of an Aircraft Turbojet Engine
- A Model Reference Adaptive Sliding Mode Control Method for Aero-Engine
- Numerical Study of Mixing Enhancement in 2D Supersonic Ejector
- Flow Development Through An S-Shaped Diffusing Duct
- Nozzle Geometry Effect on Twin Jet Flow Characteristics
- Application of Proper Orthogonal Decomposition Method in Unsteady Flow Field Analysis of Axial High Bypass Fan
- A Research on Aero-engine Control Based on Deep Q Learning
- Blade Number Selection for a Splittered Mixed-Flow Compressor Impeller Using Improved Loss Model
- Study of Correctly Expanded Sonic Jet with Air Tabs
- Large-Eddy Simulation of Shaped Hole Film Cooling with the Influence of Cross Flow
- Modal Analysis of the Axial Compressor Blade: Advanced Time-Dependent Electronic Interferometry and Finite Element Method
- Exergy Analysis of a Turboprop Engine at Different Flight Altitude and Speeds Using Novel Consideration
- Thermal Optimization Design of Heat Exchanger in Supersonic Engine with Parameters’ Fluctuation
