Numerical study of transition process in different zones of a compressor cascade channel
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Xiang Li
,
Qun Zheng
Abstract
The complex vortex structure compressor leads to the problem that the transition model is insufficient in predicting the flow instability of the compressor. In this paper, the rectangular cascade of compressor of different turning-angle conditions is taken as the object, and the transition characteristics on the end wall and the blade surface of the compressor cascade are in comparison by the method of large eddy simulation/LES. The effects of the horseshoe vortex and the separation bubble over the compressor cascade on the transition process are emphatically discussed. By analyzing characteristic parameters of the vortex structure, it is found that the separated transitional flow corresponds to multiple separations-and reattachments of the shedding vortex, and is affected by the cross-flow transition and the separate-transition. Finally, by discussing the instability of the separation line, reattachment line and the cross-flow inflection point of the separated transitional flow, it reveals that the transient disturbance caused by the vortex motion is an important reason affecting the prediction accuracy of the transition model.
Acknowledgments
The authors wish to thank the financial support of Harbin Engineering University.
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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: National Natural Science Foundation of China joint fund for regional innovation and development U20A20298 and National Science and Technology Major Project 2017-II-0006-0019.
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
References
1. Boyle, RJ, Senyitko, RG. Measurements and predictions of surface roughness effects on the turbine vane aerodynamics. In: Turbo expo: power for lanld, sea, and air; 2003, vol 36894:291–303 pp.10.1115/GT2003-38580Search in Google Scholar
2. Menter, FR, Langtry, RB, Likki, SR. A correlation-based transition model using local variables: Part I—model formulation. In: Turbo expo: power for land, sea, and air; 2004, vol 41693:57–67 pp.10.1115/GT2004-53452Search in Google Scholar
3. Papa, F, Madanan, U, Goldstein, RJ. Modeling and measurements of heat/mass transfer in a linear turbine cascade. J Turbomach 2017;139:091002. https://doi.org/10.1115/1.4036106.Search in Google Scholar
4. Liu, Y, Tang, Y, Scillitoe, AD, Tucker, PaulG. Modification of shear stress transport turbulence model using helicity for predicting corner separation flow in a linear compressor cascade. J Turbomach 2020;142:021004. https://doi.org/10.1115/1.4045658.Search in Google Scholar
5. Stratford, BS. The prediction of separation of the turbulent boundary layer. J Fluid Mech 1959;5:1–16. https://doi.org/10.1017/s0022112059000015.Search in Google Scholar
6. Xiang, XH, Chen, JQ, Yuana, XX, Wana, BB, Zhuang, Y, Zhang, YF, et al.. Cross-flow transition model predictions of hypersonic transition research vehicle. Sichuan: Aerospace science and technology; 2022.10.1016/j.ast.2022.107327Search in Google Scholar
7. Roberts, SK, Yaras, MI. Modeling of boundary-layer transition. In: Turbo expo: power for land, sea, and air; 2004, vol 41693:81–92 pp.10.1115/GT2004-53664Search in Google Scholar
8. Savill, AM. One-point closures applied to transition. In: Turbulence and transition modelling. Dordrecht: Springer; 1996:233–68 pp.10.1007/978-94-015-8666-5_6Search in Google Scholar
9. Xiang, X, Zhang, Y, Chen, J. Process in transition models for cross-flow in stabilities. Acta Aerodyn Sin 2018;36:254–64. https://doi.org/10.7638/kqdlxxb-2018.0041.Search in Google Scholar
10. Shi, Y, Bai, J, Hua, J. Study and modification of cross-flow induced transition model based on local variables. J Aeronaut 2016;3:780–9.Search in Google Scholar
11. Pichler, R, Zhao, Y, Sandberg, R, Michelassi, V, Pacciani, R, Marconcini, M, et al.. Large-eddy simulation and RANS analysis of the end-wall flow in a linear low-pressure turbine cascade, Part I: flow and secondary vorticity fields under varying inlet condition. J Turbomach 2019;141:121005. https://doi.org/10.1115/1.4045080.Search in Google Scholar
12. Marconcini, M, Pacciani, R, Arnone, A, Michelassi, V, Pichler, R, Zhao, Y, et al.. Large eddy simulation and RANS analysis of the end-wall flow in a linear low-pressure-turbine cascade—Part II: loss generation. J Turbomach 2019;141:051004. https://doi.org/10.1115/1.4042208.Search in Google Scholar
13. Cui, J, Nagabhushana Rao, V, Tucker, P. Numerical investigation of contrasting flow physics in different zones of a high-lift low-pressure turbine blade. ASME J Turbomach 2016;138:011003. https://doi.org/10.1115/1.4031561.Search in Google Scholar
14. Gross, A, Marks, CR, Sondergaard, R. Numerical investigation of low-pressure turbine junction flow. AIAA J 2017;55:3617–21. https://doi.org/10.2514/1.j055859.Search in Google Scholar
15. Simpson, RL. Aspects of turbulent boundary-layer separation. Prog Aero Sci 1996;32:457–521. https://doi.org/10.1016/0376-0421(95)00012-7.Search in Google Scholar
16. Gross, A, Romero, S, Marks, C. Numerical investigation of low-pressure turbine endwall flows. In: 54th AIAA aerospace sciences meeting; 2016:0331 p.10.2514/6.2016-0331Search in Google Scholar
17. Saric, WS, Reed, HL, White, EB. Stability and transition of three-dimensional boundary layers. Annu Rev Fluid Mech 2003;35:413–40. https://doi.org/10.1146/annurev.fluid.35.101101.161045.Search in Google Scholar
18. Mingyang, W, Ziliang, LI, Ge, HAN, Chengwu, Y, Shengfeng, Z, Zhang, Y, et al.. Vortex dynamics and entropy generation in separated transitional flow over a compressor blade at various incidence angles. Acta Aeronautica Astronautica Sinica 2022;35:42–52. https://doi.org/10.1016/j.cja.2021.06.021.Search in Google Scholar
19. Stratford, BS. An experimental flow with zero skin friction throughout its region of pressure rise. J Fluid Mech 1959;5:17–35. https://doi.org/10.1017/s0022112059000027.Search in Google Scholar
20. Stankowski, Tomasz, Sheaf, Cristopher, Otter, John, et al.. Aerodynamic design of separate-jet exhausts for future civil aero-engines-Part II: design space exploration, surrogate modeling, and optimization. J Eng Gas Turbines Power 2016;138:1–12. https://doi.org/10.1115/1.4032652.Search in Google Scholar
21. Tani, I. Low-speed flows involving bubble separations. Prog Aero Sci 1964;5:70–103. https://doi.org/10.1016/0376-0421(64)90004-1.Search in Google Scholar
22. Cumpsty, NA. Compressor aerodynamics. New York: Longman Scientific & Technical; 1989.Search in Google Scholar
23. Li, H, Zheng, Q, Jiang, B. Study on compressor large eddy simulation and experiment. J Eng Therm Energy Power 2021;36:117–25.Search in Google Scholar
24. Arnal, D, Habiballah, C, Coustols, C. Laminar instability theory and transition criteria in two-and three-dimensional flows. Rech Aerospatiale 1984;2:45–63.Search in Google Scholar
25. Michel, R, Arnal, D, Coustols, E, Juillen, JC. Experimental and theoretical studies of boundary layer transition on a swept infinite wing. In: Kozlov, VV, editor. Laminar-turbulent transition. International union of theoretical and applied mechanics. Berlin, Heidelberg: Springer; 1985.10.1007/978-3-642-82462-3_69Search in Google Scholar
26. Misaka, T, Obayashi, S. Application of local correlation-based transition model to flows around wings. In: AIAA; 2006:918 p.10.2514/6.2006-918Search in Google Scholar
27. Han, Y, Cao, W. Flat-plate hypersonic boundary-layer flow instability and transition prediction considering air dissociation. Appl Math Mech 2019;40:719–36. https://doi.org/10.1007/s10483-019-2480-6.Search in Google Scholar
28. Medida, S, Baeder, J. A new crossflow transition onset criterion for RANS turbulence models. In: Aiaa computational fluid dynamics conference; 2013.10.2514/6.2013-3081Search in Google Scholar
29. Zhang, Z. Theory and modeling of turbulence. Beijing: Ttinghua University Press; 2005.Search in Google Scholar
30. Xue, Feng Zhang. Separation and Transition Control on Ultral-High-Lift Low Pressure Turbine Blades in Unsteady Flow. New York: Cambridge University; 2005.Search in Google Scholar
31. Muti Lin, JC, Laura, LP. Low-Reynolds-number separation on an airfoil. AIAA 1996;34:1570–7. https://doi.org/10.2514/3.13273.Search in Google Scholar
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Articles in the same Issue
- Frontmatter
- The International Journal of Turbo and Jet Engines
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- Analysis on impulse characteristics of pulse detonation engine with nozzles
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- Research on new integral squeeze film damper vibration control of micro turbojet engine at high speed
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Articles in the same Issue
- Frontmatter
- The International Journal of Turbo and Jet Engines
- The aerothermodynamic cycle optimal design of a turbofan engine
- Multi-condition design optimization of groove flow control technique in an axial-flow pump
- Analysis on impulse characteristics of pulse detonation engine with nozzles
- Numerical investigation on implication of innovative hydrogen strut injector on performance and combustion characteristics in a scramjet combustor
- Optimization of Kiel geometry for better recovery factor in high temperature measurement in aero gas turbine engine
- Applicability of correlational data-mining to small-scale turbojet performance map generation
- Effect of multi-zone effusion cooling on an adiabatic flat plate for gas turbine application
- Flow quality improvement of the wind tunnel testing for a highly-loaded compressor cascade at high incidence
- Modeling and analysis of 3D radiative heat transfer in combustor
- A creep-fatigue life prediction model considering multi-factor coupling effect
- Optimization-based transient control of turbofan engines: a sequential quadratic programming approach
- Investigations on the interaction between the front and aft purge flow and the downstream vane of 1.5-stage turbine
- A study on design optimization for compressor blisks
- Exploration of an unconventional validation tool to investigate aero engine transonic fan flutter signature
- Evaluation of non-uniform water film behavior on the performance of an axial aeroengine compressor
- Predicting remaining useful life of turbofan engines using degradation signal based echo state network
- Effect of G-type integral squeeze film damper on the dynamic characteristics in rotor system
- Development of a one-dimensional code for the initial design of a micro gas turbine mixed flow compressor stage
- Numerical and experimental investigations of tip clearance effects in a high-flow-coefficient centrifugal compressor
- Experimental and numerical investigation on the effect of turboprop engine exhaust gas impingement on pusher aircraft
- Heat transfer distribution of single oblique jet impingement in crossflow under different inlet conditions
- Performance enhancement and flow separation control in an S-duct by air injection
- Gas dynamic analysis of the modern single shaft gas turbine engine flow path
- Aero engine health monitoring, diagnostics and prognostics for condition-based maintenance: an overview
- Influence of leading edge point on aerodynamic performance of asymmetric leading edge compressor airfoils
- The aerothermal performance of turbine blade squealer tip at various Reynolds numbers and Mach numbers with moving endwall
- Numerical investigation of a variable stator vane with nonuniform partial radial gaps in an annular compressor cascade
- Effect of self-recirculating casing treatment on the unsteady flow and stability of counter-rotating axial-flow compressor
- Research on temperature rise characteristics of end V-groove ring seal
- Research on the influence of honeycomb cell blockage on the seal leakage characteristics
- Vortex structure control based bleed in axial compressor cascade with tip clearance using large eddy simulation
- Development and application of a profile loss model considering the low-Re effect in low-pressure turbine
- Optimization of ACE mode transition control schedule considering geometric adjustment speed
- Numerical investigation of flow control in low-pressure turbine cascade using Gurney Flaps
- The design method of the V-shaped groove piston ring
- Control of subsonic jets using vanes as vortex generators
- Impact investigation of inlet environmental changes on the rated condition performance of a high-pressure compressor
- Research on new integral squeeze film damper vibration control of micro turbojet engine at high speed
- Effect of the distribution of the upstream probe support on performance of compressor cascade
- Effect of bypass ratio on sonic underexpanded co-flow jets with finite lip thickness
- Machine learning augmented multi-sensor data fusion to detect aero engine fan rotor blade flutter
- CFD analysis of flow control in compressor cascade using MVGs
- Quantitative investigation of the evaporation and resistance characteristics of inlet jet precooling
- Study on laser de-weight and dynamic balance technology of rotating machines
- Integrated design and analysis of inlet and missile with two side layout
- Research on turboprop engine control method based on linear parameter varying model
- Modeling and validation of the volume effect on the axial fan transient performance
- Ground effects on the aerodynamics of a wing with slot type distributed propulsion system for VTOL applications
- Multidisciplinary sensitivity analysis for turbine blade considering thickness uncertainties
- Accurate measurement and evaluation method of axial compressor efficiency under the influence of multiple factors
- Control mechanism of secondary flow in a turbine cascade with non-axisymmetric endwall profiling under Co-rotating incoming vortex
- Infrared simulation of aircraft rear fuselage based on a coupled CFD method
- Effect of multi-hole trench cooling on an adiabatic flat plate for gas turbine application
- Numerical study of transition process in different zones of a compressor cascade channel
