Effect of rotor–stator rim cavity flow on the turbine
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Xingyun Jia
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Wenhao Wang
Abstract
Relative high pressure in the rotor–stator (RS) cavity helps to improve its seal effectiveness. However, every 1% increase in the cavity flow results in a decrease of the stage power of turbine by about 0.32% and a decrease in the aerodynamic efficiency by about 0.33%. With rim cavity flow, the pressure distribution in the suction side of rotor blade domain and the turbine flow structure show obvious circumferential differences, which are caused by the interactions between the RS cavity flow and the mainstream. The flow characteristic in the false externally-induced ingress in rim clearance is proposed for the first time to reveal the flow mechanism in the effect of RS rim cavity flow on the turbine.
Funding source: National Science and Technology Major Project
Award Identifier / Grant number: 2017-IV-0010-0047
Funding source: China Postdoctoral Science Foundation
Award Identifier / Grant number: 2020M670113
Funding source: Fundamental Research Funds for the Central Universities
Award Identifier / Grant number: ZY2105
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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: The authors wish to thank the support of the National Science and Technology Major Project (2017-IV-0010-0047), the China Postdoctoral Science Foundation funded project (2020M670113) and the Fundamental Research Funds for the Central Universities (ZY2105).
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
References
1. Young, C, Smout, PD. Recent advances in the simulation of gas turbine secondary air systems. In: 25th congress of the international council of the aeronautical sciences, Hamburg; 2006.Suche in Google Scholar
2. Smout, PD, Chew, JW, Childs, P. ICAS-GT: a European collaborative research programme on internal cooling air systems for gas turbines. In: ASME turbo expo: power for land, sea, & air, Amsterdam; 2002. https://doi.org/10.1115/gt2002-30479.Suche in Google Scholar
3. Childs, P, Dullenkopf, K, Bohn, D. Internal air systems experimental rig best practice. In: ASME turbo expo 2006: power for land, sea and air, Barcelona; 2006. https://doi.org/10.1115/gt2006-90215.Suche in Google Scholar
4. Coren, DD, Atkins, NR, Turner, JR, Eastwood, DE, Davies, S, Childs, PRN, et al.. An advanced multi configuration turbine stator well cooling test facility. In: ASME turbo expo 2010, Glasgow; 2010. https://doi.org/10.1115/gt2010-23450.Suche in Google Scholar
5. Valencia, AG, Dixon, JA, Guardini, A, Coren, DD, Eastwood, D. Heat transfer in turbine hub cavities adjacent to the main gas path including FE-CFD coupled thermal analysis. In: ASME turbo expo 2011, Vancouver; 2011.Suche in Google Scholar
6. Owen, JM. Prediction of ingestion through turbine rim seals. Part I: rotationally-induced ingress. In: ASME turbo expo 2009, Orlando; 2009. https://doi.org/10.1115/gt2009-59121.Suche in Google Scholar
7. Owen, JM. Prediction of ingestion through turbine rim seals. Part II: externally-induced and combined ingress. In: ASME turbo expo 2009, Orlando; 2009. https://doi.org/10.1115/gt2009-59122.Suche in Google Scholar
8. Bohn, D, Rudzinski, B, Sürken, N, Gärtner, W. Experimental and numerical investigation of the influence of rotor blades on hot gas ingestion into the upstream cavity of an axial turbine stage. In: ASME turbo expo: power for land, sea, & air 2000, Munich; 2001.10.1115/2000-GT-0284Suche in Google Scholar
9. Bhon, D, Wolff, M. Improved formulation to determine minimum sealing flow-Cw, min-for different sealing configurations. In: ASME turbo expo 2003, collocated with the 2003 international joint power generation conference 2003, Atlanta; 2003.10.1115/GT2003-38465Suche in Google Scholar
10. Jakoby, R, Zierer, T, Lindblad, K, Larsson, J, Devito, L, Bohn, DE, et al.. Numerical simulation of the unsteady flow field in an axial gas turbine rim seal configuration. In: ASME turbo expo 2004: power for land, sea, and air 2004, Vienna; 2004. https://doi.org/10.1115/gt2004-53829.Suche in Google Scholar
11. Chew, JW, Dadkhah, S, Turner, AB. Rim sealing of rotor–stator wheelspaces in the absence of external flow. J Turbomach 1992;114:433–8. https://doi.org/10.1115/1.2929162.Suche in Google Scholar
12. Gao, F, Chew, JW, Beard, PF, Amirante, D, Hills, NJ. Large-eddy simulation of unsteady turbine rim sealing flows. Int J Heat Fluid Flow 2018;70:160–70. https://doi.org/10.1016/j.ijheatfluidflow.2018.02.002.Suche in Google Scholar
13. Chew, JW, Gao, F, Palermo, DM. Flow mechanisms in axial turbine rim sealing. Proc IME C J Mech Eng Sci 2019;233:7637–57. https://doi.org/10.1177/0954406218784612.Suche in Google Scholar
14. Reid, K, Denton, J, Pullan, G, Curtis, E, Longley, J. The effect of stator-rotor hub sealing flow on the mainstream aerodynamics of a turbine. In: ASME turbo expo 2006: power for land, sea, and air. Spain 2006. https://doi.org/10.1115/gt2006-90838.Suche in Google Scholar
15. Horwood, J, Hualca, FP, Wilson, M, Scobie, JA , Sangan, CM , Lock, GD. Unsteady computation of ingress through turbine rim seals. In: ASME turbo expo 2018: turbomachinery technical conference and exposition, Oslo; 2018. https://doi.org/10.1115/gt2018-75321.Suche in Google Scholar
16. Popovic, I, Hodson, HP. Aerothermal impact of the interaction between hub leakage and mainstream flows in highly-loaded high pressure turbine blades. J Turbomach 2013;135:061014-1-061014-11.10.1115/1.4023621Suche in Google Scholar
17. Chilla, M, Hodson, H, Newman, D. Unsteady interaction between annulus and turbine rim seal flows. J Turbomach 2013;135:1–10. https://doi.org/10.1115/1.4023016.Suche in Google Scholar
18. Gallier, K, Lawless, P, Fleeter, S. Investigation of seal purge flow effects on the hub flow field in a turbine stage using particle image velocimetry. In: 36th AIAA/ASME/SAE/ASEE joint propulsion conference and exhibit, Las Vegas; 2000. https://doi.org/10.2514/6.2000-3370.Suche in Google Scholar
19. Jia, W. Numerical investigation of the effects of rim seal geometric structure on turbine performance. Sci Technol Eng 2018;18:177–83.Suche in Google Scholar
20. Yang, F, Zhou, L, Wang, ZX. Numerical investigation for interaction and loss mechanisms between rim seal flow and rotor. J Propuls Technol 2018;39:2481–9.Suche in Google Scholar
21. Li, J, Chen, Y, Song, LM, Gao, Q, Li, ZG. Review of the aerothermal performance of turbine stage with consideration of interaction between the rim seal purge flow and mainstream. Gas Turbine Technol 2017;30:18–26+31.Suche in Google Scholar
22. Gao, J, Cao, FK, Chu, ZF, Yue, GQ, Zheng, Q. Rotationally-induced unstable flow characteristics and structural optimization of rim seals. Sci Sin Technol 2019;49:753–66.10.1360/N092018-00337Suche in Google Scholar
23. Jia, XY. Research on gas ingestion and sealing mechanism of turbine rotor–stator cavity [Ph.D. thesis]. PR China: Harbin Engineering University; 2019.Suche in Google Scholar
24. Jiang, YT, Lin, HF, Yue, GQ, Zheng, Q, Xu, XL. Aero-thermal optimization on multi-rows film cooling of a realistic marine high pressure turbine vane. Appl Therm Eng 2017;111:537–49. https://doi.org/10.1016/j.applthermaleng.2016.09.143.Suche in Google Scholar
© 2021 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Natural frequency analysis of a functionally graded rotor-bearing system with a slant crack subjected to thermal gradients
- Evaluation of exit pattern factors of an annular aero gas turbine combustor at altitude off-design conditions
- Research on quasi-one-dimensional modeling and performance analysis of RBCC propulsion system
- Performance characteristics of flow in annular diffuser using CFD
- Control-oriented quasi-one dimensional modeling method for scramjet
- Effect of rotor–stator rim cavity flow on the turbine
- An improved aerodynamic performance optimization method of 3-D low Reynolds number rotor blade
- Hot gas ingestion in chute rim seal clearance of gas turbine
- An improved compact propulsion system model based on batch normalize deep neural network
- Study of the vortex chamber and its application for the development of novel measurement and control devices
- Effect of equivalence ratio on the detonation noise characteristics of pulse detonation engine
- Simulation and analysis of hot plume infrared signature based on SNB model
Artikel in diesem Heft
- Frontmatter
- Natural frequency analysis of a functionally graded rotor-bearing system with a slant crack subjected to thermal gradients
- Evaluation of exit pattern factors of an annular aero gas turbine combustor at altitude off-design conditions
- Research on quasi-one-dimensional modeling and performance analysis of RBCC propulsion system
- Performance characteristics of flow in annular diffuser using CFD
- Control-oriented quasi-one dimensional modeling method for scramjet
- Effect of rotor–stator rim cavity flow on the turbine
- An improved aerodynamic performance optimization method of 3-D low Reynolds number rotor blade
- Hot gas ingestion in chute rim seal clearance of gas turbine
- An improved compact propulsion system model based on batch normalize deep neural network
- Study of the vortex chamber and its application for the development of novel measurement and control devices
- Effect of equivalence ratio on the detonation noise characteristics of pulse detonation engine
- Simulation and analysis of hot plume infrared signature based on SNB model
