Hot gas ingestion in chute rim seal clearance of gas turbine
-
Xingyun Jia
,
Huaiyu Dong
Abstract
The Reynolds-averaged Navier–Stokes (RANS) solver was used to calculate, using a test rig to verify the accuracy. The interaction mechanism between different sealed cooling air and gas ingestion at the rotor-stator cavity and chute rim clearance has been investigated. Several groups of representative sealed cooling air flow were selected to explore the cooling efficiency, flow characteristics, tangential and radial velocity ratios in the cavity and the pressure potential field characteristics of trailing edge. The conclusions are obtained: the sealed cooling air flow rate has a significant marginal effect on the sealing effect. The gas ingestion behavior under the small sealed cooling air flow belongs to the disc cavity intrusion, and the intrusion and outflow regions at the of rim clearance are obviously divided into the intrusion characteristic section and the outflow characteristic section. The ingestion behavior under large sealed cooling air flow belongs to clearance ingestion, and the intrusion flow is limited to the chute rim clearance position, which cannot be further penetrated into the cavity. At this time, the clearance area and the cavity area become independent, and the gas ingestion characteristics depend more on the internal flow of the clearance and the vortex structure formed.
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
-
Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
-
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).
-
Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
References
1. Wang, CZ, Johnson, BV, Cloud, DF. Rim seal ingestion characteristics for axial clearance rim seals in a closely-spaced turbine stage from a numerical simulation. ASME paper no. GT2006-90965; 2006.10.1115/GT2006-90965Search in Google Scholar
2. Young, C, Smout, PD. Recent advances in the simulation of gas turbine secondary air systems. In: Proceedings of 25th ICAS congress, Hamburg, Germany, 2006.Search in Google Scholar
3. Zhang, H, Chai, BQ, Jiang, B, Yue, GQ. Numerical analysis of finger seal with grooves on lifting pads. J Propul Power 2015;31:805–14.10.2514/1.B35377Search in Google Scholar
4. Childs, P, Dullenkopf, K. Internal air systems experimental rig best practice. ASME paper no. GT2006-90215; 2006.10.1115/GT2006-90215Search in Google Scholar
5. Coren, DD, Atkins, NR, Turner, J, Eastwood, D, Davies, S, Child, P, et al.. An advanced multi configuration turbine stator well cooling test facility. ASME paper no. GT2010-23450; 2010.10.1115/GT2010-23450Search in Google Scholar
6. Antonio, GV, Jeffrey, AD, Attilio, G, Coren, DD, Eastwood, D. Heat transfer in turbine hub cavities adjacent to the main gas path including FE-CFD coupled thermal analysis. ASME paper no. GT2011-45695; 2011.Search in Google Scholar
7. Owen, JM. Prediction of ingestion through turbine rim seals, part I: rotationally-induced ingress. ASME paper no. GT2009-59121; 2009.10.1115/GT2009-59121Search in Google Scholar
8. Owen, JM. Prediction of ingestion through turbine rim seals, part II: externally-induced and combined ingress. ASME paper no. GT2009-59122; 2009.10.1115/GT2009-59122Search in Google Scholar
9. Cao, C, Chew, JW, Millington, PR, Hogg, SI. Interaction of rim seal and annulus flows in an axial flow turbine. ASME paper no. GT2003-38368; 2003.10.1115/GT2003-38368Search in Google Scholar
10. Bhon, D, Rudzinski, B. Influence of rim seal geometry on hot gas ingestion into the upstream cavity of an axial turbine stage. ASME paper no. 99-GT-248; 1999.10.1115/99-GT-248Search in Google Scholar
11. Bhon, 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. ASME paper no. GT2000-0284, 2000.10.1115/2000-GT-0284Search in Google Scholar
12. Bhon, D, Michael, W. Improved formulation to determine minimum sealing flow–Cw,min–for different sealing configurations. ASME paper no. GT2003-38465; 2003.10.1115/GT2003-38465Search in Google Scholar
13. Jakoby, R, Zierer, T, Lindblad, K, Larsson, J, Decker, A. Numerical simulation of the unsteady flow field in an axial gas turbine rim seal configuration. ASME paper no. GT2004-53829; 2004.10.1115/GT2004-53829Search in Google Scholar
14. 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.Search in Google Scholar
15. 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.Search in Google Scholar
16. Chew, JW, Gao, F, Palermo, DM. Flow mechanisms in axial turbine rim sealing. Proc Inst Mech Eng C Mech Eng Sci 2018;233. https://doi.org/10.1177/0954406218784612.Search in Google Scholar
17. Berg, RA, Tan, CS, Ding, Z, Laskowski, G, Palafox, P, Miorini, R. Experimental and analytical assessment of cavity modes in a gas turbine wheelspace. J Eng Gas Turbines Power 2018;140, https://doi.org/10.1115/1.4038474.Search in Google Scholar
18. Li, J, Gao, Q, Li, Z, Feng, Z. Numerical investigations on the sealing effectiveness of turbine honeycomb radial rim seal. J Eng Gas Turbines Power 2016;138, https://doi.org/10.1115/1.4033139.Search in Google Scholar
19. Zhang, JH, Ma, HW. Numerical investigation of improving turbine sealing effectiveness through slot width modification of the rim seal. ASME paper no. GT2013-95570; 2013.10.1115/GT2013-95570Search in Google Scholar
20. Scobie, JA, Teuber, R, Yan, SL, Sangan, CM, Wilson, M, Lock, GD Design of an improved turbine rim-seal. J Eng Gas Turbines Power 2016;138, https://doi.org/10.1115/1.4031241.Search in Google Scholar
21. Durocher, E, Lefebvre, G. Abradable rim seal for low pressure turbine stage. United States patent US 20090110548, 2009.Search in Google Scholar
22. Glezer, B, Boyd, GL, Norton, PF. Rim seal for turbine wheel. United States patent US 5503528, 1996.Search in Google Scholar
23. Gao, J, Cao, FK, Chu, ZF, Yue, GQ, Zheng, Q. Rotationally-induced unstable flow characteristics and structural optimization of rim seals [in Chinese] Sci Sin Tech 2019;49:753–66.10.1360/N092018-00337Search in Google Scholar
24. Rohsenow, WM, Hartnett, JP, Cho, YI. Handbook of heat transfer. New York: McGraw-Hill; 1998.Search in Google Scholar
25. Jiang, Y, Lin, H, Yue, G, Zheng, Q, Xu, X. 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.Search in Google Scholar
© 2021 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- 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
Articles in the same Issue
- 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
