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Research Papers: Gas Turbines: Turbomachinery

Unsteady Analysis on the Effects of Tip Clearance Height on Hot Streak Migration Across Rotor Blade Tip Clearance

[+] Author and Article Information
Zhaofang Liu, Zhao Liu

Institute of Turbomachinery,
Xi'an Jiaotong University,
Xi'an 710049, China

Zhenping Feng

Institute of Turbomachinery,
Xi'an Jiaotong University,
Xi'an 710049, China
e-mail: zpfeng@mail.xjtu.edu.cn

1Corresponding author.

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received January 16, 2014; final manuscript received January 27, 2014; published online February 28, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 136(8), 082605 (Feb 28, 2014) (11 pages) Paper No: GTP-14-1033; doi: 10.1115/1.4026805 History: Received January 16, 2014; Revised January 27, 2014

This paper presents an investigation on the hot streak migration across rotor blade tip clearance in a high pressure gas turbine with different tip clearance heights. The blade geometry is taken from the first stage of GE-E3 turbine engine. Three tip clearances, 1.0%, 1.5%, and 2.5% of the blade span with a flat tip were investigated, respectively, and the uniform and nonuniform inlet temperature profiles were taken as the inlet boundary conditions. A new method for heat transfer coefficient calculation recommended by Maffulli and He has been adopted. By solving the unsteady compressible Reynolds-averaged Navier–Stokes equations, the time dependent solutions were obtained. The results indicate that the large tip clearance intensifies the leakage flow, increases the hot streak migration rate, and aggravates the heat transfer environment on the blade tip. However, the reverse secondary flow dominated by the relative motion of casing is insensitive to the change of tip clearance height. Attributed to the high-speed rotation of rotor blade and the low pressure difference between both sides of blade, a reverse leakage flow zone emerges over blade tip near trailing edge. Because it is possible for heat transfer coefficient distributions to be greatly different from heat flux distributions, it becomes of great concern to combine both of them in consideration of hot streak migration. To eliminate the effects of blade profile variation due to twist along the blade span on the aerothermal performance in tip clearance, the tested rotor (straight) blade and the original rotor (twisted) blade of GE-E3 first stage with the same tip profile are compared in this paper.

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References

Povey, T., and Qureshi, I., 2009, “Developments in Hot-Streak Simulators for Turbine Testing,” ASME J. Turbomach., 131(3), p. 031009. [CrossRef]
Povey, T., and Qureshi, I., 2008, “A Hot-Streak (Combustor) Simulator Suited to Aerodynamic Performance Measurements,” Proc. IMechE., Part G: J. Aerospace Eng., 222(6), pp. 705–720. [CrossRef]
Barringer, M. D., Thole, K. A., and Polanka, M. D., 2004, “Developing a Combustor Simulator for Investigating High Pressure Turbine Aerodynamics and Heat Transfer,” ASME Paper No. GT2004-53613. [CrossRef]
Barringer, M. D., Thole, K. A., and Polanka, M. D., 2006, “Experimental Evaluation of an Inlet Profile Generator for High-Pressure Turbine Tests,” ASME Paper No. GT2006-90401. [CrossRef]
Butler, T. L., Sharma, O. P., Joslyn, H. D., and Dring, R. P., 1989, “Redistribution of Inlet Temperature Distortion in an Axial Flow Turbine Stage,” AIAA J. Propul. Power, 5(1), pp. 64–71. [CrossRef]
Roback, R. J., and Dring, R. P., 1993, “Hot Streaks and Phantom Cooling in a Turbine Rotor Passage: Part 1—Separate Effects,” ASME J. Turbomach., 115(4), pp. 657–666. [CrossRef]
Mathison, R. M., Haldeman, C. W., and Dunn, M. G., 2012, “Aerodynamics and Heat Transfer for a Cooled One and One-Half Stage High-Pressure Turbine—Part I: Vane Inlet Temperature Profile Generation and Migration,” ASME J. Turbomach., 134(1), p. 011006. [CrossRef]
Barringer, M. D., Thole, K. A., Polanka, M. D., Clark, J. P., and Koch, P. J., 2007, “Migration of Combustor Exit Profiles Through High Pressure Turbine Vanes,” ASME Paper No. GT2007-27157. [CrossRef]
Povey, T., Chana, K. S., Jones, T. V., and Hurrion, J., 2007, “The Effect of Hot-Streaks on HP Vane Surface and Endwall Heat Transfer: An Experimental and Numerical Study,” ASME J. Turbomach., 129(1), pp. 32–43. [CrossRef]
Qureshi, I., Beretta, A., and Povey, T., 2011, “Effect of Simulated Combustor Temperature Nonuniformity on HP Vane and Endwall Heat Transfer: An Experimental and Computational Investigation,” ASME J. Gas Turbine Power, 133(3), p. 031901. [CrossRef]
Povey, T., Chana, K. S., and Jones, T. V., 2003, “Heat Transfer Measurements on an Intermediate Pressure Nozzle Guide Vane Tested in a Rotating Annular Turbine Facility, and the Modifying Effects of a Non-Uniform Inlet Temperature Profile,” Proc. IMechE., Part A: J. Power Energy, 217(4), pp. 421–431. [CrossRef]
Jenny, P., Lenherr, C., Kalfas, A., and Abhari, R. S., 2010, “Effect of Hot Streak Migration on Unsteady Blade Row Interaction in an Axial Turbine,” ASME Paper No. GT2010-23034. [CrossRef]
Basol, A. M., Jenny, P., Ibrahim, M., Kalfas, A. I., and Abhari, R. S., 2010, “Hot Streak Migration in a Turbine Stage: Integrated Design to Improve Aerothermal Performance,” ASME Paper No. GT2010-23556. [CrossRef]
Regina, K., Kalfas, A. I., and Abhari, R. S., 2012, “Experimental Investigation of Purge Flow Effects on a High Pressure Turbine Stage,” ASME Paper No. GT2012-69466. [CrossRef]
Lenherr, C., Kalfas, A. I., and Abhari, R. S., 2011, “High Temperature Fast Response Aerodynamic Probe,” ASME J. Gas Turbine Power, 133(1), p. 011603. [CrossRef]
Ong, J., and Miller, R. J., 2008, “Hot Streak and Vane Coolant Migration in a Downstream Rotor,” ASME Paper No. GT2008-50971. [CrossRef]
Smith, C. I., Chang, D., and TavoularisS., 2010, “Effect of Inlet Temperature Non-Uniformity on High-Pressure Turbine Performance,” ASME Paper No. GT2010-22845. [CrossRef]
Dorney, D. J., and Burlet, K. G., 1995, “Hot-Streak Clocking Effects in a 1.5 Stage Turbine,” AIAA J. Propul. Power, 12(3), p. 619–620. [CrossRef]
Burlet, K. G., and Dorney, D. J., 1997, “Three-Dimensional Simulations of Hot Streak Clocking in a 1-1/2 Stage Turbine,” Int. J. Turbo Jet Engines, 14(3), pp. 133–144. [CrossRef]
Burlet, K. G., and DorneyD. J., 2000, “Effects of Radial Location on the Migration of Hot Streaks in a Turbine,” AIAA J. Propul. Power, 16(3), pp. 377–387. [CrossRef]
Simone, S., Montomoli, F., Martelli, F., Chana, K. S., Qureshi, I., and Povey, T., 2012, “Analysis on the Effect of a Nonuniform Inlet Profile on Heat Transfer and Fluid Flow in Turbine Stages,” ASME J. Turbomach., 134(1), p. 011012. [CrossRef]
He, L., Menshikova, V., and Haller, B. R., 2004, “Influence of Hot Streak Circumferential Length-Scale in Transonic Turbine Stage,” ASME Paper No. GT2004-53370. [CrossRef]
Zhao, Q. J., Wang, H. S., and Tang, F., 2008, “Influence of Hot Streak/Airfoil Count Ratios on High Pressure Stage of a Vaneless Counter-Rotating Turbine,” ASME Paper No. GT2008-50542. [CrossRef]
Zhao, Q. J., Wang, H. S., Zhao, X. L., and Xu, J. Z., 2007, “Numerical Investigation on the Influence of Hot Streak Temperature Ratio in a High-Pressure Stage of Vaneless Counter-Rotating Turbine,” Int. J. Rotating Mach., 2007, p. 56097. [CrossRef]
Sondak, D. L., Gupta, V., Orkwis, P. D., and Doney, D. J., 2002, “Effects of Blade Count on Linearized and Nonlinear Hot Streak Clocking Simulations,” AIAA J. Propulsion and Power, 18(6), pp. 1273–1279. [CrossRef]
Khanal, B., He, L., Northall, J., and Adami, P., 2012, “Analysis of Radial Migration of Hot-Streak in Swirling Flow Through HP Turbine Stage,” ASME Paper No. GT2012-68983. [CrossRef]
Azad, G. S., Han, J. C., Teng, S., and Boyle, R. J., 2000, “Heat Transfer and Pressure Distributions on a Gas Turbine Blade Tip,” ASME J. Turbomach., 122(4), pp. 717–724. [CrossRef]
Azad, G. S., Han, J. C., and Boyle, R. J., 2000, “Heat Transfer and Flow on the Squealer Tip of a Gas Turbine Blade,” ASME J. Turbomach., 122(4), pp. 725–732. [CrossRef]
Kwak, J. S., and Han, J. C., 2000, “Heat Transfer Coefficients on the Squealer Tip and Near Squealer Tip Region of a Gas Turbine Blade,” ASME J. Heat Transfer, 125(4), pp. 669–677. [CrossRef]
Kwak, J. S., and Han, J. C., 2002, “Heat Transfer Coefficients on a Gas Turbine Blade Tip and Near Tip Regions,” AIAA Paper No. 2002-3012. [CrossRef]
Yang, D. L., Yu, X. B., and Feng, Z. P., 2010, “Investigation of Leakage Flow and Heat Transfer in a Gas Turbine Blade Tip With Emphasis on the Effect of Rotation,” ASME J. Turbomach., 132(4), p. 041010. [CrossRef]
Ameri, A. A., Rigby, D. L., Steinthorsson, E., Heidmann, J., and Fabian, J. C., 2010, “Unsteady Analysis of Blade and Tip Heat Transfer as Influenced by the Upstream Momentum and Thermal Wakes,” ASME J. Turbomach., 132(4), p. 041007. [CrossRef]
Shyam, V., Ameri, A. A., and Chen, J. P., 2012, “Analysis of Unsteady Tip and Endwall Heat Transfer in a Highly Loaded Transonic Turbine Stage,” ASME J. Turbomach., 134(4), p. 041022. [CrossRef]
Chana, K. S., and Jones, T. V., 2002, “An Investigation on Turbine Tip and Shroud Heat Transfer,” ASME Paper No. GT2002-30554. [CrossRef]
Dorney, D. J., and Sondak, D. L., 2000, “Effects of Tip Clearance on Hot Streak Migration in a High-Subsonic Single-Stage Turbine,” ASME J. Turbomach., 122(4), pp. 613–620. [CrossRef]
Rahman, M. H., Kim, S. I., and Hassan, I., 2012, “Effects of Inlet Temperature Uniformity and Nonuniformity on the Tip Leakage Flow and Rotor Blade Tip and Casing Heat Transfer Characteristics,” ASME J. Turbomach., 134(2), p. 021001. [CrossRef]
Prasad, D., and Hendricks, G. J., 2000, “A Numerical Study of Secondary Flow in Axial Turbines With Application to Radial Transport of Hot Streaks,” ASME J. Turbomach., 122(4), p. 667–673. [CrossRef]
Maffulli, R., and He, L., 2013, “Wall Temperature Effects on Heat Transfer Coefficient,” ASME Paper No. GT2013-94291. [CrossRef]
Rai, M. M., 1989, “Three-Dimensional Navier-Stokes Simulations of Turbine Rotor-Stator Interaction. Part 1—Methodology,” AIAA J. Propul. Power, 5(3), pp. 305–311. [CrossRef]
Timko, L. P., 1984, “Energy Efficient Engine High Pressure Turbine Component Test Performance Report,” NASA CR-168289.
Krishnababu, S. K., Dawes, W. N., Hodson, H. P., Lock, G. D., Hannis, J., and Whitney, C., 2007, “Aero-Thermal Investigations of Tip Leakage Flow in Axial Flow Turbines: Part 2—Effect of Relative Casing Motion,” ASME Paper No. GT2007-27957. [CrossRef]
Roache, P. J., 1994, “Perspective: A Method for Uniform Reporting of Grid Refinement Studies,” ASME J. Fluids Eng., 116(3), pp. 405–413. [CrossRef]
Yaras, M. I., and Sjolander, S. A., 1992, “Effects of Simulated Rotation on Tip Leakage in a Planar Cascade of Turbine Blades: Part 1—Tip Gap Flow,” ASME J. Turbomach., 114(3), pp. 652–659. [CrossRef]

Figures

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Fig. 1

Geometry of the first stage of the GE-E3 turbine

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Fig. 2

Circumferential mass averaged total temperature distribution at the turbine inlet in the radial direction

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Fig. 3

Heat transfer coefficient distributions on blade tips for experimental and predicted results

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Fig. 4

Heat transfer coefficient distributions on blade tips for different meshes

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Fig. 5

Computational domain grids

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Fig. 6

Periodic variation of mass flow, pressure, and temperature separately at four monitoring points: (a) mass flow at the outlet of the stage; (b) tip pressure at the leading and trailing edge (purple line: leading edge, green line: trailing edge); and (c) temperature at the middle of the rotor passage

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Fig. 7

Pressure distribution on the blade surface at 95% of the blade span (AC: axial chord)

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Fig. 8

T distribution in the middle surface of the tip clearance

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Fig. 9

Streamlines and temperature distributions at different ACs at t1 in case no. 2 (left is pressure side)

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Fig. 10

Heat transfer coefficient distribution on the rotor blade tip. (a) The distributions of hq on the rotor blade tip and (b) the distributions of h on the rotor blade tip.

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Fig. 11

Streamline variation with time at 50% AC near the tip region (left is pressure side)

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Fig. 12

Time-space plots of heat transfer coefficient at 50% AC on the rotor blade tip (PS: pressure side, SS: suction side). (a) The distributions of hq on rotor blade tip, and (b) the distributions of h on rotor blade tip.

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Fig. 13

Pressure distribution on the blade surface at 95% of the blade span

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Fig. 14

T distribution in the middle surface of the tip clearance

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Fig. 15

The distributions of hq on rotor blade tip

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