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Research Papers

Influence of Mainstream Turbulence Intensity on Heat Transfer Characteristics of a High Pressure Turbine Stage With Inlet Hot Streak

[+] Author and Article Information
Zhiduo Wang, Zhaofang Liu

Institute of Turbomachinery,
School of Energy and Power Engineering,
Xi'an Jiaotong University,
Xi'an, Shaanxi 710049, China

Zhenping Feng

Institute of Turbomachinery,
School of Energy and Power Engineering,
Xi'an Jiaotong University,
Xi'an, Shaanxi 710049, China
e-mail: zpfeng@mail.xjtu.edu.cn

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received November 2, 2015; final manuscript received November 8, 2015; published online December 29, 2015. Editor: Kenneth C. Hall.

J. Turbomach 138(4), 041005 (Dec 29, 2015) (11 pages) Paper No: TURBO-15-1243; doi: 10.1115/1.4032062 History: Received November 02, 2015; Revised November 08, 2015

An unsteady computational study was carried out on GE-E3 high pressure (HP) turbine at inflow turbulence intensities of 5%, 10%, and 20% accompanying with inlet hot streak (HS) at two circumferential positions (impinging and nonimpinging relative to vane leading edge) to analyze the interacted turbulence and HS influences. Turbulence decay mechanisms in turbine passage were presented, and the airfoil heat transfer behaviors were explored by means of adiabatic wall temperature, heat transfer coefficient (HTC), and wall heat flux. The results indicate that the elevated turbulence leads to favorable turbine airfoil temperature distributions, and turbulence induced HS attenuation mainly occurs in vane passage. In addition, the HS dispersion is related directly to the temperature gradients. Although the endwall temperature increases by more than 20 K (2.8% inlet mass-averaged temperature) and midregion temperature decreases by 16 K at blade leading edge, the hot region on blade pressure surface (PS) is only weakened by about 7 K, when turbulence intensity is increased from 5% to 20%. Higher turbulence significantly affects the airfoil HTC, excepting the regions secondary and leakage flow effects are dominating. Therefore, the tip and blade suction surface (SS) trailing edge heat flux is decreased for the temperature decline at higher turbulence, which is beneficial to tip cooling. HS position not only affects the airfoil surface temperature variations but also slightly affects the vane and blade midspan HTC for the variation of heat transfer driving temperature.

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Figures

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Fig. 3

Predicted and experimental HTCs on blade tip

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Fig. 4

Mesh of the computational domain

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Fig. 5

Turbine inlet temperature profiles: (a) radial and circumferential total temperature distributions and (b) inlet total temperature distributions and isosurface of total temperature 780 K

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Fig. 6

Turbulence kinetic energy at: (a) vane 50% span and (b) blade 50% span (Tu = 10%, HS at vane leading edge)

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Fig. 7

Time-averaged turbulence intensity at: (a) vane 50% span and (b) blade 50% span (HS impinging on vane leading edge)

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Fig. 8

Vane surface temperature at Tu of 5%

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Fig. 9

Vane SS limiting streamlines colored with turbulence kinetic energy (adiabatic wall and impinging HS)

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Fig. 10

Vane surface temperature variations caused by the turbulence effect: (a) T10% − T5% and (b) T20% − T10%

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Fig. 11

Temperature at Tu of 5% and 20% and the temperature difference between Tu of 20% and 5% on vane PS 50% axial chord

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Fig. 2

Predicted and experimental HTCs at C3X midspan of different inlet turbulence levels

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Fig. 1

C3X cascade midspan HTCs predicted by different turbulence models

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Fig. 12

Circumferential averaged temperature difference at the vane and blade interface (adiabatic wall condition)

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Fig. 13

HTC distributions at: (a) 10% vane span, (b) 50% vane span, and (c) 90% vane span

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Fig. 14

Rotor surface temperature at Tu of 5%

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Fig. 15

Temperature difference T20% − T5% of a transient time instant at four cross sections to illustrate the HS attenuation (HS at vane midpassage, AC-axial chord)

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Fig. 16

Time-averaged temperature differences T20% − T5% at three axial cross sections in the rotor passage (HS at leading edge, SF-secondary flow, LF-leakage flow)

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Fig. 17

Rotor surface temperature differences T20% − T5%

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Fig. 18

Circumferential averaged temperature at the blade trailing edge (adiabatic wall condition)

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Fig. 19

HTC distributions at: (a) 10% blade span, (b) 50% blade span, and (c) 90% blade span

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Fig. 20

Tip surface: (a) temperature at Tu of 5% and (b) temperature difference T20% − T5% (left for HS at vane leading edge, and right for HS at vane midpassage)

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Fig. 21

Tip HTC distributions at: (a) Tu = 5%, (b) Tu = 10%, and (c) Tu = 20% (left for HS at vane leading edge and right for HS at vane midpassage)

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Fig. 22

HTC differences at blade tip surface for HS at vane leading edge

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Fig. 23

Isentropic Mach number of tip surface and Mach number of four axial cross sections for Tu of 10% and HS at vane leading edge

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Fig. 24

Blade surface heat flux difference q20% − q5% for HS at vane midpassage

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