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Research Papers

Numerical Investigation on Unsteady Effects of Hot Streak on Flow and Heat Transfer in a Turbine Stage

[+] Author and Article Information
Bai-Tao An

Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, P.R.C.anbt@mail.etp.ac.cn

Jian-Jun Liu

Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, P.R.C.jjl@mail.etp.ac.cn

Hong-De Jiang

Department of Thermal Engineering, Tsinghua University, Beijing 100084, P.R.C.jianghd@tsinghua.edu.cn

J. Turbomach 131(3), 031015 (Apr 20, 2009) (15 pages) doi:10.1115/1.2988172 History: Received April 09, 2008; Revised April 13, 2008; Published April 20, 2009

This paper presents a detailed flow and heat transfer characteristic analysis on gas turbine first-stage turbine under hot streak inlet conditions. Two kinds of inlet total temperature conditions are specified at the turbine stage inlet. The first is uniform inlet total temperature, and the second is hot streak 2D total temperature contour. The two kinds of inlet conditions have the same mass-averaged total temperature and the same uniform inlet total pressure. The hot streak total temperature contours are obtained according to the exit shape of an annular-can combustor. The ratio of the highest total temperature in the hot streak to the mass-averaged total temperature is about 1.23, and one hot streak corresponds to two vane passages and four blade passages. Six hot streak circumferential positions relative to the Vane 1 leading edge varied from 2% to 81% pitch are computed and analyzed. The results show that hot streak obviously increases the nonuniform degree of vane heat load in comparison with the uniform total temperature inlet condition. The change in hot streak circumferential position leads to the circumferential parameter variation at stator exit and also leads to different transient periodic fluctuating characteristics of heat load and pressure on the rotor blade surface. The hot streak of relative pitch at 65% obtains a similar heat load for the two vanes corresponding to one hot streak and small fluctuation in the averaged heat load on the rotor blade.

Copyright © 2009 by American Society of Mechanical Engineers
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Figures

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Figure 1

Model of the first-stage turbine: (a) meridian view, and (b) S1 view (N=0)

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Figure 2

Computational grid for the present simulations: (a) domain grid, and (b) near wall grid

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Figure 3

Temperature periodic variation of the monitor point in rotor domain

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Figure 4

Computational grid for Mark-II cascade (11)

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Figure 5

Wall heat transfer coefficient comparison

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Figure 6

Circumferential mass-averaged total temperature distribution along radial direction at stage inlet plane

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Figure 7

Inlet total temperature conditions: (a) the circumferential positions of the inlet hot streak and probing planes and points in stator and rotor domain, and (b) the inlet total temperature contours

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Figure 8

Temperature contours at 65% vane height

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Figure 9

Hot streak development along flow direction in stator

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Figure 10

Wall limiting stream line of the vane under uniform total temperature inlet condition: (a) suction surface, and (b) pressure surface

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Figure 11

Exit (x/C=103%) circumferential temperature distribution across the highest temperature point (N=10)

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Figure 12

Exit (x/C=103%) radial temperature distribution across the highest temperature point (N=10)

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Figure 13

Surface pressure distributions of Vane 1 (N=10)

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Figure 14

Stator exit flow field under uniform total temperature inlet condition (N=0): (a) static temperature contours, (b) static pressure contours, and (c) total pressure contours

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Figure 15

Exit (x/C=103%) circumferential parameter distribution at 65% vane height (N=10): (a) flow angle, (b) Mach number, (c) total pressure, (d) static pressure, (e) total temperature, and (f) velocity

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Figure 16

Total temperature and total pressure contours in rotational frame at rotor inlet for the seven schemes (N=20)

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Figure 17

Surface pressure distributions at 65% blade height (N=0–39): (a) uniform total temperature inlet condition, and (b) hot streak inlet condition (RPLE=48%)

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Figure 18

Transient variation of surface pressure at 65% blade height of three typical points

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Figure 19

q/q0 distributions at 65% vane height (N=10)

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Figure 20

q/q0 distributions at 10% vane height (N=10)

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Figure 21

q/q0 distributions of rotor blade (N=0–39): (a) uniform total temperature inlet condition, and (b) hot streak inlet condition (RPLE=48%)

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Figure 22

Transient variation of q/q0 on blade suction surface (RPLE=48%)

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Figure 23

Transient temperature contours at 65% blade height (N=15)

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Figure 24

Transient variation of q/q0 at 65% blade height of three typical points

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Figure 25

Transient variation of the averaged q/q0 on the blade surface

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