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Research Papers

Endwall Film Cooling Performance for a First-Stage Guide Vane With Upstream Combustor Walls and Inlet Injection

[+] Author and Article Information
Xing Yang

Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Institute of Turbomachinery,
School of Energy and Power Engineering,
Xi'an Jiaotong University,
Xi'an 710049, Shaanxi, China;
Department of Mechanical Engineering,
University of Minnesota Twin Cities,
Minneapolis, MN 55455

Zhao Liu, Zhansheng Liu

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

Terrence Simon

Department of Mechanical Engineering,
University of Minnesota Twin Cities,
Minneapolis, MN 55455

Zhenping Feng

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

1Corresponding author.

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF THERMAL SCIENCE AND ENGINEERING APPLICATIONS. Manuscript received December 8, 2017; final manuscript received July 23, 2018; published online October 15, 2018. Assoc. Editor: Ting Wang.

J. Thermal Sci. Eng. Appl 11(1), 011008 (Oct 15, 2018) (11 pages) Paper No: TSEA-17-1477; doi: 10.1115/1.4041342 History: Received December 08, 2017; Revised July 23, 2018

Effects of an upstream combustor wall on turbine nozzle endwall film cooling performance are numerically examined in a linear cascade in this paper. Film cooling is by two rows of cooling holes at 20% of the axial chord length upstream of the vane leading edge (LE) plane. The combustor walls are modeled as flat plates with square trailing edges (TE) positioned upstream of the endwall film cooling holes. A combustor wall is in line with the LE of every second vane. The influence of the combustor wall, when shifted in the axial and tangential directions, is investigated to determine effects on passage endwall cooling for three representative film cooling blowing ratios. The results show how shed vortices from the combustor wall greatly alter the flow field near the cooling holes and inside the vane passage. Film cooling distribution patterns, particularly in the entry region and along the pressure side of the passage, are affected. The combustor wall leads to an imbalance in film cooling distribution over the endwalls for adjacent vane passages. Results show a larger effect of tangential shift of the combustor wall on endwall cooling effectiveness than the effect of an equal axial shift. The study provides guidance regarding design of combustor-to-turbine transition ducts.

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Figures

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Fig. 1

Schematic of multiple combustors with first turbine vanes in an industrial gas turbine, MHI [26,27]

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Fig. 2

Schematic of endwall cooling design

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Fig. 3

Computation domain

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Fig. 4

Local Nusselt number distributions on the blade surfaces at z/S = 0.371 for Rein = 2.2 × 105, Tuin = 4.0%: (a) pressure surface and (b) suction surface

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Fig. 5

Laterally averaged film cooling effectiveness on the endwall for blowing ratios of 0.5

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Fig. 6

Grid independency and uncertainty of numerical solutions: (a) local effectiveness along the −0.25P streamline (see streak near the suction surface) and (b) fine grid solution with discretization error bars

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Fig. 7

Comparison of streamwise nondimensional vorticity contours on planes of different axial and circumferential locations: (a) datum no combustor wall, (b) case 1 a/D = 5, t/P = 0.2, (c) case 2 a/D = 5, t/P = −0.2, (d) case 3 a/D = 1, t/P = 0, (e) case 4 a/D = 5, t/P=0, and (f) case 5 a/D = 10, t/P = 0

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Fig. 8

Nondimension temperature distributions on centerline cut plane of R2N7, superimposed with streamlines: (a) datum (no combustor wall), (b) case 1 (a/D = 5, t/P = 0.2), (c) case 2 (a/D = 5, t/P = −0.2), (d) case 3 (a/D = 1, t/P = 0), (e) case 4 (a/D = 5, t/P = 0), and (f) case 5 (a/D = 10, t/P = 0)

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Fig. 9

Film cooling distributions on the endwall for inlet blowing ratio of 1.3: (a) datum, (b) case 1, (c) case 2, (d) case 3, (e) case 4, and (f) case 5

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Fig. 10

Film cooling distributions on the endwall for inlet blowing ratio of 2.1: (a) datum, (b) case 1, (c) case 2, (d) case 3, (e) case 4, and (f) case 5

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Fig. 11

Film cooling distributions on the endwall for inlet blowing ratio of 2.8: (a) datum, (b) case 1, (c) case 2, (d) case 3, (e) case 4, and (f) case 5

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Fig. 12

Axial variation of laterally averaged film cooling effectiveness on the neighboring vane endwalls at different blowing ratios: (a) datum, (b) case 1, (c) case 2, (d) case 3, (e) case 4, and (f) case 5

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Fig. 13

Area-averaged cooling effectiveness enhancement over the datum case for various inlet blowing ratios

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