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Research Papers

Aerothermal Performance of a Nozzle Vane Cascade With a Generic Nonuniform Inlet Flow Condition—Part I: Influence of Nonuniformity Location

[+] Author and Article Information
A. Perdichizzi

Dipartimento di Ingegneria e Scienze Applicate,
Università degli Studi di Bergamo,
Dalmine, BG 24044, Italy
e-mail: antonio.perdichizzi@unibg.it

H. Abdeh

Dipartimento di Ingegneria e Scienze Applicate,
Università degli Studi di Bergamo,
Dalmine, BG 24044, Italy
e-mail: hamed.abdeh@unibg.it

G. Barigozzi

Dipartimento di Ingegneria e Scienze Applicate,
Università degli Studi di Bergamo,
Dalmine, BG 24044, Italy
e-mail: giovanna.barigozzi@unibg.it

M. Henze, J. Krueckels

Ansaldo Energia Switzerland Ltd.,
Baden 5401, Switzerland

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 7, 2016; final manuscript received September 22, 2016; published online November 8, 2016. Editor: Kenneth Hall.

J. Turbomach 139(3), 031002 (Nov 08, 2016) (9 pages) Paper No: TURBO-16-1230; doi: 10.1115/1.4034816 History: Received September 07, 2016; Revised September 22, 2016

In this paper, the modifications induced by the presence of an inlet flow nonuniformity on the aerodynamic performance of a nozzle vane cascade are experimentally assessed. Tests were carried out in a six vane linear cascade whose profile is typical of a first stage nozzle guide vane of a modern heavy-duty gas turbine. An obstruction was located in the wind tunnel inlet section to produce a nonuniform flow upstream of the leading edge plane. The cascade was tested in an atmospheric wind tunnel at an inlet Mach number Ma1 = 0.12, with a high turbulence intensity (Tu1 = 9%) and variable obstruction tangential and axial positions, as well as tangential extension. The presented results show that an inlet flow nonuniformity influences the stagnation point position when it faces the vane leading edge from the suction side. A relevant increase of both 2D and secondary losses is observed when the nonuniformity is aligned to the vane leading edge. When it is instead located in between the passage, it does not affect the stagnation point location, in the meanwhile allowing a reduction in the secondary loss.

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References

Figures

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Fig. 1

The wind tunnel assembly

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Fig. 2

Cascade model and blockage

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Fig. 3

Inlet boundary layer (X/cax = −1.6—uniform)

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Fig. 4

Inlet flow: (a) velocity, (b) angle, and (c) Tu distributions at X/cax = −0.3 and Z/H = 0.5 (a = 0.7cax and w = 0.3 s)

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Fig. 5

Vane load for variable t (a = 0.7cax and w = 0.3s): (a) vane #1 and (b) vane #2

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Fig. 6

Ma distributions at Z/H = 0.5 (a = 0.7cax and w = 0.3s): (a) uniform, (b) t = 0s, and (c) t = 0.5s

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Fig. 7

Tu distribution at Z/H = 0.5 (a = 0.7cax and w = 0.3s): (a) t = 0s and (b) t = 0.5s

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Fig. 8

pt,2/pt,1 distributions at Z/H = 0.5 and X/cax = 1.5 (a = 0.7cax and w = 0.3s)

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Fig. 9

Platform oil and dye surface flow visualizations (a = 0.7cax and w = 0.3s): (a) uniform, (b) t = 0s, (c) t = 0.25s, (d) t = 0.5s, (e) t = 0.75s

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Fig. 10

Platform TLC color map

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Fig. 11

ζ distributions at X/cax = 1.5 (a = 0.7cax and w = 0.3s): (a) uniform inlet, (b) t = 0s, (c) t = 0.25s, (d) t = 0.5s, (e) t = 0.75s, and (f) t = 1s

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Fig. 12

Ω distributions at X/cax = 1.5 (a = 0.7cax and w = 0.3s): (a) uniform inlet, (b) 0s, (c) 0.25s, (d) 0.5s, (e) 0.75s, and (f) 1s

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Fig. 13

Vane #1 load distribution for variable a and w (t = 0s)

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Fig. 14

Platform surface flow visualizations (t = 0s): (a) a = 0.54cax (w = 0.3s), (b) a = 0.96cax (w = 0.3s), and (c) w = 0.24s (a = 0.7cax)

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Fig. 15

ζ distributions for variable axial position a (t = 0s and w = 0.3s): (a) a = 0.54cax and (b) a = 0.96cax

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Fig. 16

Mass-averaged loss coefficient: influence of (a) t and (b) a

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