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Research Papers

Aerothermal Performance of a Nozzle Vane Cascade With a Generic Nonuniform Inlet Flow Condition—Part II: Influence of Purge and Film Cooling Injection

[+] Author and Article Information
G. Barigozzi

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

H. Abdeh

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

A. Perdichizzi

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

M. Henze, J. Krueckels

Ansaldo Energia Switzerland AG,
Baden 5401, Switzerland

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 1, 2016; final manuscript received March 24, 2017; published online May 9, 2017. Editor: Kenneth Hall.

J. Turbomach 139(10), 101004 (May 09, 2017) (9 pages) Paper No: TURBO-16-1221; doi: 10.1115/1.4036437 History: Received September 01, 2016; Revised March 24, 2017

In the present paper, the influence of the presence of an inlet flow nonuniformity on the aerodynamic and thermal performance of a film cooled linear nozzle vane cascade is fully assessed. Tests have been carried out with platform cooling, with coolant ejected through a slot located upstream of the leading edge. Cooling air is also ejected through a row of cylindrical holes located upstream of the slot, simulating a combustor cooling system. An obstruction was installed upstream of the cascade at variable tangential and axial position to generate a flow nonuniformity. The cascade was tested at a high inlet turbulence intensity level (Tu1 = 9%) and at a constant inlet Mach number of 0.12 and nominal cooling condition. Aerothermal characterization of vane platform was obtained through five-hole probe and end wall adiabatic film cooling effectiveness measurements. Results show a relevant negative impact of inlet flow nonuniformity on the cooled cascade aerodynamic and thermal performance. Higher film cooling effectiveness and lower aerodynamic losses are obtained when the inlet flow nonuniformity is located at midpitch, while lower effectiveness and higher losses are obtained when it is aligned to the vane leading edge. Moving the nonuniformity axially or changing its blockage only marginally influences the platform thermal protection.

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Figures

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Fig. 1

The wind tunnel assembly

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Fig. 2

Cascade model and platform cooling scheme

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Fig. 3

Inlet flow: (a) velocity and (b) Tu distributions at X/cax = −0.3 and Z/H = 0.5

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Fig. 4

ζ distributions at X/cax = 150%: (a) nonuniform (t = 0.5s) [25], (b) nonuniform (t = 0.0s) [25], (c) nonuniform and cooled (t = 0.5s), and (d) nonuniform and cooled (t = 0.0s)

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Fig. 5

Ω distributions at X/cax = 150%: (a) nonuniform (t = 0.5s) [25], (b) nonuniform (t = 0.0s) [25], (c) nonuniform and cooled (t = 0.5s), and (d) nonuniform and cooled (t = 0.0s)

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Fig. 6

η distributions: (a) uniform inlet [11], (b) 0s, (c) 0.25s, (d) 0.5s, (e) 0.75s, and (f) 1s

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Fig. 7

Pitch-averaged η distributions for variable t (a = 0.7cax and w = 0.3s)

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Fig. 8

η distributions (t = 0.5s): (a) a = 0.54cax, (b) a = 0.96cax, and (c) a = 0.7cax and w = 0.24s

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Fig. 9

Pitch-averaged η distributions for variable a and w (t = 0.5s)

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Fig. 10

Area-averaged effectiveness variation: influence of (a) t (a = 0.7caxw = 0.3s) and (b) a and w (t = 0.5s)

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