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Research Papers

Improving Purge Air Cooling Effectiveness by Engineered End-Wall Surface Structures—Part II: Turbine Cascade

[+] Author and Article Information
Xin Miao

Department of Mechanical Engineering and
Aeronautics,
City, University of London,
Northampton Square, London EC1V 0HB, UK
e-mail: Xin.Miao@city.ac.uk

Qiang Zhang

Department of Mechanical Engineering and
Aeronautics,
City, University of London,
Northampton Square, London EC1V 0HB, UK
e-mail: Qiang.Zhang.1@city.ac.uk

Chris Atkin

Department of Mechanical Engineering and
Aeronautics,
City, University of London,
Northampton Square, London EC1V 0HB, UK
e-mail: Chris.Atkin.1@city.ac.uk

Zhengzhong Sun

Department of Mechanical Engineering
and Aeronautics City,
University of London Northampton Square,
London EC1V 0HB, UK
e-mail: Zhengzhong.Sun@city.ac.uk

Yanshang Li

Siemens Industrial Turbomachinery Limited,
Lincoln LN5 7FD, UK
e-mail: yansheng.li@siemens.com

1Correponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received January 31, 2018; final manuscript received July 11, 2018; published online August 20, 2018. Assoc. Editor: David G. Bogard.

J. Turbomach 140(9), 091002 (Aug 20, 2018) (11 pages) Paper No: TURBO-18-1014; doi: 10.1115/1.4040854 History: Received January 31, 2018; Revised July 11, 2018

Motivated by the recent advances in additive manufacturing, a novel turbine end-wall aerothermal management method is presented in this two-part paper. The feasibility of enhancing purge air cooling effectiveness through engineered surface structure was experimentally and numerically investigated. The fundamental working mechanism and improved cooling performance for a 90 deg turning duct are presented in Part I. The second part of this paper demonstrates this novel concept in a low-speed linear cascade environment. The performance in three purge air blowing ratios is presented and enhanced cooling effectiveness and net heat flux reduction (NHFR) were observed from experimental data, especially for higher blow ratios. The Computational fluid dynamics (CFD) analysis indicates that the additional surface features are effective in reducing the passage vortex and providing a larger area of coolant coverage without introducing additional aerodynamic loss.

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Figures

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Fig. 1

A schematic of experiment facility

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Fig. 2

Inlet end-wall boundary layer velocity profile measured one axial chord upstream of the blade leading edge

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Fig. 3

(a) Time histories of the cold purge air, end-wall and inlet temperatures, and (b) variations of wall heat flux and surface temperature during one typical transient measurement for one selected wall location

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Fig. 4

Measurement errors due to 1D semi-infinite conduction assumption, assessed through a two-dimensional (2D) transient conduction analysis

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Fig. 5

(a) R2 distribution for linear regression and (b) relative uncertainty (%U) in Tad distribution

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Fig. 6

Computational domain and mesh

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Fig. 7

Film cooling effectiveness distributions obtained by Wright et al. [45] and present CFD study

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Fig. 8

Distributions of film cooling effectiveness (experimental data)

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Fig. 9

Distributions of hf/h0 (experimental data)

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Fig. 10

Distributions of NHFR (experimental data)

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Fig. 11

Distributions of film cooling effectiveness (CFD results): (a) smooth surface and (b) ribbed surface

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Fig. 12

Distribution of hf/h0 (CFD results): (a) smooth surface and (b) ribbed surface

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Fig. 13

Distribution of NHFR (CFD results): (a) smooth surface and (b) ribbed surface

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Fig. 14

Isosurfaces of Q-criteria for smooth and ribbed surface: (a) smooth surface and (b) ribbed surface

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Fig. 15

An isotemperature surface with θ=0.6: (a) smooth surface and (b) ribbed surface

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Fig. 16

Nondimensional temperature θ distributions at three cross sections: (a) smooth surface and (b) ribbed surface

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Fig. 17

Streamwise vorticity distribution at three cross sections: (a) smooth surface and (b) ribbed surface

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Fig. 18

Dimensionless entropy generation rate per unit volume distributions at three cross sections: (a) smooth surface and (b) ribbed surface

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Fig. 19

Distributions of Aerodynamic loss coefficient at the exit plane: (a) smooth surface and (b) ribbed surface

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