Research Papers: Flows in Complex Systems

Improving the Film Cooling of a Rotor Blade Platform

[+] Author and Article Information
Giovanna Barigozzi

Department of Engineering and
Applied Sciences,
University of Bergamo,
Viale Marconi 5,
Dalmine 24044, BG, Italy
e-mail: giovanna.barigozzi@unibg.it

Antonio Perdichizzi

Department of Engineering and
Applied Sciences,
University of Bergamo,
Viale Marconi 5,
Dalmine 24044, BG, Italy
e-mail: antonio.perdichizzi@unibg.it

Roberto Abram

Ansaldo Energia S.p.A.,
Via Nicola Lorenzi 8,
Genova 16152, Italy
e-mail: roberto.abram@ansaldoenergia.it

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received July 20, 2016; final manuscript received August 12, 2017; published online October 19, 2017. Assoc. Editor: Olivier Coutier-Delgosha.

J. Fluids Eng 140(2), 021101 (Oct 19, 2017) (6 pages) Paper No: FE-16-1464; doi: 10.1115/1.4037972 History: Received July 20, 2016; Revised August 12, 2017

This paper shows the results of an experimental activity developed in cooperation between Ansaldo Energia and the Department of Engineering and Applied Science of Bergamo University with the aim of assessing the impact of newly designed holes on the thermal protection of a rotor blade platform. The original rotor blade platform featured ten cylindrical holes located along the blade pressure side (PS). Moreover, the channel front side was cooled exploiting the seal purge flow exiting the stator to rotor interface gap. The front midchannel, and particularly the region around the interplatform gap, remained uncooled. To protect this region, two sets of cylindrical holes were designed and manufactured on a seven blade cascade model for experimental verification. Aerodynamic and thermal tests were carried out at low Mach number. To evaluate the interaction of injected flow with secondary flows a five hole probe was traversed downstream of the trailing edge plane. The thermal behavior was analyzed by using thermochromic liquid crystals technique, so to obtain film cooling effectiveness distributions. The seven-hole configuration coupled with a low blowing ratio of about 1.0 provided the best thermal protection without any impact on the aerodynamic performance.

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Fig. 1

Platform film cooling effectiveness distribution: (a) PS cooling holes [24] and (b) purge gap [17]

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Fig. 2

The wind tunnel (1: inlet duct; 2: test section; 3: tailboard; 4: diffuser; 5: fan; 6: AC motor; 7: discharge channel)

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Fig. 3

Cascade and end wall cooling geometry

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Fig. 4

The cooling flow supply lines

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Fig. 5

TLC calibration curve

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Fig. 6

Example of selected image

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Fig. 7

ζ and Ω distributions at X/cax = 108% for seven holes (M1,PS = 1.3 and M1,7 holes = 1.1)

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Fig. 8

Oil and dye flow visualization (solid end wall)

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Fig. 9

Film cooling effectiveness distributions for the five-hole scheme and variable injection conditions

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Fig. 10

Film cooling effectiveness distributions for the seven-hole scheme and variable injection conditions

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Fig. 11

η Distributions along the interplatform separation line: (a) five holes and (b) seven holes configuration




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