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Research Papers: Gas Turbines: Turbomachinery

Effects of Impeller Squealer Tip on Centrifugal Compressor Performance

[+] Author and Article Information
Riccardo Da Soghe

Ergon Research srl,
Via Panciatichi 92,
Florence 50127, Italy
e-mail: riccardo.dasoghe@ergonresearch.it

Cosimo Bianchini

Ergon Research srl,
Via Panciatichi 92,
Florence 50127, Italy
e-mail: cosimo.bianchini@ergonresearch.it

Dante Tommaso Rubino

GE Oil & Gas,
Via Matteucci 2,
Florence 50127, Italy
e-mail: dantetommaso.rubino@ge.com

Lorenzo Toni

GE Oil & Gas,
Via Matteucci 2,
Florence 50127, Italy
e-mail: lorenzo.toni@ge.com

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received June 28, 2016; final manuscript received July 29, 2016; published online October 11, 2016. Editor: David Wisler.

J. Eng. Gas Turbines Power 139(3), 032603 (Oct 11, 2016) (7 pages) Paper No: GTP-16-1284; doi: 10.1115/1.4034541 History: Received June 28, 2016; Revised July 29, 2016

This paper summarizes the main results sorted out from a design of experiment (DoE) based on a validated computational fluid dynamics (CFD). Several tip recessed geometries applied to an unshrouded impeller were considered in conjunction with two tip clearance levels. The computations show that recessed tip geometries have positive effects when considering high-flow coefficient values, while in part-load conditions the gain is reduced. Starting from the results obtained when studying tip cavities, a single rim tip squealer geometry was then analyzed: the proposed geometry leads to performance improvements for all the tested conditions considered in this work.

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References

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Figures

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Fig. 1

Flow through the tip gap for an unshrouded blade [9]: (a) thick blade and (b) thin blade

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Fig. 2

Flat tip (a) and squealered tip (b)

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Fig. 4

Tip characteristics—(up right) ribs' details and (bottom) single side rim arrangement details

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Fig. 5

Analyzed domain and applied boundary conditions

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Fig. 6

Computational grid details

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Fig. 7

Schematic cross section of a model test stage

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Fig. 8

Comparisons between CFD and experiments

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Fig. 9

Variation of β as a function of η at the impeller exit, Φ/Φ* = 120%

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Fig. 10

Scaled entropy contour, Φ/Φ* = 120%—(left) case baseline_LowCl, (center) case 006, and (right) case 028

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Fig. 11

Scaled entropy contour, Φ/Φ* = 120%—(up) case 028 and (down) case 022

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Fig. 12

Blade load 95% span, geometry baseline_LowCl

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Fig. 13

Fluid tangential velocity case baseline_LowCl—(up) Φ/Φ* = 120% and (down) Φ/Φ* = 100%

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Fig. 14

β over η at the impeller exit, Φ/Φ* = 100%

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Fig. 15

β over η at the impeller exit, Φ/Φ* = 92%

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Fig. 16

Single rim arrangement—efficiency gain for different operating conditions

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Fig. 17

Scaled entropy contour—(left) single rim design and (right) case 22, Φ/Φ* = 120%

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