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Research Papers

Numerical Analysis of Flow in a Transonic Compressor With a Single Circumferential Casing Groove: Influence of Groove Location and Depth on Flow Instability

[+] Author and Article Information
Yasunori Sakuma

School of Engineering,
University of Tokyo,
Tokyo 1138656, Japan
e-mail: sakuma@aero.t.u-tokyo.ac.jp

Takehiro Himeno

Department of Aeronautics and Astronautics,
University of Tokyo,
Tokyo 1138656, Japan

Yukari Shuto

IHI Corporation,
Tokyo 1901297, Japan

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 3, 2013; final manuscript received July 29, 2013; published online October 25, 2013. Editor: Ronald Bunker.

J. Turbomach 136(3), 031017 (Oct 25, 2013) (9 pages) Paper No: TURBO-13-1132; doi: 10.1115/1.4025575 History: Received July 03, 2013; Revised July 29, 2013

The effect of circumferential single grooved casing treatment on the stability enhancement of NASA Rotor 37 has been examined with computational fluid dynamics analysis. Stall inception mechanism of Rotor 37 is presented first with principal focus on the tip leakage flow behavior, passage blockage, and the vortical flow structures. Detailed observation showed that the combined interaction of the stagnated flow of tip leakage vortex breakdown and the jetlike leakage flow from the midchord region leads to the blade tip-initiated stall inception. The result of numerical parametric study is then demonstrated to show the effect of varying the axial location and the depth of a circumferential single groove. The evaluation based on stall margin improvement showed a higher potential of deeper grooves in stability enhancement, and the optimal position for the groove to be located was indicated to exist near the leading edge of the blade.

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References

Figures

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Fig. 1

NASA Rotor 37 experimental measurement locations

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Fig. 2

Numerical grid alignment near the casing groove

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Fig. 3

Characteristics plot of NASA Rotor 37

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Fig. 4

Comparison of spanwise distribution of total pressure ratio and adiabatic efficiency at Station 4

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Fig. 5

Blockage region distribution within the blade passage in smooth wall condition at three different operating points

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Fig. 6

Mach number distribution at 96% span and the leakage flow streamlines colored with normalized helicity

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Fig. 7

Schematic of near tip flow field

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Fig. 8

Blockage region distribution and the leakage flow streamlines colored with normalized helicity at operating point C

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Fig. 9

Characteristics plot at shallow groove conditions

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Fig. 10

Characteristics plot at deep groove conditions

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Fig. 11

Stall margin improvement in each wall condition

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Fig. 12

Pressure coefficient distribution at 98% span height in operating point C

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Fig. 13

Relationship between groove location and Aeff

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Fig. 14

Relationship between local blade loading and Aeff

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Fig. 15

Tip leakage flow momentum perpendicular to the blade tip camber in operating point C

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Fig. 16

Schematic of flow structure at the blade tip in the region near the casing groove; (a) flow in and out of the groove; (b) flow below the groove

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Fig. 17

Mach number distribution at 96% span and the leakage flow streamlines colored with normalized helicity

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Fig. 18

Blockage region distribution at 96% span in operating point C

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Fig. 19

Definition of jcrit

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