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Research Papers

A Comprehensive Investigation of Blade Row Interaction Effects on Stator Loss Utilizing Vane Clocking

[+] Author and Article Information
Natalie R. Smith

School of Mechanical Engineering,
Purdue University,
500 Allison Rd,
West Lafayette, IN 47907
e-mail: natalie.smith@swri.org

Nicole L. Key

School of Mechanical Engineering,
Purdue University,
West Lafayette, IN 47907
e-mail: nkey@purdue.edu

1Present address: Machinery Program, Southwest Research Institute, 6220 Culebra Rd, San Antonio, TX 78238.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 27, 2017; final manuscript received October 10, 2017; published online June 14, 2018. Editor: Kenneth Hall.

J. Turbomach 140(7), 071004 (Jun 14, 2018) (12 pages) Paper No: TURBO-17-1178; doi: 10.1115/1.4040111 History: Received September 27, 2017; Revised October 10, 2017

Blade row interactions drive the unsteady performance of high-pressure compressors. Vane clocking is the relative circumferential positioning of consecutive stationary vane rows with the same vane count. By altering the upstream vane wake's path with respect to the downstream vane, vane clocking changes the blade row interactions and results in a change in steady total pressure loss on the downstream vane. The open literature lacks a conclusive discussion of the flow physics governing these interactions in compressors. This paper presents the details of a comprehensive vane clocking study on the embedded stage of the Purdue three-stage axial compressor. The steady loss results, including radial total pressure profiles and surface flow visualization, suggest a shift in the stator 2 corner separations occurs between clocking configurations associated with the maximum and minimum total pressure loss. To better understand the flow mechanisms driving the vane clocking effects on the steady stator 2 performance, time-resolved interrogations of the stator 2 inlet flow field, surface pressure unsteadiness, and boundary layer response were conducted. The stator 2 surface flows, both pressure unsteadiness and boundary layer transition, are influenced by vane clocking and interactions between rotor 1 and rotor 2, but neither of these results indicate a cause for the change in steady total pressure loss. Moreover, they are a result of upstream changes in the flow field: the interaction between the stator 1 wake and rotor 2 results in a circumferentially varying pattern which alters the inlet flow field for the downstream row, including the unsteadiness and frequency content in the tip and hub regions. Therefore, under different clocking configurations, stator 2 experiences significantly different inlet blockage and unsteadiness from the rotor 2 tip leakage flow and hub corner separation, which, in turn, shifts the radial blade loading distribution and subsequent loss development of stator 2.

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References

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Figures

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Fig. 2

Compressor flowpath including station numbering scheme and instrumentation locations

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Fig. 1

Definition of vane clocking configuration, CL

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Fig. 3

Stator 2 instrumented with (a) leading edge Kiel-heads and static taps around the under stator knife seal, (b) Kulites embedded at 50% and 80% span, and (c) 18 sensor hot-film array

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Fig. 4

Loading conditions along 100%Nc with change in stator 2 total pressure loss due to vane clocking

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Fig. 8

CP RMS average rotor 2 blade pass period for different clocking configuration at (a) peak efficiency, (b) L7, and (c) L8

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Fig. 5

Radial total pressure profiles downstream of stator 2 for six clocking configurations at three loading conditions

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Fig. 6

Stator 2 wake profiles for two clocking configurations at (a) PE tip, (b) L6 tip, (c) L7 tip, (d) PE hub, (e) L6 hub, and (f) L7 hub

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Fig. 7

Surface flow visualization of stator 2 suction surface for clocking configurations CL2 and CL5 at high loading

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Fig. 9

Time-averaged radial profiles of total pressure at the stator 2 inlet highlighting clocking configurations CL2 and CL5 at high loading

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Fig. 10

Surface pressure unsteadiness on stator 2 suction side at 20%cx changes with clocking configuratio: (a) 50%span and (b) 80%span

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Fig. 11

Space-time diagrams of (a,c) QWSS RMS and (b,d) QWSS skew for two clocking configurations at loading L4 at 50%span: (a) CL2 RMS/RMSmax, (b) CL2 Skew/Skewmax, (c) CL5 RMS/RMSmax, and (d) CL5 Skew/Skewmax

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