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Research Papers

Experimental Study of Aerodynamic Damping of an Annular Compressor Cascade With Large Mean Incidences

[+] Author and Article Information
M. C. Keerthi

Department of Aerospace Engineering,
Indian Institute of Technology Kanpur,
Kanpur 208016, Uttar Pradesh, India
e-mail: mckee@iitk.ac.in

Abhijit Kushari

Department of Aerospace Engineering,
Indian Institute of Technology Kanpur,
Kanpur 208016, Uttar Pradesh, India
e-mail: akushari@iitk.ac.in

1Corresponding author.

Manuscript received March 8, 2018; final manuscript received December 7, 2018; published online January 21, 2019. Assoc. Editor: Li He.

J. Turbomach 141(6), 061002 (Jan 21, 2019) (17 pages) Paper No: TURBO-18-1055; doi: 10.1115/1.4042214 History: Received March 08, 2018; Revised December 07, 2018

This study addresses flutter that can occur in compressors when operating at high relative incidence. Studies are performed on a subsonic annular compressor cascade containing a sector of blades that can be subjected to controlled torsional oscillation. Measurements taken on the centrally located blade are used to study the unsteady surface pressures developed. Three large mean incidences are considered to characterize the aeroelastic performance. Aerodynamic damping is calculated for each test condition and its variation due to interblade phase angle (IBPA), reduced frequency, and incidence is studied. The source of stability or instability is traced to the nature of unsteady pressures. When the incidence is below the static-stall limit, an increasing incidence is found to exhibit aeroelastically more stable performance, whereas beyond the limit, the stability worsens. For the latter, the amount of improvement in stability by increasing reduced frequency is less compared to the former and its variation with IBPA is not as regular owing to the associated large uncertainty. The nonlinearity effects were found to be relatively higher for this case, especially from the aft region of the suction surface. It is also found that the phase of the local fluctuating pressure and its location on the chord has a decisive influence on the aerodynamic damping and its trends with respect to various parameters are discussed. The results are expected to be useful in the assessing aerodynamic damping trends in relation to the pressure phase variations in specific regions along the chord.

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Figures

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Fig. 1

Photograph and schematic of the oscillating annular cascade

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Fig. 2

(a) Schematic of oscillation mechanism shown for a single blade, (b) photograph of five oscillating blades assembly (c) location of ports along the surface of the instrumented blade, and (d) tube transfer function for pressure measurements

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Fig. 3

Surface static pressure distribution at mid-span location for different incidences

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Fig. 4

Spatio-temporal variation of surface static pressure coefficient for baseline case, IBPA = 0 deg, shown with blade 0 displacement with time

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Fig. 5

Fourier amplitudes of surface static pressure coefficient for baseline case, IBPA = 0 deg

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Fig. 6

(a) Magnitude and (b) phase lead of the first harmonic of pressure for baseline case

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Fig. 7

Carta's stability parameter variation with IBPA for baseline case

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Fig. 8

(a) Local stability parameter variation for baseline case and (b) the sense of stability w.r.t. pressure phase at different regions on blade 0

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Fig. 9

(a) Carta's stability parameter for all IBPAs and (b) the minimum Ξ for low, medium and high-incidence cases

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Fig. 10

Ratio of (a) second and first harmonic pressure magnitudes and (b) first harmonic and mean of other frequencies pressure magnitude for all incidences at k = 0.06

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Fig. 11

(a) Carta's stability parameter for medium incidence at low reduced frequencies and (b) critical reduced frequency curve for medium incidence

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Fig. 12

Effect of average inlet velocity on critical reduced frequency

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Fig. 13

Pressure phase magnitude, phase lead, and local stability parameter at blade mid-span for low incidence

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Fig. 14

Pressure phase magnitude, phase lead, and local stability parameter at blade mid-span for medium incidence

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Fig. 15

Pressure phase magnitude, phase lead, and local stability parameter at blade mid-span for high incidence

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Fig. 16

Pressure phase variation for IBPA corresponding to minimum Ξ for different reduced frequencies

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