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Research Papers

Influence of Acoustic Blockage on Flutter Instability in a Transonic Nozzle

[+] Author and Article Information
Quentin Rendu

Laboratoire de Mécanique des Fluides et
d'ôAcoustique,
Université Claude Bernard Lyon 1,
Université de Lyon,
43 Boulevard du 11 Novembre 1918,
Villeurbanne 69100, France
e-mail: quentin.rendu@univ-lyon1.fr

Yannick Rozenberg

Laboratoire de Mécanique des Fluides et
d'ôAcoustique,
Université Claude Bernard Lyon 1,
Université de Lyon,
43 Boulevard du 11 Novembre 1918,
Villeurbanne 69100, France

Stéphane Aubert

Laboratoire de Mécanique des Fluides et
d'ôAcoustique,
École Centrale Lyon,
Université de Lyon,
36, avenue Guy de Collongue,
Ecully 69134, France
e-mail: stephane.aubert@ec-lyon.fr

Pascal Ferrand

Laboratoire de Mécanique des Fluides et
d'ôAcoustique,
École Centrale Lyon,
Université de Lyon,
36, avenue Guy de Collongue,
Ecully 69134, France

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received March 14, 2017; final manuscript received September 28, 2017; published online November 21, 2017. Editor: Kenneth Hall.

J. Turbomach 140(2), 021004 (Nov 21, 2017) (10 pages) Paper No: TURBO-17-1044; doi: 10.1115/1.4038279 History: Received March 14, 2017; Revised September 28, 2017

In order to predict oscillating loads on a structure, time-linearized methods are fast enough to be routinely used in design and optimization steps of a turbomachine stage. In this work, frequency-domain time-linearized Navier–Stokes computations are proposed to predict the unsteady separated flow generated by an oscillating bump in a transonic nozzle. The influence of regressive pressure waves on the aeroelastic stability is investigated. This case is representative of flutter of a compressor blade submitted to downstream stator potential effects. The influence of frequency is first investigated on a generic oscillating bump to identify the most unstable configuration. Introducing backward traveling pressure waves, it is then showed that aeroelastic stability of the system depends on the phase shift between the wave's source and the bump motion. Finally, feasibility of active control through backward traveling pressure waves is evaluated. The results show a high stabilizing effect even for low amplitude, opening new perspectives for the active control of choke flutter.

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Figures

Grahic Jump Location
Fig. 1

Sketch of the flow in transonic KTH-VM100 facility

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Fig. 2

Sketch of the polyurethane bump with camshaft

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Fig. 3

Mesh deformation due to bump displacement: rigid body motion is imposed close to the bump (small cells) and mesh deformation is achieved in freestream part of the flow where cells are larger, involving small relative volume variation (<1%)

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Fig. 4

Amplitude of bump deformation along streamwise axis, experimental data from Andrinopoulos et al. [14]

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Fig. 5

Steady and extremes positions of the bump in URANS computations (corresponding to a maximum section variation of 0.5%)

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Fig. 6

Structured H mesh of KTH-VM100 bi-dimensional bump

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Fig. 7

Contours of Mach number over the transonic bump and position of separation (S) and reattachment (R) points obtained from steady computation

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Fig. 8

Steady pressure coefficient along the bump: numerical results compared with experimental results of Ferria [12] and Bron [27]

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Fig. 9

Amplitude and phase of the first harmonic of unsteady pressure coefficient along the bump at kr = 0.05 (f = 100 Hz) for nonlinear URANS and LRANS computations as well as experimental results of Ferria [12]

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Fig. 10

Local aerodynamic work along the bump at kr = 0.05 (f = 100 Hz) for LRANS and nonlinear URANS computations

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Fig. 11

Damping parameter along reduced frequency for the bump motion, obtained from LRANS computations

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Fig. 12

Local aerodynamic work along the bump at kr = 0.15 (f = 300 Hz) for LRANS computation and nonlinear URANS computations

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Fig. 13

Amplitude (top) and phase (bottom) of the first harmonic of unsteady pressure coefficient along the bump for linearized and nonlinear computations at kr = 0.15 (f = 300 Hz) for an amplitude of back pressure perturbations δPs/Psoutlet = 2% and a phase shift ΔΦ = 0 deg

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Fig. 14

Amplitude (top) and phase (bottom) of the first harmonic of unsteady pressure coefficient along the bump for linearized and nonlinear computations at kr = 0.15 (f = 300 Hz) for an amplitude of back pressure perturbations δPs/Psoutlet = 2% and a phase shift ΔΦ = 90 deg

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Fig. 15

Amplitude of unsteady static pressure due to bump motion (a) and acoustic waves (b), kr = 0.15 (f = 300 Hz)

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Fig. 16

Phase of unsteady static pressure due to bump motion (a) and acoustic waves (b), kr = 0.15 (f = 300 Hz)

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Fig. 17

Local aerodynamic work extracted along the bump at kr = 0.15 (f = 300 Hz) due to bump motion and back-pressure fluctuations at different phase shifts ΔΦ

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Fig. 18

Influence of amplitude and phase shift of acoustic perturbations at kr = 0.15 (f = 300 Hz) on the added damping parameter (lines from linearized computations)

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Fig. 19

Added damping parameter and phase measured at xC = 115 mm and xR = 201 mm along phase shift of back-pressure perturbations (kr = 0.15, f = 300 Hz)

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