Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

Stability and Sensitivity Analysis of Hydrodynamic Instabilities in Industrial Swirled Injection Systems

[+] Author and Article Information
Thomas L. Kaiser

Institut de Mécanique des Fluides de Toulouse,
Toulouse 31400, France
e-mail: tkaiser@imft.fr

Thierry Poinsot

Institut de Mécanique des Fluides de Toulouse,
Toulouse 31400, France

Kilian Oberleithner

Chair of Fluid Dynamics,
Technische Universität Berlin,
Berlin 10623, Germany

1Corresponding author.

Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 28, 2017; final manuscript received August 22, 2017; published online January 10, 2018. Editor: David Wisler.

J. Eng. Gas Turbines Power 140(5), 051506 (Jan 10, 2018) (10 pages) Paper No: GTP-17-1409; doi: 10.1115/1.4038283 History: Received July 28, 2017; Revised August 22, 2017

The hydrodynamic instability in an industrial, two-staged, counter-rotative, swirled injector of highly complex geometry is under investigation. Large eddy simulations (LES) show that the complicated and strongly nonparallel flow field in the injector is superimposed by a strong precessing vortex core (PVC). Mean flow fields of LES, validated by experimental particle image velocimetry (PIV) measurements, are used as input for both local and global linear stability analysis (LSA). It is shown that the origin of the instability is located at the exit plane of the primary injector. Mode shapes of both global and local LSA are compared to dynamic mode decomposition (DMD) based on LES snapshots, showing good agreement. The estimated frequencies for the instability are in good agreement with both the experiment and the simulation. Furthermore, the adjoint mode shapes retrieved by the global approach are used to find the best location for periodic forcing in order to control the PVC.

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Fig. 1

Schematic representations of wave packets in flows with different stability properties: (a) stable flow, (b) convectively unstable flow, and (c) absolutely unstable flow

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Fig. 2

Schematic sketch of the experiment: (a) primary vanes, (b) secondary vanes, (c) center body, (d) primary injector exit plane, and (e) dump plane

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Fig. 3

Experimental sound pressure level and dynamic mode decomposition (DMD) spectrum of pressure based on LES snapshots

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Fig. 4

Comparison of experimental and LES mean profiles of axial velocity, u¯x, and radial velocity, u¯r, for varying axial positions

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Fig. 5

Mean flow field inside the injector: (a) axial velocity and (b) 2D line integral convolution

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Fig. 6

PVC modes based on LES/DMD and LSA; right column: global LSA adjoint modes

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Fig. 7

Spectrum of global stability analysis

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Fig. 8

Structural sensitivity, λ: (a) global LSA and (b) local LSA

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Fig. 9

Real and imaginary part of the nondimensional frequency, ω, in the complex α-plane for the velocity profile at the exit of the primary injector

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Fig. 10

Real and imaginary part of the absolute frequency, ω0, over the axial coordinate, x

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Fig. 11

Expansion of the absolute frequency, ω0, into the complex x-plane

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Fig. 12

α+ and α as a function of the axial position



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