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

Assessment of the Indirect Combustion Noise Generated in a Transonic High-Pressure Turbine Stage

[+] Author and Article Information
Dimitrios Papadogiannis, Florent Duchaine

CFD Team,
42 Avenue Gaspard Coriolis,
Toulouse 31057, France

Gaofeng Wang, Stéphane Moreau

Département de Génie Mécanique,
University of Sherbrooke,
Sherbrooke, QC J1K 2R1, Canada

Laurent Gicquel

CFD Team,
42 Avenue Gaspard Coriolis,
Toulouse 31057, France
e-mail: laurent.gicquel@cerfacs.fr

Franck Nicoud

CNRS UMR 5149,
Université de Montpellier II,
Place Eugène Bataillon,
Montpellier 34095, France

1Present address: Safran Tech., 1 rue Geneviève Aubé, Magny-les-Hameaux 78772, France.

2Present address: Zhejiang University, School of Aeronautics and Astronautics, Hangzhou, 310027, China.

Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 20, 2015; final manuscript received August 14, 2015; published online October 21, 2015. Editor: David Wisler.

J. Eng. Gas Turbines Power 138(4), 041503 (Oct 21, 2015) (8 pages) Paper No: GTP-15-1350; doi: 10.1115/1.4031404 History: Received July 20, 2015; Revised August 14, 2015

Indirect combustion noise, generated by the acceleration and distortion of entropy waves through the turbine stages, has been shown to be the dominant noise source of gas turbines at low-frequencies and to impact the thermoacoustic behavior of the combustor. In the present work, indirect combustion noise generation is evaluated in the realistic, fully 3D transonic high-pressure turbine stage MT1 using large eddy simulations (LESs). An analysis of the basic flow and the different turbine noise generation mechanisms is performed for two configurations: one with a steady inflow and a second with a pulsed inlet, where a plane entropy wave train at a given frequency is injected before propagating across the stage generating indirect noise. The noise is evaluated through the dynamic mode decomposition (DMD) of the flow field. It is compared with the previous 2D simulations of a similar stator/rotor configuration, as well as with the compact theory of Cumpsty and Marble. Results show that the upstream propagating entropy noise is reduced due to the choked turbine nozzle guide vane. Downstream acoustic waves are found to be of similar strength to the 2D case, highlighting the potential impact of indirect combustion noise on the overall noise signature of the engine.

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Fig. 1

Mesh view of the stator at midspan (a), of the rotor at midspan (b), and at the rotor tip (c)

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Fig. 2

|∇ρ|/ρ of an instantaneous solution at midspan for the steady inflow (a) and pulsed cases (b) and at an x-normal plane near the rotor for the steady inflow case (c)

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Fig. 3

DMD spectra of temperature for the stator (left) and rotor (right) domains at midspan—steady inflow case (deg) and pulsed case (×)

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Fig. 4

DMD spectra of pressure for the stator (left) and rotor (right) domains at midspan—steady inflow case (deg) and pulsed case (×)

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Fig. 5

DMD 2 kHz mode at midspan—modulus and phase of the temperature (a) and (b) and pressure (c) and (d), respectively

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Fig. 6

DMD temperature spectra of the pulsed case with different number for different runtimes—stator (left) and rotor domain (right) at midspan

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Fig. 7

DMD pressure spectra of the pulsed case with different number different runtimes—stator (left) and rotor domain (right) at midspan

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Fig. 8

SPDMD at the stator inlet (left) and rotor outlet (right)—original DMD modes (deg) and SPDMD selected modes (×)

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Fig. 9

Comparisons of the evaluated transmission coefficients using 3D LES (×), 2D predictions (+ and •) and the compact theory (−)



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