Initial Growth and Development of Thermoacoustic Instabilities in a Gas Turbine Combustor

2018 AIAA Aerospace Sciences Meeting ◽

10.2514/6.2018-0676 ◽

2018 ◽

Author(s):

Timothy M. Wabel ◽

Mitchell Passarelli ◽

J.D. M. Cirtwill ◽

Pankaj Saini ◽

Adam M. Steinberg ◽

...

Keyword(s):

Gas Turbine ◽

Growth And Development ◽

Initial Growth ◽

Gas Turbine Combustor ◽

Thermoacoustic Instabilities

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Design of Acoustic Liner in Small Gas Turbine Combustor Using One-Dimensional Impedance Models

Journal of Engineering for Gas Turbines and Power ◽

10.1115/1.4040765 ◽

2018 ◽

Vol 140 (12) ◽

Cited By ~ 1

Author(s):

Daesik Kim ◽

Seungchai Jung ◽

Heeho Park

Keyword(s):

Gas Turbine ◽

Side Wall ◽

Acoustic Energy ◽

Gas Turbine Combustor ◽

Design Guideline ◽

Acoustic Damping ◽

Thermoacoustic Instabilities ◽

Acoustic Dissipation ◽

Acoustic Liner ◽

Bias Flow

The side-wall cooling liner in a gas turbine combustor serves main purposes—heat transfer and emission control. Additionally, it functions as a passive damper to attenuate thermoacoustic instabilities. The perforations in the liner mainly convert acoustic energy into kinetic energy through vortex shedding at the orifice rims. In the previous decades, several analytical and semi-empirical models have been proposed to predict the acoustic damping of the perforated liner. In the current study, a few of the models are considered to embody the transfer matrix method (TMM) for analyzing the acoustic dissipation in a concentric tube resonator with a perforated element and validated against experimental data in the literature. All models are shown to quantitatively appropriately predict the acoustic behavior under high bias flow velocity conditions. Then, the models are applied to maximize the damping performance in a realistic gas turbine combustor, which is under development. It is found that the ratio of the bias flow Mach number to the porosity can be used as a design guideline in choosing the optimal combination of the number and diameter of perforations in terms of acoustic damping.

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Structure and Control of Thermoacoustic Instabilities in a Gas-turbine Combustor

Combustion Science and Technology ◽

10.1080/00102209808952069 ◽

1998 ◽

Vol 138 (1-6) ◽

pp. 213-232 ◽

Cited By ~ 59

Author(s):

C.O. PASCHEREIT ◽

E. GUTMARK ◽

W. WEISENSTEIN

Keyword(s):

Gas Turbine ◽

Gas Turbine Combustor ◽

Thermoacoustic Instabilities ◽

And Control

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Structure and control of thermoacoustic instabilities in a gas-turbine combustor

10.2514/6.1998-1067 ◽

1998 ◽

Cited By ~ 7

Author(s):

Christian Paschereit ◽

Ephraim Gutmark ◽

Wolfgang Weisenstein

Keyword(s):

Gas Turbine ◽

Gas Turbine Combustor ◽

Thermoacoustic Instabilities ◽

And Control

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Effect of Flow Pulsations in Premixed, Swirl Stabilized Combustor

ASME 2014 Gas Turbine India Conference ◽

10.1115/gtindia2014-8246 ◽

2014 ◽

Author(s):

Aayush K. Sharma ◽

Uddalok Sen ◽

Pallab Sinha Mahapatra ◽

Swarnendu Sen ◽

Achintya Mukhopadhyay

Keyword(s):

Numerical Model ◽

Gas Turbine ◽

Formation Rate ◽

Combustion Process ◽

Product Formation ◽

Primary Objective ◽

Gas Turbine Combustor ◽

Ansys Fluent ◽

Thermoacoustic Instabilities ◽

Product Formation Rate

In the present work, a numerical model has been developed using ANSYS Fluent 14.5 to simulate the combustion phenomenon in a partially premixed, swirl-stabilized, LPG-fueled gas turbine combustor. In a practical gas turbine combustor, pulsations in the flow at the air side cannot be avoided which can lead to thermoacoustic instabilities. The primary objective of the study is to numerically analyze the effect of such pulsations on the fluid flow and combustion process inside the combustor. Different parameters like static temperature, progress variable and product formation rate are compared at the outlet plane of the combustor. The effect of change in the parameters like amplitude and frequency of the sinusoidal air flow input has also been investigated in the present study. It is observed that the solution changes from periodic to quasi-periodic at a higher amplitude condition. The numerical model was qualitatively validated against experiments performed on a laboratory-scale premixed, swirl-stabilized, gas turbine combustor.

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