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

1998 ◽  
Author(s):  
Christian Paschereit ◽  
Ephraim Gutmark ◽  
Wolfgang Weisenstein
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Combustor ◽  
Thermoacoustic Instabilities ◽  
And Control

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

2018 ◽  
Vol 140 (12) ◽  
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.

Effect of Flow Pulsations in Premixed, Swirl Stabilized Combustor

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.

Development of a Durable Catalyst Axial Restraint Structure

2003 ◽  
Author(s):  
John E. Barnes
Keyword(s):  
Quality Assurance ◽  
Fluid Flow ◽  
Gas Turbine ◽  
Contact Area ◽  
Aerodynamic Performance ◽  
Gas Turbine Combustor ◽  
And Control ◽  
Foil Substrate ◽  
Quality Assurance And Control

A unique structural component known as the thermally free axial support or TFA has been developed to restrain a foil substrate catalyst within a gas turbine combustor. Designing a device for this application has been extremely challenging due to competing requirements. Functionally, this support must restrain a catalyst against significant pressure load at temperatures as high as 940°Celsius (C). Enough contact area with the catalyst must exist to avoid foil deformation while at the same time the device must not overly restrict or disturb combustion fluid flow. The aerodynamic performance of the TFA has been validated in actual turbine operation. The TFA is also expected to survive in base loaded gas turbine operation for at least 8000 hours. Long-term durability, crucial to this component since it is upstream of the turbine has been proven with significant analytical and testing efforts. Manufacturing quality assurance and control has been utilized to achieve a consistent product.

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

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

Control of thermoacoustic instabilities and emissions in an industrial-type gas-turbine combustor

1998 ◽  
Vol 27 (2) ◽  
pp. 1817-1824 ◽  
Author(s):  
Christian Oliver Paschereit ◽  
Ephraim Gutmark ◽  
Wolfgang Weisenstein
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Combustor ◽  
Thermoacoustic Instabilities

PHASE DOPPLER PARTICLE SIZING INSIDE A PRODUCTION GAS TURBINE COMBUSTOR

1994 ◽  
Vol 3 (1-6) ◽  
pp. 301-312 ◽  
Author(s):  
R. Kneer ◽  
M. Willmann ◽  
R. Zeitler ◽  
S. Wittig ◽  
K.-H. Collin
Keyword(s):  
Gas Turbine ◽  
Particle Sizing ◽  
Gas Turbine Combustor
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