Hybrid Method for The Prediction of Thermo-Acoustic Waves in a Gas Turbine Combustor

2007 ◽  
Author(s):  
Robert-Zoltan Szasz ◽  
Christophe Duwig ◽  
Laszlo Fuchs
Keyword(s):  
Gas Turbine ◽  
Hybrid Method ◽  
Acoustic Waves ◽  
Gas Turbine Combustor

Predicting Thermoacoustic Instability in an Industrial Gas Turbine Combustor: Combining a Low Order Network Model With Flame LES

2017 ◽  
Author(s):  
Y. Xia ◽  
A. S. Morgans ◽  
W. P. Jones ◽  
J. Rogerson ◽  
G. Bulat ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Acoustic Waves ◽  
Gas Turbine Combustor ◽  
Network Modelling ◽  
Weakly Nonlinear ◽  
Thermoacoustic Instability ◽  
Reduced Chemistry ◽  
Flame Describing Function ◽  
Industrial Gas Turbine ◽  
Low Order

The thermoacoustic modes of a full scale industrial gas turbine combustor have been predicted numerically. The predictive approach combines low order network modelling of the acoustic waves in a simplified geometry, with a weakly nonlinear flame describing function, obtained from incompressible large eddy simulations of the flame region under upstream forced velocity perturbations, incorporating reduced chemistry mechanisms. Two incompressible solvers, each employing different numbers of reduced chemistry mechanism steps, are used to simulate the turbulent reacting flowfield to predict the flame describing functions. The predictions differ slightly between reduced chemistry approximations, indicating the need for more involved chemistry. These are then incorporated into a low order thermoacoustic solver to predict thermoacoustic modes. For the combustor operating at two different pressures, most thermoacoustic modes are predicted to be stable, in agreement with the experiments. The predicted modal frequencies are in good agreement with the measurements, although some mismatches in the predicted modal growth rates and hence modal stabilities are observed. Overall, these findings lend confidence in this coupled approach for real industrial gas turbine combustors.

Absorption of Normal-Incidence Acoustic Waves by Double Perforated Liners of Industrial Gas Turbine Combustors

2012 ◽  
Author(s):  
Charith Jayatunga ◽  
Qin Qin ◽  
Victoria Sanderson ◽  
Phil Rubini ◽  
Danning You ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Parametric Study ◽  
Acoustic Waves ◽  
Rigid Wall ◽  
Gas Turbine Combustor ◽  
Air Cavity ◽  
Impedance Tube ◽  
Impedance Model ◽  
Incident Plane ◽  
Absorption Characteristics

Perforated liners consist of sheet metal perforated with multiple holes with diameters of magnitude in the order of millimeters and regular spacing, backed by an air cavity in front of a rigid wall. This type of liner is very effective at absorbing sound and is used in many applications. At the resonance frequency, the liner shifts the phase of the incident wave by 180° thus providing damping through wave cancellation. The perforations in the liner convert acoustic energy into flow energy through vortex shedding at the rims of the liner apertures. Applied to gas turbine combustors they can attenuate thermoacoustic instabilities and as such significantly improve the reliability of the gas turbine with an additional benefit to the emissions. The Siemens SGT-100 to 400 engines exploit this technology in their DLE combustion system in a configuration of two concentric liners separated by an air cavity with the rear liner acting as the rigid wall in the conventional setting. In this paper the evaluation of double perforated liners in the absorption of normal-incident plane acoustic waves in an impedance tube and in a gas turbine combustor environment is investigated. A one-dimensional impedance model that embodies the electro-acoustic analogy was used to predict the absorption characteristics of the double perforated liner. The model was validated by comparing the predictions with experimental data obtained from the impedance tube, with excellent agreement. With the confidence in the equations of the model in predicting the acoustic behavior, the model was then applied to predict the damping performance under realistic gas turbine combustor operating conditions. The prediction also shows two distinct peaks in the absorption characteristics of a double-liner. Geometric parameters such as hole diameters & thicknesses of the two liners, gap between the liners and the overall pressure drop across the liners have been considered for the predictions. A parametric study of these parameters carried out using the ISIGHT software with design investigation tools identified the order of importance of the parameters considered for sound absorption. The work reported in this paper has successfully validated an impedance model in the prediction of double perforated liners in the absorption of normal-incident plane acoustic waves. Based on the parametric study carried out design guidelines are given for designing a double perforated liner for maximum absorption of normal incident acoustic waves.

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

A distributed vaporization time-lag model for gas turbine combustor dynamics

1992 ◽  
Author(s):  
JAYESH MEHTA ◽  
P. MUNGUR ◽  
W. DODDS ◽  
L. DODGE
Keyword(s):  
Gas Turbine ◽  
Time Lag ◽  
Gas Turbine Combustor ◽  
Lag Model

Correction: Lean blow-out (LBO) computations in a gas turbine combustor

2018 ◽  
Author(s):  
Veeraraghava Raju Hasti ◽  
Prithwish Kundu ◽  
Gaurav Kumar ◽  
Scott A. Drennan ◽  
Sibendu Som ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Combustor

Combustion Dynamics Behavior in a Single-Element Lean Direct Injection (LDI) Gas Turbine Combustor

2014 ◽  
Author(s):  
Cheng Huang ◽  
Rohan Gejji ◽  
William Anderson ◽  
Changjin Yoon ◽  
Venkateswaran Sankaran
Keyword(s):  
Gas Turbine ◽  
Direct Injection ◽  
Single Element ◽  
Gas Turbine Combustor ◽  
Combustion Dynamics ◽  
Lean Direct Injection

Numerical Investigation of the Pressure Effect on the NOx Formation in a Lean-Premixed Gas Turbine Combustor

2021 ◽  
Vol 35 (8) ◽  
pp. 6776-6784
Author(s):  
Truc Huu Nguyen ◽  
Jungkyu Park ◽  
Changhun Sin ◽  
Seungchai Jung ◽  
Shaun Kim
Keyword(s):  
Numerical Investigation ◽  
Gas Turbine ◽  
Pressure Effect ◽  
Gas Turbine Combustor ◽  
Nox Formation ◽  
Lean Premixed
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