Analysis of the combustion instability of a model gas turbine combustor by the transfer matrix method

2009 ◽  
Vol 23 (6) ◽  
pp. 1602-1612 ◽  
Author(s):  
Dong Jin Cha ◽  
Jay H. Kim ◽  
Yong Jin Joo
Keyword(s):  
Gas Turbine ◽  
Transfer Matrix ◽  
Transfer Matrix Method ◽  
Matrix Method ◽  
Combustion Instability ◽  
Gas Turbine Combustor ◽  
Model Gas Turbine Combustor

COMBUSTION INSTABILITY ANALYSIS OF A MODEL GAS TURBINE COMBUSTOR WITH CLOSED ACOUSTIC BOUNDARIES AT BOTH ENDS

2011 ◽  
Vol 19 (03) ◽  
pp. 231-238
Author(s):  
DONG-JIN CHA
Keyword(s):  
Gas Turbine ◽  
Transfer Matrix ◽  
Transfer Matrix Method ◽  
Matrix Method ◽  
Combustion Instability ◽  
Combustion Process ◽  
Side Branch ◽  
Combustion System ◽  
Efficient Operation ◽  
Gas Turbine Combustors

Combustion instability is a major issue in designing gas turbine combustors for an efficient operation with low emissions. Combustion instability is induced by the interaction of the unsteady heat release of the combustion process and changes in the acoustic pressure in the combustion chamber. In an effort to develop a technique to predict self-excited combustion instability of gas turbine combustors, a new stability analysis method based on the transfer matrix method was developed. The method views the combustion system as a one-dimensional acoustic system with a side branch and describes the heat source as the input to the system. This approach makes it possible to use not only the advantages of the transfer matrix method but also well established classic control theories. The approach is applied to a gas turbine combustion system, which shows the validity and effectiveness of the approach.

The Effect of Fuel Composition on Combustion Instability Mode Occurrence in a Model Gas Turbine Combustor

2015 ◽  
Author(s):  
Jisu Yoon ◽  
Seongpil Joo ◽  
Min Chul Lee ◽  
Jeongjin Kim ◽  
Jaeyo Oh ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Alternative Fuels ◽  
Combustion Instability ◽  
Longitudinal Mode ◽  
Fuel Composition ◽  
Instability Mode ◽  
Gas Turbine Combustor ◽  
Global Issues ◽  
Model Gas Turbine Combustor ◽  
Instability Frequency

Recently, energy resource depletion and unstable energy prices have become global issues. Worldwide pressure to secure and make more gas and oil available to support global power needs has increased. To meet these needs, alternative fuels composed of various types of fuels have received attention, including biomass, dimethyl ether (DME), and low rank coal. For this reason, the fuel flexibility of the combustion system becomes more important. In this study, H2 and CH4 were selected as the main fuel composition variables and the OH-chemiluminescence measurement technique was also applied. This experimental study was conducted under equivalence ratio and fuel composition variations with a model gas turbine combustor to examine the relation between combustion instability and fuel composition. The combustion instability peak occurs in the H2/CH4 50:50 composed fuel and the combustion instability frequency shifted to higher harmonic of longitudinal mode based on the H2 concentration of the fuel. Based on instability mode and flame length calculation, the effect of the convection time during the instability frequency increasing phenomenon was found in a partially premixed gas turbine combustor. The time-lag analysis showed that the short convection time in a high H2 concentration fuel affects the feedback loop period reduction and, in these conditions, high harmonics of longitudinal mode instability occurs. This fundamental study on combustion instability frequency shifting characteristics was conducted for H2/CH4 composed fuel and the results contribute key information for the conceptual design of a fuel flexible gas turbine and its optimum operation conditions.

Effect of fuel–air mixture velocity on combustion instability of a model gas turbine combustor

2013 ◽  
Vol 54 (1) ◽  
pp. 92-101 ◽  
Author(s):  
Jisu Yoon ◽  
Min-Ki Kim ◽  
Jeongjae Hwang ◽  
Jongguen Lee ◽  
Youngbin Yoon
Keyword(s):  
Gas Turbine ◽  
Combustion Instability ◽  
Gas Turbine Combustor ◽  
Model Gas Turbine Combustor ◽  
Mixture Velocity

An Investigation on Dynamic Characteristics of a Gas Turbine Rotor Using an Improved Transfer Matrix Method

2013 ◽  
Vol 135 (12) ◽  
Author(s):  
Cheng Meng ◽  
Ming Su ◽  
Shaobo Wang
Keyword(s):  
Gas Turbine ◽  
Dynamic Model ◽  
Transfer Matrix ◽  
Dynamic Characteristics ◽  
Transfer Matrix Method ◽  
Matrix Method ◽  
Mode Shapes ◽  
Correction Coefficient ◽  
Critical Speeds ◽  
Contact Effects

This paper presents an investigation on dynamic characteristics of a rod-fastened rotor. Based on the framework of a traditional Riccati transfer matrix method (TMM), an improved Riccati TMM considering contact effects brought by a face tooth is developed. A correction coefficient for equivalent stiffness imported from a three-dimensional (3D) finite element contact case analysis is defined to evaluate the contact effects, and then the dynamic model of the rod-fastened rotor including bearing support is established. A computer program is further developed to obtain the dynamic characteristics such as critical speeds of lateral vibration, mode shapes, and an unbalance response. The improved TMM is applied to investigate the dynamic characteristics of a real central tie rod rotor of the class-F gas turbine for verification of its effectiveness, and the calculated critical speeds are in good agreement with test measurement results, implying that the method is accurate and the dynamic model is reliable. This approach can also be applied to analyze other combined rotors with a homogeneous structure.

Sign in / Sign up

Export Citation Format

Share Document