Gas Turbine Combustor Liner Life Assessment Using a Combined Fluid/Structural Approach

Abstract

A life assessment was performed on a fighter jet engine annular combustor liner, using a combined fluid/structural approach. Computational fluid dynamics analyses were performed to obtain the thermal loading of the combustor liner and finite element analyses were done to calculate the temperature and stress/strain distribution in the liner during several operating conditions. A method was developed to analyze a complete flight with limited computational effort. Finally, the creep and fatigue life for a measured flight were calculated and the results were compared to field experience data. The absolute number of cycles to crack initiation appeared hard to predict, but the location and direction of cracking could be correlated well with field data.

On the Effect of Hot Isostatic Pressing on the Creep Life of a Single Crystal Superalloys

“…Design procedures for superalloy components prescribe small allowable maximum strains < 2%. [23] 3. 4…”

Effect of thermal stress on creep lifetime for a gas turbine combustion liner

“…Likewise, for the combustion systems, there are also numerous studies such as combustion mechanism, combustion gas flow, and heat transfer in combustors [13][14][15]. There have been some efforts to predict failure and lifetime in combustors, but only for the local part of component or segments in archival journal papers [16,17].…”

Conjugated heat transfer and temperature distributions in a gas turbine combustion liner under base-load operation

“…Many researchers [8][9][10][11][12][13][14][15] have performed CFD prediction including combustion, fluid flow, and heat transfer in the gas turbine combustors. In addition, Tinga et al [16] predicted lifecycle in a gas turbine blade and Yun et al [17,18] predicted lifetime in a gas turbine combustion liner using the material temperature and thermal stresses. Various technical papers or gas turbine analysis have been published using numerical methods.…”