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TECHNICAL PAPERS: Gas Turbines: Combustion and Fuels

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

[+] Author and Article Information
T. Tinga

 National Aerospace Laboratory NLR, Anthony Fokkerweg 2, 1059 CM, Amsterdam, The Netherlandstinga@nlr.nl

J. F. van Kampen, B. de Jager, J. B. Kok

Thermal Engineering, Twente University, P. O. Box 217, 7500 AE Enschede, The Netherlands

J. Eng. Gas Turbines Power 129(1), 69-79 (Jun 28, 2006) (11 pages) doi:10.1115/1.2360603 History: Received January 05, 2006; Revised June 28, 2006

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.

Copyright © 2007 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Cracks in inner and outer liner of combustor

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Figure 2

Combustor liner with 1∕16th section that is modeled indicated by dotted line

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Figure 3

Geometry of CFD (left) and FE models (right)

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Figure 4

Inlets and outlet in CFD geometry

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Figure 5

Schematic representation of heat flows in combustor cross section

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Figure 6

Creep strain extrapolation using the average strain rate (1) and the tangent strain rate (2)

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Figure 7

Schematic representation of mission analysis method

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Figure 8

Comparison of CFD calculated and interpolated Tgas and h

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Figure 9

Comparison of results based on real (left) and interpolated temperature distribution on outer liner

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Figure 10

Variation of power setting (PLA) and flight altitude during analyzed mission

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Figure 11

Vector plot of the velocity field in a radial plane of the combustor

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Figure 12

Contour plot of the temperature field in a radial plane of the combustor at condition 1

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Figure 13

(a) Temperature (in °C) and (b) tangential stress (in Pa) distribution at operating condition 6

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Figure 14

Location of nodes used for plotting the temperature and stress history

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Figure 15

Temperature and tangential stress variation on liner during a mission for the locations shown in Fig. 1

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Figure 16

Creep life (in hours) and fatigue life (in number of flights) distribution in the liner

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Figure 17

Distribution of (a) circumferential and (b) max. principal stress on the final louvers of the inner liner

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Figure 18

The temperature and species profiles for a premixed flame at a pressure of 1 and 18atm

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Figure 19

Composed species concentration and source term (reaction rate)

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Figure 20

CSP source term (reaction rate) fitted with Gaussian function

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