Effect of thermal stress on creep lifetime for a gas turbine combustion liner
Source abstract
Abstract
Abstract The present study investigates the effect of thermal stress on the creep lifetime for a combustion liner in a gas turbine. For the calculation of thermal stress of a combustion liner, 3D-numerical analyses are performed using an FEM commercial code. Actual operating conditions and material properties are also applied for the realistic calculation. As a result, high thermal stress is locally induced in the inlet of the rib-roughened region of the whole combustion liner. That is attributed to the high temperature gradients formed from the large temperature differences between the hot spots and the surrounding low temperature regions. The result is in a good agreement with the actually damaged combustion liner. Moreover, the hot gas side of the inlet of the rib-roughened region appeared vulnerable to creep and the minimum creep lifetime is estimated to be approximately 26,900 h.
Source: openaire · Quality: candidate unverified · Source record ↗
Research context
OpenAlex topics: Combustion and flame dynamics · Turbomachinery Performance and Optimization · Heat Transfer Mechanisms
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
References (19)
Show source-provided references
1. Film cooling10.1016/S0065-2717(08)70020-0 ↗
2. Lakshminarayana · 1996
3. Han · 2012
4. Jet-impingement heat transfer in gas turbine systems10.1111/j.1749-6632.2001.tb05849.x ↗
5. Detailed measurement of heat/mass transfer with continuous and multiple V-shaped ribs in rectangular channel10.1016/j.energy.2009.07.011 ↗
6. Optimal design of transverse ribs in tubes for thermal performance enhancement10.1016/j.energy.2010.02.020 ↗
7. Local heat transfer and thermal performance on periodically dimple-protrusion patterned walls for compact heat exchangers10.1016/j.energy.2010.07.022 ↗
8. Measurement of local heat/mass transfer coefficients on a dimple using naphthalene sublimation10.1016/j.ijheatmasstransfer.2010.10.036 ↗
9. Effect of jet direction on heat/mass transfer of rotating impingement jet10.1016/j.applthermaleng.2009.02.014 ↗
10. Failure analysis in after shell section of gas turbine combustion liner under base-load operation10.1016/j.engfailanal.2009.10.018 ↗
11. Analysis of conjugated heat transfer, stress and failure in a gas turbine blade with circular cooling passages10.1016/j.engfailanal.2011.03.002 ↗
12. Yun N, Jeon YH, Kim KM, Lee DH, Cho HH. Thermal and creep analysis in a gas turbine combustion liner. In: Proceedings of the 4th IASME/WSEAS international conference on energy & environment, World Scientific and Engineering Academy and Society (WSEAS); 2009. p. 315–20.
13. Sivaramakrishna G, Muthuveerappan N, Shankar V. ISABE-2001-1089 Combustor geometry optimization studies using CFD technique. Ahsiracfésmggv ISABE; 2001. p. 62.
14. Combined effect of slot injection, effusion array and dilution hole on the heat transfer coefficient of a real combustor liner: part 1—Experimental analysis
15. Experimental and numerical investigation of convective heat transfer in a gas turbine can combustor10.1115/1.4001173 ↗
16. Gas turbine combustor liner life assessment using a combined fluid/structural approach10.1115/1.2360603 ↗
17. Thermo-mechanical life prediction for material lifetime improvement of an internal cooling system in a combustion liner10.1016/j.energy.2010.12.016 ↗
18. Special metals · 2007
19. Conjugated heat transfer and temperature distributions in a gas turbine combustion liner under base-load operation10.1007/s12206-010-0625-8 ↗