| 摘要 |
A gas turbine engine (10) having a combustor (16), a turbine (18) and a transition duct (17), the transition duct (17) is located between the combustor (16) and the turbine (18) to channel hot gas (34) from the combustor (16) to the turbine (18). The transition duct (17) has an internal surface (54, 55, 56, 57) on which the hot gas (34) impinges to cause a varying temperature profile over the internal surface (54, 55, 56, 57). A thermal barrier coating (100) is located on the internal surface (54, 55, 56, 57) and comprises at least a first thermal barrier coating patch (72P) and a second thermal barrier coating patch (74P). The first thermal barrier coating patch (72P) having a first predetermined thickness (72T) located on the internal surface (54, 55, 56, 57) and within a first area (72A) subject to a higher temperature than an uncoated part of the internal surface (54, 55, 56, 57) and bounded by a first isotherm (73) of a first predetermined temperature. The second thermal barrier coating patch (74P) having a second predetermined thickness (74T) located on the internal surface (54, 55, 56, 57) and within a second area (74A) subject to a higher temperature than the uncoated part of the internal surface (54, 55, 56, 57) and bounded by a second isotherm (75) of a second predetermined temperature. The second predetermined temperature is higher than the first predetermined temperature and the second predetermined thickness (74T) is thicker than the first predetermined thickness (72T). A corresponding method of manufacturing a transition duct is also provided. |
