| 摘要 |
An aircraft gas turbine axisymmetric vectoring nozzle has an interface ring centered about a nozzle, a vectoring ring disposed radially inwardly of and apart from the interface ring, and a bearing radially disposed between the vectoring ring and the interface ring. The bearing may be a sliding bearing having a sliding interface between the vectoring ring and the interface ring and the sliding interface is spherical. The bearing may be constructed of sliding bearing segments having sliding interfaces between the vectoring ring and the interface ring and the sliding interfaces are spherical. Each of the bearing segments includes an outer sliding element attached to the interface ring, an inner sliding element attached to the vectoring ring, and spherically curved outer and inner sliding surfaces on the outer and inner sliding elements respectively wherein the spherically curved outer and inner sliding surfaces define the sliding interfaces between the vectoring ring and the interface ring. At least one of the outer sliding elements is circumferentially disposed and trapped between circumferentially spaced apart rails disposed on a corresponding one of the inner sliding elements. A plurality of interface ring support guides are disposed radially inwardly of and in sliding support relationship with the interface ring and located axially forward of the vectoring ring.
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