| 摘要 |
A tip treatment bar component 16 for use in an annular cavity surrounding a fan within a gas turbine engine comprises a longitudinal portion 30 with a laterally extending platform 32, 34 at each end. The platforms 32, 34 of adjacent bar components 16 abut each other so that a slot 28 is formed between the longitudinal portions 30 of the components 16. Projections or tangs 24, 26 extend from the platforms 32, 34 in a direction away from the longitudinal portions 30, to provide a means of locating the components 16 in a casing of an engine. The projections or tangs 24, 26 of adjacent components 16 may abut each other to from a circumferential rib. |
