A shroud assembly for a gas turbine engine comprising: an annular mounting ring; an aft seal; a first vane; a second vane; and a continuous, annular seal body formed of ceramic matrix composite material, wherein: the seal body has an outer diameter surface; the assembly further comprises a spring assembly operative to engage the outer diameter surface of the seal body at multiple circumferential locations about the seal body such that the seal body may be urged into alignment about a longitudinal axis of the gas turbine engine; and the seal body has an upstream end, an intermediate portion and a downstream end; and characterised in that the downstream end exhibits a radial curvature, such that the downstream end extends radially outwardly from the adjacent intermediate portion of the seal body to accommodate the aft seal that is positioned between a surface forming the inner curvature radius and the annular mounting ring, such that the seal body is configured to be retained in position without the use of a dedicated carrier, the upstream end of the seal body being retained by a portion of the first vane and the downstream end of the seal body being maintained in position by the second vane. an annular mounting ring; an aft seal; a first vane; a second vane; and a continuous, annular seal body formed of ceramic matrix composite material, wherein: the seal body has an outer diameter surface; the assembly further comprises a spring assembly operative to engage the outer diameter surface of the seal body at multiple circumferential locations about the seal body such that the seal body may be urged into alignment about a longitudinal axis of the gas turbine engine; and the seal body has an upstream end, an intermediate portion and a downstream end; and characterised in that the downstream end exhibits a radial curvature, such that the downstream end extends radially outwardly from the adjacent intermediate portion of the seal body to accommodate the aft seal that is positioned between a surface forming the inner curvature radius and the annular mounting ring, such that the seal body is configured to be retained in position without the use of a dedicated carrier, the upstream end of the seal body being retained by a portion of the first vane and the downstream end of the seal body being maintained in position by the second vane. the seal body has an outer diameter surface; the assembly further comprises a spring assembly operative to engage the outer diameter surface of the seal body at multiple circumferential locations about the seal body such that the seal body may be urged into alignment about a longitudinal axis of the gas turbine engine; and the seal body has an upstream end, an intermediate portion and a downstream end; and characterised in that the downstream end exhibits a radial curvature, such that the downstream end extends radially outwardly from the adjacent intermediate portion of the seal body to accommodate the aft seal that is positioned between a surface forming the inner curvature radius and the annular mounting ring, such that the seal body is configured to be retained in position without the use of a dedicated carrier, the upstream end of the seal body being retained by a portion of the first vane and the downstream end of the seal body being maintained in position by the second vane.