Patent attributes
A gas turbine engine is described which has first and second turbine vane assemblies with multiple turbine vanes within respective first and second circumferential outer shrouds. The first outer shroud has a first radially extending flange and the second outer shroud has a second radially extending flange. The radially extending first and second flanges each defining an upstream mating surface and a downstream mating surface relative to a direction of air flow through the engine in use. The downstream mating surface of the first flange mates with the upstream mating surface of the second flange. An axial retaining ring axially retains together the first and second flanges, and has an annular body extending between an upstream portion of the body abutted against the upstream mating surface of the first flange and a downstream portion of the body abutted against the downstream mating surface of the second flange.
