Continuous ring composite turbine shroud

A gas turbine engine turbine shroud assembly comprising:

• a composite annular shroud supported by a multi-ring shroud support assembly including at least two single piece full 360 degree rings,
• the shroud being at least partially disposed within an innermost one of the single piece full 360 degree rings,
• an axial biasing means for biasing the shroud against and in sealing engagement with an annular inwardly extending inner flange of the innermost one of the single piece full 360 degree rings,
• the single piece full 360 degree rings including metallic and concentric inner, middle, and outer rings respectively,
• the inner ring disposed radially inwardly of the middle ring,
• the middle ring disposed radially inwardly of the outer ring,
• the shroud at least partially disposed within the inner ring, and
• at least three clocking pins extending radially inwardly from the middle ring through axially extending slots in the inner ring into axially extending notches in the shroud.

A gas turbine engine turbine shroud assembly comprising:

• a composite annular shroud supported by a multi-ring shroud support assembly including at least two single piece full 360 degree rings,
• the shroud being at least partially disposed within an innermost one of the single piece full 360 degree rings,
• an axial biasing means for biasing the shroud against and in sealing engagement with an annular inwardly extending inner flange of the innermost one of the single piece full 360 degree rings,
• the single piece full 360 degree rings including metallic and concentric inner, middle, and outer rings respectively,
• the inner ring disposed radially inwardly of the middle ring,
• the middle ring disposed radially inwardly of the outer ring,
• the shroud at least partially disposed within the inner ring, and
• the single piece full 360 degree rings including metallic and concentric combination ring and middle ring,
• the combination ring including annular inner and outer ring portions and a central ring portion,
• the middle ring disposed radially inwardly of the outer ring portion, and
• the shroud at least partially disposed within the inner ring portion.

A gas turbine engine hot section comprising:

• a combustor upstream of a high pressure turbine,
• the high pressure turbine includes an annular rotatable high pressure turbine rotor,
• a row of high pressure turbine blades extending radially outwardly from the high pressure turbine rotor,
• a shroud assembly including a composite annular shroud circumscribing the turbine blades,
• the composite annular shroud comprising a full 360 degree continuous ring of composite material,
• the composite annular shroud supported by a multi-ring shroud support assembly including at least two single piece full 360 degree rings,
• the shroud being at least partially disposed within an innermost one of the single piece full 360 degree rings, and
• an axial biasing means for biasing the shroud against and in sealing engagement with an annular inwardly extending inner flange of the innermost one of the single piece full 360 degree rings.

A gas turbine engine hot section comprising:

• a combustor upstream of a high pressure turbine,
• the high pressure turbine includes an annular rotatable high pressure turbine rotor,
• a row of high pressure turbine blades extending radially outwardly from the high pressure turbine rotor,
• a shroud assembly including a composite annular shroud circumscribing the turbine blades,
• the composite annular shroud supported by a multi-ring shroud support assembly including at least two single piece full 360 degree rings,
• the shroud being at least partially disposed within an innermost one of the single piece full 360 degree rings, and
• an axial biasing means for biasing the shroud against and in sealing engagement with an annular inwardly extending inner flange of the innermost one of the single piece full 360 degree rings,
• the single piece full 360 degree rings including metallic and concentric inner, middle, and outer rings respectively,
• the inner ring disposed radially inwardly of the middle ring,
• the middle ring disposed radially inwardly of the outer ring,
• the shroud at least partially disposed within the inner ring, and
• at least three clocking pins extending radially inwardly from the middle ring through axially extending slots in the inner ring into axially extending notches in the shroud.