Segmented turbine flowpath assembly

A gas turbine annular flowpath assembly located about a longitudinal centerline axis for channeling combustion gases comprising:

• an annular outer casing;
• a plurality of circumferentially spaced apart, radially extending airfoils each having a radially outer band extending axially and circumferentially therefrom and a radially inner band extending axially and circumferentially thereform;
• a plurality of flowpath radially outer panels, each forming a circumferential segment of said annular flowpath assembly and having a radially outwardly extending member fixedly joined to said outer casing, each outer panel extending circumferentially between and circumferentially overlapping adjacent ones of said outer bands radially thereover;
• a plurality of flowpath radially inner panels, each forming a circumferential segment of said annular flowpath assembly and, each inner panel extending circumferentially between and circumferentially overlapping adjacent ones of said inner bands radially thereover;
• means for joining together said outer bands and panels, and said inner bands and panels, respectively, at said respective overlaps thereof for restraining radial movement while allowing circumferential movement therebetween;
• and
• said outer and inner panels being disposed in pairs between adjacent ones of said airfoils to define a flow duct therebetween for channeling said combustion gases, said flow duct being supported and suspended from said outer casing by said outer panel.