초록 ▼

A turbine flowpath apparatus for a gas turbine engine includes: a flowpath component exposed at least partially to a primary combustion gas flowpath of the engine, the flowpath component comprising low-ductility material; a metallic annular stationary structure surrounding the flowpath component, in

A turbine flowpath apparatus for a gas turbine engine includes: a flowpath component exposed at least partially to a primary combustion gas flowpath of the engine, the flowpath component comprising low-ductility material; a metallic annular stationary structure surrounding the flowpath component, including a bearing surface which bears against the flowpath component, so as to restrain the flowpath component from axial movement in a first direction; and a spring element disposed between the flowpath component and the stationary structure which resilient urges the flowpath component in the first direction against the bearing surface.

대표청구항 ▼

1. A turbine shroud apparatus for a gas turbine engine, comprising: a plurality of arcuate shroud segments arranged to form an annular shroud, each of the shroud segments comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner

1. A turbine shroud apparatus for a gas turbine engine, comprising: a plurality of arcuate shroud segments arranged to form an annular shroud, each of the shroud segments comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces;an annular turbine case surrounding the shroud segments, the turbine case including a bearing surface which bears against the shroud segments, so as to restrain the shroud segments from axial movement in a first direction;an annular nozzle support mounted to the turbine case and positioned on an axially opposite side of the shroud segments from the bearing surface, the nozzle support defining a radially-outward facing seal slot;a piston ring disposed in the seal slot and extending radially outward so as to contact an inner surface of the turbine case; anda spring element disposed between the nozzle support and the shroud segments which resiliently urges the shroud segments in the first direction against the bearing surface. 2. The apparatus of claim 1 wherein the spring element is an annular wave spring. 3. The apparatus of claim 1 wherein the spring element is an annular seal having a cross-sectional shape comprising a plurality of annular convolutions. 4. The apparatus of claim 1 further including an annular sealing element extending between the nozzle support and the shroud segments. 5. The apparatus of claim 1 wherein the nozzle support includes an annular rear flange disposed at an end of the body nearest the shroud segments, the rear flange including two or more annular, spaced-apart, axially-extending seal teeth which define one or more annular seal pockets adjacent the shroud segments. 6. The apparatus of claim 5 wherein the spring element is disposed within one of the seal pockets. 7. The apparatus of claim 1 wherein the shroud segment comprises a ceramic matrix composite material.