초록

A nozzle segment for a gas turbine engine includes a flange which extends from a vane platform, the flange includes a hollow cavity.

대표청구항 ▼

1. A nozzle segment for a gas turbine engine comprising: a vane platform;a flange which extends from said vane platform, said flange includes a hollow cavity and a stiffening feature within said hollow cavity. 2. The nozzle segment as recited in claim 1, wherein said stiffening feature is a rib. 3.

1. A nozzle segment for a gas turbine engine comprising: a vane platform;a flange which extends from said vane platform, said flange includes a hollow cavity and a stiffening feature within said hollow cavity. 2. The nozzle segment as recited in claim 1, wherein said stiffening feature is a rib. 3. The nozzle segment as recited in claim 1, wherein said stiffening feature is a post. 4. The nozzle segment as recited in claim 1, wherein said flange defines a first seal surface. 5. The nozzle segment as recited in claim 4, wherein said flange defines a second seal surface. 6. The nozzle segment as recited in claim 4, wherein said flange is an aft flange. 7. The nozzle segment as recited in claim 1, wherein said vane platform is an outer vane platform. 8. The nozzle segment as recited in claim 1, further comprising at least one purge opening in communication with said hollow cavity. 9. The nozzle segment as recited in claim 8, wherein said at least one purge opening extends through a first seal surface. 10. A nozzle segment for a gas turbine engine comprising: an outer vane platform;an inner vane platform;a vane which extends between said outer vane platform and said inner vane platform;a flange which extends from said outer vane platform, said flange includes a hollow cavity anda stiffening feature within said hollow cavity. 11. The nozzle segment as recited in claim 10, wherein said stiffening feature is a rib. 12. The nozzle segment as recited in claim 10, wherein said stiffening feature is a post. 13. The nozzle segment as recited in claim 10, wherein said flange defines a first seal surface and a second seal surface, said hollow cavity at least partially between said first seal surface and said second seal surface. 14. The nozzle segment as recited in claim 10, wherein said hollow cavity defines an opening through a radial face. 15. The nozzle segment as recited in claim 10, wherein said hollow cavity defines an opening through a forward seal surface. 16. A nozzle segment for a gas turbine engine comprising: an outer vane platform;an inner vane platform;a vane which extends between said outer vane platform and said inner vane platform; anda flange which extends from said outer vane platform, said flange includes a hollow cavity, wherein said hollow cavity defines an opening through a forward seal surface. 17. A nozzle segment for a gas turbine engine comprising: a vane platform; a flange which extends from said vane platform, said flange includes a hollow cavity and at least one purge opening in communication with said hollow cavity, wherein said at least one purge opening extends through a first seal surface.