Cooling nozzle vanes of a turbine engine
An assembly for a turbine engine includes a nozzle structure, a septum and a plurality of cooling vanes. The nozzle structure includes a first platform, a second platform and a plurality of nozzle vanes arranged circumferentially about an axis. The septum axially and circumferentially overlaps the first platform with a cooling cavity formed by and radially between the septum and the first platform. The septum includes a plurality of cooling apertures aligned with the nozzle vanes. Each of the cooling apertures extends radially through the septum to the cooling cavity. The cooling cavity includes a cavity outlet fluidly coupled to a flowpath. The cooling vanes are arranged circumferentially about the axis and project from the first platform into the cooling cavity. The cooling vanes are located between the cooling apertures and the cavity outlet along the cooling cavity.
1. An assembly for a turbine engine, comprising:
a nozzle structure including a first platform, a second platform and a plurality of nozzle vanes arranged circumferentially about an axis, the first platform forming a first boundary of a flowpath through the nozzle structure, the second platform forming a second boundary of the flowpath, and the plurality of nozzle vanes extending radially across the flowpath from the first platform to the second platform;
a septum axially and circumferentially overlapping the first platform with a cooling cavity formed by and radially between the septum and the first platform, the septum comprising a plurality of cooling apertures aligned with the plurality of nozzle vanes, each of the plurality of cooling apertures extending radially through the septum to the cooling cavity, and the cooling cavity comprising a cavity outlet fluidly coupled to the flowpath; and
a plurality of cooling vanes arranged circumferentially about the axis and projecting from the first platform into the cooling cavity, the plurality of cooling vanes located between the plurality of cooling apertures and the cavity outlet along the cooling cavity.
2. The assembly of claim 1 , wherein the cavity outlet is located upstream of the first platform along the flowpath.
3. The assembly of claim 1 , wherein each of the plurality of cooling apertures is configured to direct a stream of air across the cooling cavity against the first platform.
4. The assembly of claim 1 , wherein the plurality of cooling apertures are axially aligned along the axis and arranged circumferentially about the axis in an annular array.
5. The assembly of claim 1 , wherein
the plurality of nozzle vanes comprise a first nozzle vane; and
the plurality of cooling apertures comprises a first cooling aperture, and the first cooling aperture is axially and circumferentially aligned with the first nozzle vane.
6. The assembly of claim 1 , wherein
the plurality of nozzle vanes include a first nozzle vane and a second nozzle vane that circumferentially neighbors the first nozzle vane with a channel formed by and extending circumferentially between the first nozzle vane and the second nozzle vane;
a first set of the plurality of cooling apertures are axially and circumferentially aligned with the first nozzle vane;
a second set of the plurality of cooling apertures are axially and circumferentially aligned with the second nozzle vane; and
a section of the septum is non-perforated, the section of the septum extends circumferentially between the first set of the plurality of cooling apertures and the second set of the plurality of cooling apertures, and the section of septum axially overlaps at least a major portion of the channel.
7. The assembly of claim 1 , wherein
the plurality of nozzle vanes comprise a first nozzle vane, and the first nozzle vane extends longitudinally between a leading edge and a trailing edge; and
a first set of the plurality of cooling apertures are axially and circumferentially aligned with the first nozzle vane, and a density of cooling apertures in the first set of the plurality of cooling apertures is greater in an area aligned with the trailing edge than in an area aligned with the leading edge.
8. The assembly of claim 1 , wherein
the plurality of cooling vanes comprise a first cooling vane; and
the first cooling vane projects radially and/or axially from the first platform to an unsupported distal end of the first cooling vane.
9. The assembly of claim 1 , wherein the plurality of cooling vanes are axially offset from the plurality of nozzle vanes.
10. The assembly of claim 1 , wherein
the plurality of cooling vanes comprise a first cooling vane; and
the first cooling vane comprises a cambered cooling vane.
11. The assembly of claim 1 , wherein
the plurality of nozzle vanes are configured to swirl combustion products in a circumferential direction about the axis; and
the plurality of cooling vanes are configured to swirl air in the circumferential direction about the axis.
12. The assembly of claim 1 , further comprising:
a baffle axially and circumferentially overlapping the septum with a feed cavity formed by and radially between the baffle and the septum; and
the septum radially between the baffle and the first platform with the plurality of cooling apertures fluidly coupling the feed cavity to the cooling cavity.
13. The assembly of claim 12 , further comprising:
a turbine wall; and
an intermediate structure extending between a downstream end of the first platform and an upstream end of the turbine wall;
the septum extending axially to the intermediate structure; and
the baffle extending axially to the intermediate structure with one or more ports formed through the baffle adjacent the intermediate structure.
14. The assembly of claim 1 , further comprising:
a combustor wall radially between and bordering a plenum and a combustion chamber;
a downstream end of the combustor wall axially spaced from an upstream end of the first platform to form the cavity outlet.
15. The assembly of claim 1 , further comprising:
a combustor disposed in a plenum and comprising a combustion chamber;
the nozzle structure arranged at an outlet from the combustion chamber; and
the plurality of cooling aperture configured to receive air from the plenum to direct across the cooling cavity onto the first platform.
16. The assembly of claim 1 , further comprising a monolithic body that includes the nozzle structure, the septum and the plurality of cooling vanes.
17. The assembly of claim 1 , wherein
the first platform is an inner platform which circumscribes the septum and the plurality of cooling vanes; and
the second platform is an outer platform which circumscribes the inner platform.
18. An assembly for a turbine engine, comprising:
a combustor arranged in a plenum and comprising a combustion chamber;
a nozzle structure arranged at an outlet from the combustion chamber, the nozzle structure including a first platform, a second platform and a plurality of nozzle vanes arranged circumferentially about an axis, and the plurality of nozzle vanes extending radially across a flowpath from the first platform to the second platform;
a septum extending axially and circumferentially along the first platform with a cooling cavity formed by and radially between the septum and the first platform, the septum comprising a plurality of cooling apertures aligned with the plurality of nozzle vanes, and each of the plurality of cooling apertures extending radially through the septum from a feed cavity to the cooling cavity; and
a baffle extending axially and circumferentially along the septum with the feed cavity formed by and radially between the baffle and the septum, the baffle comprising a plurality of ports extending radially through the baffle from the plenum to the feed cavity.
19. The assembly of claim 18 , further comprising a plurality of cooling elements connected to the first platform and projecting partially into the cooling cavity.
20. An assembly for a turbine engine, comprising:
a combustor arranged in a plenum and comprising a combustion chamber;
a nozzle structure arranged at an outlet from the combustion chamber, the nozzle structure including a first platform, a second platform and a plurality of nozzle vanes arranged circumferentially about an axis, the plurality of nozzle vanes extending radially across a flowpath from the first platform to the second platform, the plurality of nozzle vanes comprising a first nozzle vane, and the first nozzle vane extending longitudinally between a leading edge and a trailing edge; and
a septum extending axially and circumferentially along the first platform with a cooling cavity formed by and radially between the septum and the first platform, the septum comprising a plurality of cooling apertures extending radially through the septum from a feed cavity to the cooling cavity;
a first set of the plurality of cooling apertures are axially and circumferentially aligned with the first nozzle vane, wherein a density of cooling apertures in the first set of the plurality of cooling apertures is greater in an area aligned with the trailing edge than in an area aligned with the leading edge.