Turbine vane for a gas turbine engine

A gas turbine engine for an aircraft propulsion system, the gas turbine engine comprising:

• a compressor section;
• and
• a turbine section, the turbine section including a turbine vane stage, the turbine vane stage including a plurality of turbine vanes, and a first turbine vane of the plurality of turbine vanes including:
• a vane body, the vane body extends between and to a leading edge and a trailing edge, the vane body extends between and to an inner diameter vane end and an outer diameter vane end, the vane body includes a first side wall, a second side wall, and a trailing edge rib, the first side wall, the second side wall, and the trailing edge rib form a cooling passage at the trailing edge, and the vane body further forms a plurality of cooling holes at the trailing edge;
• a baffle including a baffle body, the baffle body is disposed within the cooling passage, the baffle body includes a first baffle side and a second baffle side, the baffle body forms an internal baffle cavity, the internal baffle cavity is connected in fluid communication with the compressor section at the outer diameter vane end, the baffle body further forms a plurality of baffle apertures disposed at the second baffle side;
• and
• a plurality of axial divider ribs, each axial divider rib of the plurality of axial divider ribs extends between an inner end and an outer end, and to the outer end disposed at and contacting the second side wall, and the inner end disposed at and contacting the second baffle side;
• and
• the vane body, the baffle body, and the axial divider ribs form a feed cavity and one or more axial flow channels, the feed cavity is connected in fluid communication with the compressor section at the outer diameter vane end, the feed cavity is disposed between the vane body and the baffle body, the feed cavity is connected in fluid communication with the plurality of cooling holes, each axial flow channel of the one or more axial flow channels is formed by and between adjacent axial divider ribs of the plurality of axial divider ribs, each axial flow channel of the one or more axial flow channels is connected in fluid communication with the internal baffle cavity by one or more of the plurality of baffle apertures, and each axial flow channel of the one or more axial flow channels is connected in fluid communication with the plurality of cooling holes.

A turbine vane for a gas turbine engine, the turbine vane comprising:

• a vane body, the vane body extends between and to a leading edge and a trailing edge, the vane body including a span extends in a spanwise direction between and to an inner diameter vane end and an outer diameter vane end, the vane body includes a first side wall, a second side wall, and a trailing edge rib, the first side wall, the second side wall, and the trailing edge rib form a cooling passage at the trailing edge, and the vane body further forms a plurality of cooling holes at the trailing edge;
• a baffle including a baffle body, the baffle body is disposed within the cooling passage, the baffle body includes a first baffle side and a second baffle side, the baffle body forms an internal baffle cavity, the baffle body extends along the trailing edge rib between and to an inner diameter baffle end and an outer diameter baffle end, the baffle body further forms a plurality of baffle apertures, and the plurality of baffle apertures are disposed at the second baffle side;
• and
• a plurality of axial divider ribs, each axial divider rib of the plurality of axial divider ribs extends between and to a leading divider end and a trailing divider end, the leading divider end is disposed at the trailing edge rib, the trailing divider end is disposed adjacent the plurality of cooling holes, and each axial divider rib of the plurality of axial divider ribs extends between and to the second side wall and the second baffle side;
• the vane body, the baffle body, and the axial divider ribs form a feed cavity and one or more axial flow channels, the feed cavity is disposed between the vane body and the baffle body outside of the one or more axial flow channels, the feed cavity is connected in fluid communication with the plurality of cooling holes, each axial flow channel of the one or more axial flow channels is formed by and between adjacent axial divider ribs of the plurality of axial divider ribs, the one or more axial flow channels extend perpendicular to the spanwise direction from the leading divider end to the trailing divider end, each axial flow channel of the one or more axial flow channels is connected in fluid communication with the internal baffle cavity by one or more of the plurality of baffle apertures, and each axial flow channel of the one or more axial flow channels is connected in fluid communication with the plurality of cooling holes;
• wherein the plurality of axial divider ribs are disposed only within a spanwise portion of the span at the inner diameter vane end;
• and
• wherein the feed cavity is further disposed between the second side wall and the second baffle side, and the feed cavity between the second side wall and the second baffle side extends from the outer diameter vane end to the plurality of axial divider ribs.