Turbine engine with a nozzle having cooling features
A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. A turbine nozzle is arranged in the turbine section. Vanes of the turbine nozzle include a vane airfoil having cooling features formed in a trailing edge of the vane airfoil. Vanes of the turbine nozzle further include a baffle insert in a cavity of the vane airfoil. The baffle insert includes cooling holes.
1 . A nozzle segment for use in a turbine engine having an engine core including a combustor for generating hot combustion gases, the nozzle segment comprising:
a loading area surface configured to engage an adjacent nozzle segment, wherein the loading area surface defines a loading area (LA) between 0.000209 m 2 and 0.000256 m 2 , inclusive of endpoints;
an inner band segment configured to be oriented in an upstream direction of the engine core and having an inner band radius (IBR) defined by an arc along the inner band segment, the IBR between 0.406 m and 0.411 m, inclusive of endpoints; and
one or more vanes that extend circumferentially, individual vanes of the one or more vanes including:
an airfoil including, an outer surface defining a leading edge, a trailing edge, a suction side, and a pressure side, the airfoil further including slots extending along the trailing edge in a generally radial direction, the slots defining a total slot flow area (SFA) between 0.0000160 m 2 and 0.0000581 m 2 , inclusive of endpoints, and
a baffle insert extending within an internal cavity defined by the outer surface, the baffle insert including baffle walls and cooling holes formed in the baffle walls, the cooling holes defining a total cooling hole area (CHA) between 0.0001060 m 2 and 0.0001940 m 2 , inclusive of endpoints;
wherein:
0.112
≤
13
*
(
CHA
(
m
2
)
-
0.000103
m
2
0.000103
m
2
)
(
SPA
(
m
2
)
+
0.00004
m
2
0.00004
m
2
)
(
IBR
0.4
)
(
LA
(
m
2
)
0.001
m
2
)
≤
7.409
.
2 . The nozzle segment of claim 1 wherein the slots include a first slot having a first geometry and a second slot having a second geometry different than the first slot.
3 . The nozzle segment of claim 1 wherein the slots include generally racetrack-shaped slots.
4 . The nozzle segment of claim 1 wherein the slots include at least one slot having a circular geometry.
5 . The nozzle segment of claim 1 wherein the slots include at least one slot having a rectangular geometry.
6 . The nozzle segment of claim 1 wherein the cooling holes have a circular geometry.
7 . The nozzle segment of claim 1 wherein individual ones of the cooling holes have different geometries.