TURBINE VANE CLUSTER INCLUDING ENHANCED PLATFORM COOLING
A vane cluster for a gas turbine engine including an inner diameter platform and an outer diameter platform. A plurality of vanes span from the inner diameter platform to the outer diameter platform. An inbound region is defined between a first vane and a second vane of the plurality of vanes. A plenum is defined in the inner diameter platform at the inbound region. The plenum including a plurality of film cooling holes fluidly connecting the plenum to a primary flowpath. A feed hole connects the plenum to a core cooling cavity of one of the first vane and the second vane to the plenum.
1 . A vane cluster for a gas turbine engine comprising:
an inner diameter platform;
an outer diameter platform;
a plurality of vanes spanning from the inner diameter platform to the outer diameter platform;
an inbound region defined between a first vane and a second vane of the plurality of vanes;
a plenum defined in the inner diameter platform at the inbound region, the plenum including a plurality of film cooling holes fluidly connecting the plenum to a primary flowpath; and
a feed hole connecting the plenum to a core cooling cavity of one of the first vane and the second vane to the plenum.
2 . The vane cluster of claim 1 , wherein the first vane and the second vane are immediately adjacent to each other.
3 . The vane cluster of claim 1 , wherein the feed hole as a diameter in the range of 0.060-0.100 inches (1.524-25.4 mm).
4 . The vane cluster of claim 3 , wherein the feed hole has a diameter of 0.080 inches (2.032 mm).
5 . The vane cluster of claim 1 , wherein the plurality of film cooling holes comprises five to fifteen film cooling holes.
6 . The vane cluster of claim 5 , wherein the plurality of film cooling holes consists of ten film cooling holes.
7 . The vane cluster of claim 1 , wherein the plurality of film cooling holes are distributed evenly across the inner diameter platform at the plenum.
8 . The vane cluster of claim 1 , wherein the core cooling cavity is one of a plurality of core cooling cavities in the corresponding vane.
9 . The vane cluster of claim 8 , wherein the core cooling cavity is a trailing edge core cooling cavity.
10 . The vane cluster of claim 1 further comprising a baffle disposed within the corresponding vane, the baffle including a plurality of inboard to outboard cooling fluid holes configured to provide cooling fluid from an outboard compressor bleed to the core cooling cavity of the corresponding vane.
11 . The vane cluster of claim 1 , wherein the plenum comprises a void in the inner platform and a cover attached to an opening in the void.
12 . The vane cluster of claim 11 , wherein the cover is characterized by a lack of openings.
13 . The vane cluster of claim 11 , wherein the opening in the void is at a radially inward facing surface of the inner platform, relative to an arc defined by the vane cluster.
14 . The vane cluster of claim 1 , wherein the plurality of vanes consists of the first vane and the second vane.
15 . A gas turbine engine comprising:
a compressor section;
a combustor section fluidly connected to the compressor section;
a turbine section fluidly connected to the combustor section, the turbine section include a plurality of stages, at least one of said stages including a vane ring comprising multiple circumferentially adjacent vane clusters, wherein each of the vane clusters comprises
an inner diameter platform;
an outer diameter platform;
a plurality of vanes spanning from the inner diameter platform to the outer diameter platform;
an inbound region defined between a first vane and a second vane of the plurality of vanes;
a plenum defined in the inner diameter platform at the inbound region, the plenum including a plurality of film cooling holes fluidly connecting the plenum to a primary flowpath; and
a feed hole connecting the plenum to a core cooling cavity of one of the first vane and the second vane to the plenum.
16 . The gas turbine engine of claim 15 , wherein the first vane and the second vane are immediately adjacent to each other.
17 . The gas turbine engine of claim 15 , wherein the feed hole as a diameter in the range of 0.060-0.100 inches (1.524-25.4 mm).
18 . The gas turbine engine of claim 17 , wherein the feed hole has a diameter of 0.080 inches (2.032 mm).
19 . The gas turbine engine of claim 15 , wherein the plurality of film cooling holes consists of ten film cooling holes.
20 . The gas turbine engine of claim 15 , wherein the core cooling cavity is a trailing edge core cooling cavity.
21 . The gas turbine engine of claim 15 further comprising a baffle disposed within the corresponding vane, the baffle including a plurality of inboard to outboard cooling fluid holes configured to provide cooling fluid from an outboard compressor bleed to the core cooling cavity of the corresponding vane.
22 . The gas turbine engine of claim 15 , wherein the plenum comprises a void in the inner platform and a cover attached to an opening in the void.
23 . The gas turbine engine of claim 22 , wherein the cover is characterized by a lack of openings.