Airfoil turn channel with split and flow-through
An airfoil includes an airfoil wall that defines a leading end, a trailing end, a first side, and a second side. Radially-extending ribs partition the interior cavity of the airfoil into first and second cooling channels and a radial cooling passage that is situated between the first and second cooling channels. The cooling channels extend to respective first and second channel ends. A turn channel connects the first and second channel ends. The turn channel splits at the first channel end into first and second channel legs such that there is a region between the first and second channel legs. The channels legs merge at the second channel end. The radial cooling passage extends through the region between the first and second channel legs.
1. An airfoil comprising:
an airfoil wall defining a leading end, a trailing end, a first side, and a second side, the airfoil wall circumscribing an interior cavity; and
radially-extending ribs that partition the interior cavity into first and second cooling channels and a radial cooling passage situated between the first and second cooling channels, the first and second cooling channels extending to respective first and second channel ends; and
a turn channel connecting the first and second channel ends, the turn channel splitting at the first channel end into first and second channel legs such that there is a region between the first and second channel legs, the first and second channels legs merging at the second channel end, the radial cooling passage narrowing to a neck portion, and the neck portion extending through the region between the first and second channel legs.
2. The airfoil as recited in claim 1 , wherein the radial cooling passage is flow isolated from the first and second cooling channels.
3. The airfoil as recited in claim 1 , wherein the turn channel includes a middle section between first and second ears, the middle section splitting into the first and second channel legs.
4. The airfoil as recited in claim 1 , wherein, from the channel end of the first cooling channel, the first and second legs increase in thickness and decrease in width.
5. The airfoil as recited in claim 4 , wherein the first and second channel legs increase in thickness by diffusion angles of no greater than 15 degrees.
6. A gas turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor,
the turbine section having an airfoil that includes
an airfoil wall defining a leading end, a trailing end, a first side, and a second side, the airfoil wall circumscribing an interior cavity,
radially-extending ribs that partition the interior cavity into first and second cooling channels and a radial cooling passage situated between the first and second cooling channels, the first and second cooling channels extending to respective first and second channel ends, and
a turn channel connecting the first and second channel ends, the turn channel including a middle section between first and second ear sections, and the middle section splitting at the first channel end into first and second channel legs such that there is a region between the first and second channel legs, the first and second channels legs merging at the second channel end, the radial cooling passage extending through the region between the first and second channel legs.
7. The gas turbine engine as recited in claim 6 , wherein each of the first and second legs has a mouth at the first channel end and a crest at an apex of the turn channel, the mouth defining a cross-sectional area, the crest defining a cross-sectional area, and the cross-sectional area of the crest is from 25% to 150% of the cross-sectional area of the mouth.
8. The gas turbine engine as recited in claim 7 , wherein the first and second legs have an inner turn radius that is greater than a thickness dimension of the cross-sectional area of the mouth by a factor of at least 2, wherein the inner turn radius is taken from an intersection of planes of the cross-sectional area of the mouth and the cross-sectional area of the crest.
9. The gas turbine engine as recited in claim 6 , wherein the first and second legs increase in thickness from the first channel end with diffusion angles of no greater than 15 degrees.
10. The gas turbine engine as recited in claim 6 , wherein the radial cooling passage is flow isolated from the first and second cooling channels.
11. An airfoil comprising:
an airfoil wall defining a leading end, a trailing end, a first side, and a second side, the airfoil wall circumscribing an interior cavity; and
radially-extending ribs that partition the interior cavity into first and second cooling channels and a radial cooling passage situated between the first and second cooling channels, the first and second cooling channels extending to respective first and second channel ends; and
a turn channel connecting the first and second channel ends, the turn channel splitting at the first channel end into first and second channel legs such that there is a region between the first and second channel legs, the first and second channels legs merging at the second channel end, the radial cooling passage extending through the region between the first and second channel legs.
12. The airfoil as recited in claim 11 , wherein the radial cooling passage is flow isolated from the first and second cooling channels.
13. The airfoil as recited in claim 12 , wherein the turn channel includes a middle section between first and second ears, the middle section splitting into the first and second channel legs.
14. The airfoil as recited in claim 13 , wherein, from the channel end of the first cooling channel, the first and second legs increase in thickness and decrease in width.
15. The airfoil as recited in claim 14 , wherein the first and second channel legs increase in thickness by diffusion angles of no greater than 15 degrees.