Boas flow directing arrangement
A gas turbine engine component includes a main body. A cooling passage is within the main body. The cooling passage is defined by a first wall opposite a second wall. The cooling passage has an inlet on the second wall. A protrusion is formed on the first wall arranged across from the inlet.
1. A gas turbine engine component comprising:
a main body;
a cooling passage within the main body, the cooling passage defined by a first wall opposite a second wall, the cooling passage having a passage height between the first wall and the second wall, the cooling passage having an inlet on the second wall wherein the inlet is arranged on a dome on the second wall, the dome extending outward relative to the cooling passage, the dome defining a portion of the cooling passage having a second passage height that is larger than the passage height; and
a protrusion formed on the first wall arranged across from the inlet, wherein the dome has a first height and the protrusion has a second height, the first height is substantially the same as the second height.
2. The component of claim 1 , wherein the first wall is a radially inner wall and the second wall is a radially outer wall.
3. The component of claim 1 , wherein the protrusion extends inward relative to the cooling passage.
4. The component of claim 1 , wherein the protrusion comprises a ramp feature having a sloped surface.
5. The component of claim 4 , wherein the cooling passage defines an upstream end and a downstream end, and the ramp feature is configured to direct cooling fluid towards the upstream end.
6. The component of claim 5 , wherein the sloped surface faces toward the upstream end.
7. The component of claim 5 , wherein the ramp feature has a length in a circumferential direction and a wall extends along the length of the ramp feature.
8. The component of claim 7 , wherein the wall extends downstream of the ramp feature.
9. The component of claim 1 , wherein the passage height between the first and second walls is at least 0.050 inches (1.27 mm).
10. The component of claim 1 , wherein a plurality of turbulators are arranged on one of the first and second walls downstream of the protrusion.
11. The component of claim 1 , wherein the component is a blade outer air seal.
12. The component of claim 4 , wherein the ramp feature has a ramp width in a circumferential direction and a ramp height in a radial direction, and the ramp width is between 1.5 and 2.5 times the ramp height.
13. The component of claim 5 , wherein the ramp feature is configured to direct cooling fluid into a corner within the cooling passage.
14. A turbine section for a gas turbine engine, comprising:
a turbine blade extending radially outwardly to a radially outer tip and for rotation about an axis of rotation;
a blade outer air seal having a plurality of segments mounted in a support structure, the plurality of segments arranged circumferentially about the axis of rotation and radially outward of the outer tip; and
at least one segment of the plurality of segments having an internal cooling passage defined by a first wall opposite a second wall, the cooling passage having a passage height between the first wall and the second wall, the internal cooling passage having an inlet on the second wall and a protrusion formed in the first wall across from the inlet wherein the inlet is arranged on a dome on the second wall, the dome extending outward relative to the cooling passage, the dome defining a portion of the cooling passage having a second passage height that is larger than the passage height, wherein the dome extends a first height from the second wall and the protrusion extends a second height from the first wall, the first height being substantially the same as the second height.
15. The turbine section of claim 14 , wherein the first wall is a radially inner wall and the second wall is a radially outer wall.
16. The turbine section of claim 14 , wherein the first and second heights are between 0.03 and 0.05 inches (0.762-1.27 mm).
17. The turbine section of claim 14 , wherein the inlet is arranged in a forward portion of the at least one segment of the plurality of segments.
18. The turbine section of claim 14 , wherein the cooling passage defines an upstream end and a downstream end, and the protrusion is a ramp feature configured to direct cooling fluid towards the upstream end.