Internally cooled engine components
A component of a gas turbine engine is provided. The component may include an external surface with a skin cavity adjacent the external surface. The skin cavity may be defined by a hot-side surface and a cool-side surface with the hot-side surface between the cool-side surface and the external surface. A flat portion may be disposed on the hot-side surface and may, for example, define a wall-thickness check region. A protrusion may be disposed on the cool-side surface opposite the flat portion on the hot-side surface. The hot-side surface and the cool-side surface may tend to increase a heat transfer coefficient along the flat portion of the hot-side surface, which may also define a wall thickness check region.
1. A component of a gas turbine engine, comprising:
an external surface;
a skin cavity adjacent the external surface and internal to the component, wherein the skin cavity is defined by a hot-side surface and a cool-side surface, wherein the hot-side surface is between the cool-side surface and the external surface;
a first trip strip disposed on the hot-side surface and having a first geometry;
a second trip strip disposed on the hot-side surface adjacent the first trip strip, wherein the second trip strip has a second geometry different from the first geometry;
a third trip strip disposed on the hot-side surface;
a flat portion on the hot-side surface, the flat portion being smooth and continuous and extending from the second trip strip to the third trip strip; and
a protrusion disposed on the cool-side surface opposite the flat portion on the hot-side surface.
2. The component of the gas turbine engine of claim 1 , wherein the protrusion on the cool-side surface is disposed between a first flat portion of the cool-side surface and a second flat portion of the cool-side surface.
3. The component of the gas turbine engine of claim 2 , wherein a first hydraulic diameter of the skin cavity taken at the first flat portion of the cool-side surface is greater than a second hydraulic diameter of the skin cavity taken at the protrusion of the cool-side surface.
4. The component of the gas turbine engine of claim 3 , wherein the second hydraulic diameter is up to 40% less than the first hydraulic diameter.
5. The component of the gas turbine engine of claim 1 , further comprising an internal cooling cavity internal to the component, wherein the cool-side surface of the skin cavity is between the internal cooling cavity and the hot-side surface of the skin cavity.
6. The component of the gas turbine engine of claim 1 , wherein the hot-side surface and the cool-side surface are configured to accelerate a coolant flowing past the flat portion of the hot-side surface and the protrusion of the cool-side surface.
7. The component of the gas turbine engine of claim 1 , wherein the hot-side surface and the cool-side surface are configured to increase a heat transfer coefficient along the flat portion of the hot-side surface by at least 30% relative to a second local heat transfer coefficient along the first trip strip.
8. The component of the gas turbine engine of claim 1 , wherein the third trip strip has the first geometry of the first trip strip.
9. An airfoil, comprising:
an external surface;
an internal cooling cavity internal to the airfoil;
a skin cavity disposed between the external surface and the internal cooling cavity, wherein the skin cavity is defined by a hot-side surface and a cool-side surface, wherein the hot-side surface is between the cool-side surface and the external surface;
a first trip strip disposed on the hot-side surface and having a first geometry;
a second trip strip disposed on the hot-side surface adjacent to the first trip strip, wherein the second trip strip has a second geometry different from the first geometry;
a third trip strip disposed on the hot-side surface;
a wall thickness check region on the hot-side surface, the wall thickness check region being smooth and continuous and extending from the second trip strip to the third trip strip; and
a protrusion disposed on the cool-side surface opposite the wall thickness check region.
10. The airfoil of claim 9 , wherein the protrusion on the cool-side surface is disposed between a first flat portion of the cool-side surface and a second flat portion of the cool-side surface.
11. The airfoil of claim 10 , wherein a first hydraulic diameter of the skin cavity taken at the first flat portion of the cool-side surface is greater than a second hydraulic diameter of the skin cavity taken at the wall thickness check region.
12. The airfoil of claim 11 , wherein the second hydraulic diameter is up to 40% less than the first hydraulic diameter.
13. The airfoil of claim 9 , wherein the hot-side surface and the cool-side surface are configured to accelerate a coolant flowing past the wall thickness check region.
14. The airfoil of claim 9 , wherein the third trip strip has the first geometry of the first trip strip.
15. A gas turbine engine, comprising:
a compressor configured to rotate about an axis and compress a gas;
a combustor aft of the compressor and configured to combust the gas;
a turbine section aft of the combustor and configured to extract energy from the combusted gas, wherein the turbine section comprises an airfoil configured to rotate about the axis, the airfoil comprising:
a first external surface;
an internal cooling cavity internal to the airfoil;
a second external surface opposite the internal cooling cavity from the first external surface;
a first skin cavity disposed between the first external surface and the internal cooling cavity, wherein the first skin cavity is defined by a hot-side surface and a cool-side surface, wherein the hot-side surface is between the cool-side surface and the first external surface;
a first trip strip disposed on the hot-side surface and having a first geometry;
a second trip strip disposed on the hot-side surface adjacent to the first trip strip, wherein the second trip strip has a second geometry different from the first geometry;
a third trip strip disposed on the hot-side surface;
a wall thickness check region on the hot-side surface, the wall thickness check region being smooth and continuous and extending from the second trip strip to the third trip strip;
a protrusion disposed on the cool-side surface opposite the wall thickness check region; and
a second skin cavity disposed between the second external surface and the internal cooling cavity.
16. The gas turbine engine of claim 15 , wherein the protrusion on the cool-side surface is disposed between a first flat portion of the cool-side surface and a second flat portion of the cool-side surface.
17. The gas turbine engine of claim 16 , wherein a first hydraulic diameter of the first skin cavity taken at the first flat portion of the cool-side surface is greater than a second hydraulic diameter of the first skin cavity taken at the wall thickness check region.
18. The gas turbine engine of claim 17 , wherein the second hydraulic diameter is up to 40% less than the first hydraulic diameter.
19. The gas turbine engine of claim 15 , wherein the hot-side surface and the cool-side surface are configured to accelerate a coolant flowing past the wall thickness check region.
20. The gas turbine engine of claim 15 , wherein the third trip strip has the first geometry of the first trip strip.