Impingement jet cooling structure with wavy channel
An impingement cooling structure is provided. The impingement cooling structure includes a flow channel formed between a first wall and a second wall facing the first wall, a plurality of impingement cooling holes disposed in the first wall such that the plurality of impingement cooling holes are spaced apart from each other along the flow channel, and a flow diverter convexly protruding from a surface of the second wall in each space between injection axes of the plurality of impingement cooling holes.
1. An impingement cooling structure comprising:
a flow channel formed, in a transverse direction, between a first wall and a second wall facing the first wall;
a plurality of impingement cooling holes disposed in the first wall such that the plurality of impingement cooling holes are spaced apart from each other along the transverse direction of the flow channel; and
a flow diverter convexly protruding from a surface of the second wall in each space between injection axes of the plurality of impingement cooling holes,
wherein the flow diverter includes a bypass channel, formed in the transverse direction, passing through ridges of both sides along the flow channel, the flow channel and the bypass channel being disposed in the same transverse direction,
wherein a flow axis of the bypass channel is disposed to intersect with an axis of an adjacent impingement cooling hole from among the plurality of impingement cooling holes to provide a smooth flow of a cooling air injected from the adjacent impingement cooling hole through the bypass channel.
2. The impingement cooling structure according to claim 1 , wherein a cross-sectional shape of the flow diverter with respect to a plane including the injection axes is a triangular cross-sectional shape in which both sides form the ridges.
3. The impingement cooling structure according to claim 2 , wherein the cross-sectional shape of the flow diverter with respect to the plane including the injection axes is configured such that the ridges form a planar shape.
4. The impingement cooling structure according to claim 3 , wherein a top portion in which the ridges meet forms a planar shape.
5. The impingement cooling structure according to claim 2 , wherein the cross-sectional shape of the flow diverter with respect to the plane including the injection axes is a triangular cross-sectional shape forming a continuous curved surface.
6. The impingement cooling structure according to claim 2 , wherein the first wall includes a plurality of indentations concavely recessed along the flow channel toward a space between the flow diverters, and the plurality of impingement cooling holes are disposed in the indentation.
7. The impingement cooling structure according to claim 6 , wherein a central axis of the flow diverter faces a middle portion between the indentations, and the injection axis of the impingement cooling hole faces a middle portion between the flow diverters.
8. The impingement cooling structure according to claim 6 , wherein an angle of the indentation with respect to the first wall is greater than an angle of the flow diverter with respect to the second wall.
9. The impingement cooling structure according to claim 1 , wherein the first wall is a cold wall and the second wall is a hot wall.
10. The impingement cooling structure according to claim 9 , wherein the first wall is a flow sleeve of a combustor and the second wall is a liner or transition piece of the combustor.
11. The impingement cooling structure according to claim 9 , wherein the first wall is an inner wall defining a cavity of a turbine vane, and the second wall is an outer wall spaced apart from the inner wall and defining a contour of the turbine vane.
12. The impingement cooling structure according to claim 9 , wherein the first wall is an inner wall defining a cavity of a turbine blade, and the second wall is an outer wall spaced apart from the inner wall and defining a contour of the turbine blade.
13. The impingement cooling structure according to claim 1 , wherein the bypass channel is in a form of a tunnel, covered on a top thereof, in the flow diverter configured to be open toward both sides of the ridges along the flow channel.
14. A turbomachine component for a gas turbine, the turbomachine component comprising:
an airfoil having a first wall defining a cavity of the turbomachine component and a second wall spaced apart from the first wall and defining a contour of the turbomachine component;
a flow channel formed, in a transverse direction, between the first wall and the second wall facing the first wall;
a plurality of impingement cooling holes disposed in the first wall such that the plurality of impingement cooling holes are spaced apart from each other along the transverse direction of the flow channel; and
a flow diverter convexly protruding from a surface of the second wall in each space between injection axes of the plurality of impingement cooling holes,
wherein the flow diverter includes a bypass channel, formed in the transverse direction, passing through ridges of both sides along the flow channel, the flow channel and the bypass channel being disposed in the same transverse direction,
wherein a flow axis of the bypass channel is disposed to intersect with an axis of an adjacent impingement cooling hole from among the plurality of impingement cooling holes to provide a smooth flow of a cooling air injected from the adjacent impingement cooling hole through the bypass channel.
15. A gas turbine comprising a turbomachine component, wherein the turbomachine component is according to claim 14 .