Gas turbine engine component cooling passage turbulator
A gas turbine engine component includes opposing walls that provide an interior cooling passage. One of the walls has a turbulator with a hook that is enclosed within the walls.
1. A gas turbine engine component comprising:
opposing walls providing an interior cooling passage, one of the walls has a turbulator with a hook provided as a cross-section of the turbulator that is enclosed within the walls, wherein the hook includes a first portion extending from a surface of the one wall, and a second portion extends from the first portion longitudinally within the interior cooling passage to a terminal end providing an overhang that is unattached with respect to the surface, wherein the interior flow passage is configured to provide a flow direction, and the second portion faces away from the flow direction, and wherein the first and second portions and the surface provide a pocket, the pocket configured to provide a cavitation zone.
2. A gas turbine engine component comprising:
opposing walls providing an interior cooling passage, one of the walls has a turbulator with a hook provided as a cross-section of the turbulator that is enclosed within the walls, wherein the hook includes a first portion extending from a surface of the one wall, and a second portion extends from the first portion longitudinally within the interior cooling passage to a terminal end providing an overhang that is unattached with respect to the surface, wherein the interior flow passage is configured to provide a flow direction, and the second portion faces into the flow direction, and wherein the first and second portions and the surface provide a pocket, the pocket configured to provide a cavitation zone.
3. The gas turbine engine component according to claim 1 , wherein the first portion has a height, and the second portion has a width, the aspect ratio of height to width in the range of 0.1-10.
4. The gas turbine engine component according to claim 1 , wherein the hook provides a chevron.
5. The gas turbine engine component according to claim 1 , wherein the hook provides a curved saw-tooth shaped structure.
6. The gas turbine engine component according to claim 1 , wherein the second portion is parallel to the surface.
7. The gas turbine engine component according to claim 1 , wherein gas turbine engine component is one of a blade, a vane, a combustor liner, an exhaust liner, and a blade outer air seal.
8. The gas turbine engine component according to claim 1 , wherein the turbulator provides a surface protrusion with a stream-wise cross-sectional shape providing at least one secondary surface near parallel with the wall to which the protrusion is affixed.
9. A method of cooling a gas turbine engine component including walls providing an interior cooling passage configured to provide a flow direction, one of the walls has a turbulator with a hook that is enclosed within the walls, the method comprising the step of:
providing the hook as a cross-section of the turbulator, wherein the hook includes a first portion extending from a surface of the one wall, and a second portion extends from the first portion longitudinally within the interior cooling passage to a terminal end providing an overhang that is unattached with respect to the surface to provide a pocket;
passing a fluid flow through the interior cooling passage; and
cavitating the fluid flow through the interior cooling passage in the pocket provided by the hook.
10. The method according to claim 9 , wherein the hook provides at least one of a curved saw-tooth shaped structure and the second portion is parallel to the surface.
11. The method according to claim 9 , wherein the first portion has a height, and the second portion has a width, the aspect ratio of height to width in the range of 0.1-10.