Disclosed is a gas turbine engine including a compressor section and a turbine section. The gas turbine engine includes a gas turbine engine component having a first wall providing an outer surface of the gas turbine engine component and a second wall spaced-apart from the first wall. The first wall
Disclosed is a gas turbine engine including a compressor section and a turbine section. The gas turbine engine includes a gas turbine engine component having a first wall providing an outer surface of the gas turbine engine component and a second wall spaced-apart from the first wall. The first wall is a gas-path wall exposed to a core flow path of the gas turbine engine. The second wall is a non-gas-path wall. A cooling passageway is provided between the second wall and the first wall. The second wall has a trip strip provided thereon.
대표청구항▼
1. A gas turbine engine, comprising: a compressor section; a turbine section; anda gas turbine engine component having a first wall providing an outer surface of the gas turbine engine component and a second wall spaced-apart from the first wall, the first wall being a gas-path wall exposed to a cor
1. A gas turbine engine, comprising: a compressor section; a turbine section; anda gas turbine engine component having a first wall providing an outer surface of the gas turbine engine component and a second wall spaced-apart from the first wall, the first wall being a gas-path wall exposed to a core flow path of the gas turbine engine, the second wall being a non-gas-path wall, a cooling passageway provided between the second wall and the first wall, the second wall having a trip strip provided thereon, wherein the trip strip is chevron-shaped and includes a first leg and a second leg joined at an apex, the apex arranged to point in a direction substantially opposite a direction of fluid flow within the cooling passageway; wherein the trip strip is only in contact with the second wall. 2. The gas turbine engine as recited in claim 1, wherein the gas turbine engine component is an airfoil assembly provided in one of the compressor section and the turbine section, wherein the first wall is an airfoil wall and the second wall is provided by a baffle, wherein the passageway is provided between an outer surface of the baffle and an inner surface of the airfoil wall, and wherein the trip strip is provided on the outer surface of the baffle. 3. The gas turbine engine as recited in claim 2, wherein the baffle is provided within a cavity provided by the airfoil wall. 4. The gas turbine engine as recited in claim 3, wherein the baffle includes a plurality of said trip strips. 5. The gas turbine engine as recited in claim 4, wherein an axial flow of fluid is provided in the passageway, the axial flow of fluid flowing in an axial direction generally parallel to an engine central longitudinal axis. 6. The gas turbine engine as recited in claim 5, wherein the plurality of trip strips are arranged such that the apexes point in the axial direction. 7. The gas turbine engine as recited in claim 4, wherein a radial flow of fluid is provided in the passageway, the radial flow of fluid flowing in a radial direction generally perpendicular to an engine central longitudinal axis. 8. The gas turbine engine as recited in claim 7, wherein the plurality of trips strips are arranged such that the apexes point in the radial direction. 9. The gas turbine engine as recited in claim 4, wherein the plurality of trip strips are provided in a linear arrangement, and are arranged in a direction generally parallel to a vertical axis of the airfoil section. 10. The gas turbine engine as recited in claim 4, wherein the plurality of trip strips are provided in a skewed arrangement, and are arranged in a direction angled relative to a vertical axis of the airfoil section. 11. The gas turbine engine as recited in claim 2, wherein the airfoil wall provides a first cavity and a second cavity, the first cavity adjacent a leading edge of the airfoil section, the second cavity adjacent the trailing edge of the airfoil section. 12. The gas turbine engine as recited in claim 11, including a first baffle provided in the first cavity, and a second baffle provided in the second cavity, wherein a first airfoil cooling passageway is provided between an outer surface of the first baffle and the inner surface of the airfoil wall, and wherein a second airfoil cooling passageway is provided between an outer surface of the second baffle and the inner surface of the airfoil wall. 13. The gas turbine engine as recited in claim 12, wherein the first baffle includes a plurality of first trip strips extending from the outer surface of the first baffle into the first passageway, and wherein the second baffle includes a plurality of second trip strips extending from the outer surface of the second baffle into the second passageway. 14. The gas turbine engine as recited in claim 1, wherein an inner surface of the first wall is substantially smooth and free of any raised features. 15. An airfoil assembly, comprising: an airfoil wall; a baffle;an airfoil cooling passageway provided between an outer surface of the baffle and an inner surface of the airfoil wall, the outer surface of the baffle having a trip strip provided thereon, wherein the trip strip is chevron-shaped and includes a first leg and a second leg joined at an apex, the apex arranged to point in a direction substantially opposite a direction of fluid flow within the cooling passageway; wherein the trip strip is only in contact with the baffle. 16. The airfoil assembly as recited in claim 15, wherein the baffle is provided within a cavity provided by the airfoil wall. 17. The airfoil assembly as recited in claim 16, including an internal passageway provided inside the baffle. 18. The airfoil assembly as recited in claim 17, wherein the baffle includes a plurality of orifices to allow the internal passageway to communicate with airfoil cooling passageway. 19. The airfoil assembly as recited in claim 18, wherein the trip strip is configured to disturb a flow of fluid in the airfoil cooling passageway. 20. The airfoil assembly as recited in claim 16, wherein the baffle includes a plurality of said trip strips. 21. The airfoil assembly as recited in claim 15, wherein an inner surface of the airfoil wall is substantially smooth and free of any raised features.
Lee Ching-Pang (Cincinnati OH) Savage Joseph W. (Maineville OH) Bobo Melvin (Cincinnati OH), Scaled heat transfer surface with protruding ramp surface turbulators.
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