초록 ▼

Aspects of the disclosure are directed to a damper configured to be located in a cavity formed between first and second bases configured to seat respective first and second airfoils, the damper having a first face and a second face, where an aspect ratio between the first face and the second face en

Aspects of the disclosure are directed to a damper configured to be located in a cavity formed between first and second bases configured to seat respective first and second airfoils, the damper having a first face and a second face, where an aspect ratio between the first face and the second face ensures that the damper is installed in the cavity in accordance with a predetermined orientation.

대표청구항 ▼

1. A system for a gas turbine engine, comprising: a damper configured to be located in a cavity formed between first and second bases configured to seat respective first and second airfoils, the damper having a first face and a second face,wherein an aspect ratio between the first face and the secon

1. A system for a gas turbine engine, comprising: a damper configured to be located in a cavity formed between first and second bases configured to seat respective first and second airfoils, the damper having a first face and a second face,wherein an aspect ratio between the first face and the second face ensures that the damper is installed in the cavity in accordance with a predetermined orientation,wherein the predetermined orientation is relative to a forward axial reference direction or an aft axial reference direction with respect to an axial centerline of the gas turbine engine. 2. The system of claim 1, wherein the first face has a first width and the second face has a second width that is different from the first width, and wherein the aspect ratio is based on a ratio of the first width and the second width. 3. The system of claim 2, wherein the first width and the second width are measured with respect to a centerline that runs a length of the damper. 4. The system of claim 1, wherein the damper has a bridge section that joins the first face and the second face. 5. The system of claim 4, wherein a width of the bridge section is less than a first width associated with the first face and a second width associated with the second face. 6. The system of claim 4, wherein the damper is substantially U-shaped. 7. The system of claim 1, wherein the damper is made of a sheet stock. 8. The system of claim 1, wherein the damper is configured to be rotated in a first direction to get the first face to fit in the cavity. 9. The system of claim 8, wherein the damper is configured to be counter-rotated relative to the first direction to seat the damper within the cavity. 10. The system of claim 1, further comprising: the first and second bases. 11. The system of claim 10, further comprising: the first and second airfoils. 12. The system of claim 1, wherein the first and second airfoils are associated with blades of a turbine. 13. The system of claim 12, further comprising: a rotor disk configured to seat the first and second bases.