| 摘要 |
The invention concerns a blade element for a gas turbine engine and methods of manufacturing said blade elements. In one embodiment, a blade element 100 includes a first inner surface 108 of the blade element, wherein the first inner surface 108 is associated with a first outer blade surface 106 of the blade element, and a second inner surface 109 of the blade element, wherein the second inner surface 109 is associated with a second outer blade surface 107 of the blade element and wherein the second inner surface 109 is opposite from the first inner surface 108. The blade element 100 also includes a cross-tie 130 1 configured to connect the first inner surface 108 to the second inner surface 109, wherein the cross-tie 130 1 is positioned along a trailing edge 110 of the blade element 100 and the cross-tie 130 1 is configured to reduce vibration mode effects of the blade element 100. |
