| 摘要 |
The invention concerns a gas turbine engine component (15), comprising: a ring element (14, 27) and a plurality of circumferentially spaced load carrying vanes (12) extending in a radial direction of the ring element (14, 27); wherein at least one of said vanes (12) is made of a composite material, and wherein the at least one composite vane (12) is fastened to the ring element (14, 27), said component (15) further comprising: first and second wall portions (20, 32) that are fixed in relation to the ring element (14, 27) and arranged on opposite sides of the composite vane (12); and at least a first hole (61) extending through the first wall portion (20), the composite vane (12) and the second wall portion (32), wherein said first hole (61) is adapted to receive a first insertion member (63). The invention is characterized in that the component (15) is arranged such as to, with regard to the first hole (61), provide a tight fit (65a, 65b) for the first insertion member (63) in the first wall portion (20) as well as in the composite vane (12) and to provide a loose fit (66) with a radial play in the second wall portion (32). The invention also concerns a gas turbine component comprising a component of the above type. |
