| 摘要 |
A supporting structure for a gas turbine engine comprises an inner ring, an outer ring, a plurality of circumferentially spaced, load carrying radial elements connecting the inner and outer rings, said radial elements being configured to transfer loads between the inner ring and the outer ring, wherein a gas channel for a primary axial gas flow is defined between the inner and outer rings, an inlet side for primary gas flow entrance, and an outlet side for primary gas outflow, wherein the radial elements have an airfoil shape with a leading edge directed towards the inlet side of the supporting structure, a trailing edge directed towards the outlet side of the supporting structure, and two opposite sides connecting the leading edge and the trailing edge, wherein a locus of points midway between the two opposite sides forms a mean camber line of each radial element, wherein at least one of the radial elements comprises a gas passage arrangement configured to lead a separate bleeding gas flow from the supporting structure, and wherein the gas passage arrangement comprises a radially extending gas channel arranged inside the radial element and at least one opening in communication with said gas channel, wherein the at least one opening is arranged at one of the two opposite sides of the radial element. |
