Supporting structure for a gas turbine engine
A supporting structure for a gas turbine engine includes at least one annular member, and a plurality of circumferentially spaced elements that extend in a radial direction of the annular member and that are connected to the annular member. At least one of the circumferentially spaced elements has an airfoil shape in cross section. The annular member includes at least two substantially flat panel segments that are arranged side by side in a circumferential direction of the annular member. The panel segments are connected to each other in a connection region that extends along facing end parts of the two panel segments. The airfoil shaped element is connected to the annular member at the connection region. A mean camber line of the airfoil shaped element at least along a portion of its length is inclined in relation to an axial direction of the annular member, and the connection region at least along a portion of its length is inclined in relation to the axial direction of the annular member. The inclined portion of the connection region is directed substantially in parallel to the inclined portion of the mean camber line of the airfoil shaped element. A gas turbine engine including a supporting structure of the above type is also provided.
1. Supporting structure for a gas turbine engine, the structure comprising
at least one annular member, and
a plurality of circumferentially spaced elements that extend in a radial direction of the annular member and that are connected to the annular member, wherein at least one of the circumferentially spaced elements has an airfoil shape in cross section, wherein the annular member comprises
at least two substantially flat panel segments that are arranged side by side in a circumferential direction of the annular member, wherein the panel segments are connected to each other in a connection region that extends along facing end parts of the two panel segments, and wherein the airfoil shaped element is connected to the annular member at the connection region, wherein a mean camber line of the airfoil shaped element at least along a portion of its length is inclined in relation to an axial direction of the annular member, and the connection region at least along a portion of its length is inclined in relation to the axial direction of the annular member, wherein the inclined portion of the connection region is directed substantially in parallel to the inclined portion of the mean camber line of the airfoil shaped element.
2. A supporting structure according to claim 1 , wherein the airfoil shaped element has a cambered shape.
3. A supporting structure according to claim 2 , wherein the inclined portion of the connection region substantially coincides with the mean camber line along a substantial portion of its length.
4. A supporting structure according to claim 1 , wherein the inclined portion of the connection region follows a substantially straight line.
5. A supporting structure according to claim 1 , wherein the connection region follows a substantially straight line along its entire length.
6. A supporting structure according to claim 1 , wherein the annular member comprises a set of substantially flat panel segments and a corresponding set of connection regions, the panel segments being arranged such as to provide at least a portion of the annular member with a polygonal-shaped radial cross section, wherein each connection region corresponds to a corner in the polygonal-shaped radial cross section.
7. A supporting structure according to claim 1 , wherein the supporting structure comprises
an outer annular member and
an inner annular member ( 20 ) for receiving a turbine drive shaft ( 11 ), wherein the outer annular member and the inner annular member ( 20 ) are concentrically arranged around a common axis ( 2 ), and wherein the circumferentially spaced elements extend between and connect the outer and inner annular members.
8. A supporting structure according to claim 7 , wherein the outer annular member is provided with the panel segments.
9. A supporting structure according to claim 7 , wherein the inner annular member ( 20 ) is provided with the panel segments.
10. Gas turbine engine, wherein it comprises a supporting structure according to claim 1 .
11. An aircraft comprising a gas turbine engine comprising a supporting structure according to claim 1 .