Patent ID: 9003812
Filing Date: 2015-04-14
Classification: F01D,F02C,F05D,Y02T

Abstract:
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.