Supporting structure for a gas turbine engine

• Main Author: SJÖQVIST ROGER
• Format: Patent
• Language: English
• Published: 14.04.2015
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; ENGINE PLANTS IN GENERAL; GAS-TURBINE PLANTS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; LIGHTING; MACHINES OR ENGINES FOR LIQUIDS; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR; PRODUCING MECHANICAL POWER; STEAM ENGINES; WEAPONS; WIND, SPRING WEIGHT AND MISCELLANEOUS MOTORS

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.