Patent ID: 8454304

Claim:
Bearing support structure for turbines comprising an inner ring where the bearing is housed, and an outer ring comprising anchoring points of an engine assembly containing a turbine, wherein the inner ring and the outer ring are radially connected by means of a plurality of structural vanes in a circumference-like arrangement between both rings, which transmit the bearing loads to the anchoring points of the engine assembly in the outer ring, and through which service fluids go through between the inner ring and the outer ring, and a plurality of aerodynamic vanes in a circumference-like arrangement between both rings, which straighten the main flow of the turbine, wherein the aerodynamic vanes are lighter than the structural vanes, and wherein the number of structural vanes depends exclusively on the bearing loads to be transmitted to the anchoring points of the engine assembly in the outer ring, the amount and kind of service fluids which must go between the inner ring and the outer ring, and wherein the number of aerodynamic vanes which are arranged and their section depend exclusively on the aerodynamic requirements demanded from the support structure for straightening of turbine main flow, and wherein the structural vanes fulfill structural functions and the aerodynamic vanes fulfill aerodynamic functions; wherein the aerodynamic vanes arranged between two structural vanes are grouped in packages by an inner membrane corresponding to the inner ring, to which said aerodynamic vanes are fixed at one of their ends, and an outer membrane, corresponding to the outer ring, to which the aerodynamic vanes are fixed at their other end, each one of the aerodynamic vane packages being joined to at least one of the rings; wherein each one of the aerodynamic vane packages is fixed to the inner ring and the outer ring, the inner membrane being integral to said inner ring, and the outer membrane being integral to said outer ring.