Engine bracket for GE™

Following forms an essential design but without leaving its forms and technical functions support this proposed turbine answers all the requirements established by General Electric. The model has undergone changes in its structure, so essential and needs, there was a loss of mass of exactly 50% (Same established by GE) There was a reduction graduativa in their thicknesses, with a specific degree of 6 from the point of greatest effort for less tension. Thinking of casting and machining processes, the cavities there is also a 5 degree tilt. In its flange coupling pin, the center of gravity of the piece to the back (where the thickness is thinner), there was a gap of 4 for better structure, since that area would be a slot in the part, improving this proved by finite element simulations we really need is this inclination. The flow rate of the simulations are all within safe limits and with great off limits in their numbers. At the bottom there is a reinforced to prevent buckling, and how the piece is screwed, there is also a gas outlet for possible pressure by heating. Most forms of this model has been designed so that it can be machined or cast, machined if the same can be performed in two phases with cutters (APKT) 3 and 16mm We performed a calculation of moment and shear forces impacted to verify the part and ALL SLOPES BEEN REVISED, with the calculation based on: q=R1 [x]-¹ - F1 [x-a1]-¹ - F2 [x-a2]-¹ + R2 [x-l]-¹ Shear strength V= ∫ qdx=R1 [x]º - F1 [x-a1]º - F2 [x-a2]º + R2 [x-l]º (note that V ≠ 0) M=∫ qdx=R1 [x]¹ - F1 [x-a1]¹ - F2 [x-a2]¹ = R2 [x-l]¹ ∑= R1+R2 = 0 except 0≤x≤ L Bypassing the bending moment in regions F1 e F2 Excellent challange. Thank you in advanced.