Gas turbine engine integrally bladed rotor with asymmetrical trench fillets

An integrally bladed rotor assembly comprising:

• a first integrally bladed rotor having a first rim that provides an inner flow surface;
• circumferentially spaced apart radially extending airfoils integral with the rotor and extending therefrom, joined by an airfoil fillet;
• and
• an asymmetrical trailing edge trench provided in the first rim between adjacent airfoils near trailing edges of the airfoils, one of the adjacent airfoils having a chord length, the trailing edge trench extends to the airfoil fillet of the adjacent airfoils, wherein the asymmetrical trench extends to an edge of an aft portion of the first rim, the aft portion includes a lip configured to overlap with a second rim of an adjacent second integrally bladed rotor, and the edge of the aft portion of the second rim is arranged at the airfoil fillet.

An integrally bladed rotor comprising:

• a rotor having a rim that provides an inner flow surface;
• circumferentially spaced apart radially extending airfoils integral with the rotor and extending therefrom, joined by an airfoil fillet;
• and
• an asymmetrical trailing edge trench provided in the rim between adjacent airfoils near trailing edges of the airfoils, one of the adjacent airfoils having a chord length, the trailing edge trench extends to the airfoil fillet of the adjacent airfoils, wherein the trailing edge trench includes pressure and suction side fillets, the pressure side fillet smaller than the suction side fillet, and a ratio of the suction side fillet radius relative to the pressure side fillet radius is in the range of 2:1 to 20:1.