TANDEM ROTOR DISK APPARATUS AND CORRESPONDING GAS TURBINE ENGINE

A tandem rotor disk apparatus (100) may include a rotor disk body (110; 210; 310; 410; 510; 610; 710; 810) concentric about an axis (A-A'). The tandem rotor disk apparatus (100) may also include a first blade (121; 221; 321; 421; 521; 621; 721; 821) extending radially outward of the rotor disk body (110; 210; 310; 410; 510; 610; 710; 810) and a second blade (122; 222; 322; 422; 522; 622; 722; 822) extending radially outward of the rotor disk body (110; 210; 310; 410; 510; 610; 710; 810). The first blade (121; 221; 321; 421; 521; 621; 721; 821) may be offset from the second blade (122; 222; 322; 422; 522; 622; 722; 822) in a direction parallel to the axis (A-A'). The tandem rotor disk apparatus (100) may be implemented in a gas turbine engine (20) with no intervening stator vane stages disposed between the first blade (121; 221; 321; 421; 521; 621; 721; 821) and the second blade (122; 222; 322; 422; 522; 622; 722; 822). The tandem rotor disk apparatus (100) may include two separate rotor disk bodies (110; 210; 310; 410; 510; 610; 710; 810).