Tandem blade rotor disk
A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade.
1. A tandem rotor disk apparatus comprising:
a rotor disk body that is concentric about an axis;
a first plurality of blades distributed about the axis, each of the first plurality of blades extending radially outward from the rotor disk body, the first plurality of blades and the rotor disk body form a unitary one-piece element; and
a second plurality of blades, each of the second plurality of blades physically separate and distinct from each of the first plurality of blades, each of the second plurality of blades extending radially outward from the rotor disk body, the first plurality of blades being offset from the second plurality of blades in a direction parallel to the axis, wherein each of the second plurality of blades is coupled to the rotor disk body via a tangential engagement to the rotor disk body, wherein:
a blade platform of each of the second plurality of blades includes a protrusion, and
the protrusion is located in a tangentially extending groove formed in the rotor disk body.
2. The tandem rotor disk apparatus of claim 1 , wherein the first plurality of blades are disposed axially forward from the second plurality of blades.
3. A gas turbine engine comprising:
a first blade stage comprising:
a first rotor disk body that is concentric about an engine central longitudinal axis of the gas turbine engine; and
a plurality of sets of tandem blades circumferentially distributed about the engine central longitudinal axis, each of the plurality of sets of tandem blades including a first blade and a second blade, each of the first blade and the second blade extending radially outward from the first rotor disk body, wherein:
the first blade is spaced apart axially from the second blade,
the first blade and the first rotor disk body form a unitary one-piece element,
the second blade is physically separate and distinct from the first blade,
the second blade is coupled to the first rotor disk body via a tangential engagement to the first rotor disk body.
4. The gas turbine engine of claim 3 , wherein the blade stage is of a compressor section.
5. The gas turbine engine of claim 4 , wherein the blade stage is an aft-most blade stage of the compressor section.
6. The gas turbine engine of claim 3 , wherein a blade platform of the second blade includes a protrusion.
7. The gas turbine engine of claim 6 , wherein the protrusion is located in a tangentially extending groove formed in the rotor disk body.
8. The gas turbine engine of claim 3 , further comprising a second blade stage disposed forward of the first blade stage, the second blade stage comprising a second rotor disk body and a plurality of blades distributed about the central longitudinal axis, each of the plurality of blades extending radially outward from the second rotor disk body.