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. The tandem rotor disk apparatus may include two separate rotor disk bodies.
1. A tandem rotor disk apparatus comprising:
a rotor disk body that is concentric about an axis, the rotor disk body including a forward portion spaced apart axially from an aft portion and defining an axial gap therebetween;
a tandem blade, comprising
a blade platform;
a first blade extending radially outward from the blade platform; and
a second blade extending radially outward from the blade platform; wherein:
the first blade is offset from the second blade in a direction parallel to the axis,
the blade platform includes a first protrusion and a second protrusion,
the first protrusion extends radially inward from the blade platform,
the second protrusion extends radially inward from the blade platform,
the first protrusion is spaced apart axially from the second protrusion,
the first protrusion is coupled to a first groove extending axially through the forward portion of the rotor disk body, and
the second protrusion is coupled to a second groove extending axially through the aft portion of the rotor disk body.
2. The tandem rotor disk apparatus of claim 1 , wherein the first blade and the second blade are integrally formed together and are jointly coupled to the rotor disk body.
3. A gas turbine engine comprising:
a blade stage comprising:
a rotor disk body that is concentric about an engine central longitudinal axis of the gas turbine engine, the rotor disk body including a forward portion spaced apart axially from an aft portion and defining an axial gap therebetween;
a plurality of tandem blades circumferentially distributed about the engine central longitudinal axis, a tandem blade in the plurality of tandem blades comprising:
a blade platform,
a forward blade extending radially outward from the blade platform, and
an aft blade extending radially outward from the blade platform, the aft blade axially adjacent to the forward blade wherein:
the blade platform includes a first protrusion and a second protrusion,
the first protrusion extends radially inward from the blade platform,
the second protrusion extends radially inward from the blade platform,
the first protrusion is spaced apart axially from the second protrusion,
the first protrusion is coupled to a first groove extending axially through the forward portion of the rotor disk body, and
the second protrusion is coupled to a second groove extending axially through the aft portion of the 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 the forward blade and the aft blade are integrally formed together and are jointly coupled to the rotor disk body.