Variable vane positioning apparatus for a gas turbine engine
A variable vane assembly for a gas turbine engine includes at least one synchronization ring, a plurality of variable vanes connected to the synchronization ring, a plurality of torque boxes disposed circumferentially about the synchronization ring, a drive ring coupled to each of the torque boxes such that the drive ring causes an approximately identical torque to be applied to the synchronization ring from the torque boxes simultaneously, and an actuator coupled to one of the plurality of torque boxes and operable to drive the drive ring through the torque box.
1. A gas turbine engine comprising:
a compressor section;
a combustor fluidly coupled to the compressor section via a primary flowpath;
a turbine section fluidly coupled to the combustor section via the primary flowpath;
a variable vane assembly comprising;
at least one synchronization ring disposed about said primary flowpath in one of said compressor section and said turbine section;
a plurality of variable vanes mounted to said at least one synchronization ring;
a drive ring disposed about said primary flowpath in one of said compressor section and said turbine section;
a first torque box coupled to said at least one synchronization ring and coupled to said drive ring, such that rotation of a torque box input causes rotation of the at least one synchronization ring and the drive ring;
a single second torque box offset from the first torque box about said drive ring by 180 degrees, the single second torque box being coupled to said at least one synchronization ring and coupled to said drive ring, such that rotation of the drive ring causes rotation of an input of the single second torque box and rotation of the input of the single second torque box causes rotation of the synchronization ring; and
an actuator including an output, wherein the output is coupled to the input of the first torque box such that the actuator drives the input of the first torque box.
2. The gas turbine engine of claim 1 , wherein the actuator output is coupled to the input of the first torque box via a torque tube.
3. The gas turbine engine of claim 1 , wherein the input of each of said first torque box and said single second torque box is coupled to the at least one synchronization ring via a bell crank.
4. The gas turbine engine of claim 1 , wherein the variable vane assembly is characterized by a single actuator.
5. The gas turbine engine of claim 1 , wherein the drive ring is supported about the primary flowpath via a plurality of support arms.
6. The gas turbine engine of claim 5 , wherein the plurality of support arms comprises eight support arms, and wherein the eight support arms are distributed approximately circumferentially evenly about the drive ring.
7. The gas turbine engine of claim 1 , wherein the first torque box and the single second torque box are interchangeable components.
8. A variable vane assembly comprising:
at least one synchronization ring;
a plurality of variable vanes coupled to said synchronization ring;
a plurality of torque boxes disposed circumferentially about the synchronization ring, the plurality of torque boxes including a first torque box coupled to the at least one synchronization ring and a single second torque box;
a drive ring coupled to each of said torque boxes such that said drive ring causes an approximately identical torque to be applied to the synchronization ring from the torque boxes simultaneously;
the single second torque box being offset from the first torque box by 180 degrees about the drive ring; and
an actuator coupled to one of said plurality of torque boxes and operable to drive the drive ring through the torque box.
9. The variable vane assembly of claim 8 , further comprising a plurality of idler support arms coupled to and disposed about the drive ring.