CONCENTRIC SHAFTS FOR REMOTE INDEPENDENT VARIABLE VANE ACTUATION

• US 20170276013A1
• Filed: 03/24/2016
• Published: 09/28/2017
• Est. Priority Date: 03/24/2016
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Suciu, Gabriel L., Zimmitti, Jonathan F., Chandler, Jesse M.
• Granted Patent: US 10,107,130 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 17/162 for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F04D 29/563 specially adapted for elastic fluid pumps
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/12 Fluid guiding means, e.g. vanes
• CPC Class Codes: F05D 2260/57 using servos, independent actuators, etc.
• CPC Class Codes: F16H 19/001 for conveying reciprocating or limited rotary motion
• CPC Class Codes: F16H 49/001 Wave gearings, e.g. harmonic drive transmissions harmonic drives specially adapted for positioning programme-controlled manipulators B25J9/1025
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.

Claims

1. A gas turbine engine, comprising:

a first actuator;

a first harmonic drive driven by the first actuator;

a first drive shaft driven by the first harmonic drive;

a second actuator;

a second harmonic drive driven by the second actuator; and

a second drive shaft driven by the second harmonic drive, the first drive shaft coaxial with the second drive shaft.

2. The gas turbine engine as recited in claim 1, wherein the first drive shaft and the second drive shaft extend through a firewall.

3. The gas turbine engine as recited in claim 1, wherein the first drive shaft is operable to drive a first variable vane stage.

4. The gas turbine engine as recited in claim 3, wherein the second drive shaft is operable to drive a second variable vane stage.

5. The gas turbine engine as recited in claim 1, wherein the harmonic drive includes a strain wave gearing mechanism.

6. The gas turbine engine as recited as recited in claim 5, wherein the strain wave gearing mechanism include a fixed circular spline, a flex spline attached to an output shaft, and a wave generator attached to an input shaft, the flex spline driven by the wave generator with respect to the circular spline.

7. The gas turbine engine as recited in claim 1, wherein the harmonic drive provides between a 30:

1-320;

1 gear ratio.

8. The gas turbine engine as recited in claim 1, wherein the actuator is an electric motor.

9. The gas turbine engine as recited in claim 1, wherein the first drive shaft and the second drive shaft are operable to drive a respective first unison ring and a second unison ring.

10. The gas turbine engine as recited in claim 1, wherein the first drive shaft and the second drive shaft include a respective first drive gear and a second drive gear operable to drive a respective first unison ring and a second unison ring.

11. The gas turbine engine as recited in claim 10, wherein the first unison ring and the second unison ring include a respective gear segment meshed with the respective first drive gear and the second drive gear.