Variable rotor blade for gas turbine engine

• US 7,901,185 B2
• Filed: 02/21/2007
• Issued: 03/08/2011
• Est. Priority Date: 02/21/2007
• Status: Expired due to Fees

• Current Assignee: Raytheon Technologies Corporation d/b/a RTX
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Nordeen, Craig A., Suciu, Gabriel L.
• Primary Examiner(s): Nguyen; Ninh H
• Application Number:
  US11/709,013
• Publication Number:
  US 20080273976A1
• Time in Patent Office: 1,476 Days
• Field of Search: 415/130, 416/198.R, 416/170.R, 416/155, 416/162, 416/DIG.5
• US Class Current: 416/155
• CPC Class Codes: F01D 5/148 Blades with variable camber, e.g. by ejection of fluid
• CPC Class Codes: F01D 5/30 Fixing blades to rotors; Blade roots ; Blade spacers
• CPC Class Codes: F01D 7/02 having adjustment responsive to speed
• CPC Class Codes: F04D 29/323 adjustable
• CPC Class Codes: F04D 29/362 during rotation
• CPC Class Codes: F05D 2220/36 specially adapted for the fan of turbofan engines
• CPC Class Codes: F05D 2260/71 as a function of flow velocity
• CPC Class Codes: F05D 2260/74 by turning around an axis perpendicular the rotor centre line
• CPC Class Codes: F05D 2260/76 the adjusting mechanism using auxiliary power sources
• CPC Class Codes: F05D 2260/79 Bearing, support or actuation arrangements therefor
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10S 416/05 Variable camber or chord length

Abstract

A variable rotor blade mechanism for use in a gas turbine engine comprises a blade rotor, a blade, a harmonic drive system, a stepper motor and a bracket. The blade rotor rotates absolutely about an axial engine centerline during operation of the gas turbine engine. The blade extends radially from the blade rotor and is configured to be adjustable by rotation about a radial axis. The harmonic drive system is mounted to the blade rotor and connected to the blade to rotate the blade about the radial axis. The stepper motor drives the harmonic drive with relative rotational input with respect to the absolute rotation of the blade rotor. The bracket is disposed about the engine centerline and supports the stepper motor stationary with respect to the rotation of blade rotor such that the relative rotational input to the stepper motor is generated.

Claims

1. A variable rotor blade mechanism for use in a gas turbine engine, the mechanism comprising:

a blade rotor for rotating about an axial engine centerline during operation of the gas turbine engine;

a blade extending radially from blade rotor and configured for rotation about a radial axis;

a harmonic drive system mounted to the blade rotor and connected to the blade to rotate the blade about the radial axis;

a stepper motor for driving the harmonic drive with relative rotational input with respect to the rotation of the blade rotor;

a bearing assembly disposed between the stepper motor and the harmonic drive; and

a bracket disposed about the engine centerline for supporting the stepper motor stationary with respect to the rotation of blade rotor such that the relative rotational input to the stepper motor is generated.

2. The variable rotor blade mechanism of claim 1 and further comprising an actuator arm axially extending from the blade for converting the relative rotational input to the harmonic drive to rotation of the blade about the radial axis.

3. The variable rotor blade mechanism of claim 1 wherein the stepper motor comprises:

a stator coil mounted to the bracket such that it is stationary with respect to the rotation of the blade rotor and such that it circumscribes the centerline; and

a drive rotor connected to the harmonic drive and configured for rotation about the stator coil;

wherein the stator provides electrical input to the drive rotor such that the drive rotor rotates about the centerline.

4. The variable rotor blade mechanism of claim 3 wherein the stepper motor comprises stepped engagements such that the drive rotor advances in incremental steps and such that the rotor can be locked at each incremental step.

5. The variable rotor mechanism of claim 4 and further comprising a digital control device for providing electrical input to the stator coil.

6. The variable rotor blade mechanism of claim 5 wherein the stepper motor is continuously operated to drive the drive rotor with the absolute rotation of the blade rotor, or is intermittently operated to allow free rotation of the drive rotor with the absolute rotation of the blade rotor.

7. The variable rotor blade mechanism of claim 3 wherein the harmonic drive system comprises:

an annular rigid gear connected to the actuator arm and having a set of radially inward facing teeth; and

an annular flexible gear mounted to the blade rotor such that it rotates absolutely with the blade rotor, the flexible gear having a set of radially outward facing teeth engaged with the set of radially inward facing teeth;

wherein the drive rotor is disposed within the flexible gear such that relative rotation of the drive rotor with respect to the blade rotor produces rotation of the blade about the radial axis through the toothed engagement and the actuator arm.

8. A variable rotor blade mechanism comprising:

a blade rotor for rotating about an axial engine centerline during operation of the gas turbine engine;

a blade extending radially from blade rotor and configured for rotation about a radial axis;

a harmonic drive system mounted to the blade rotor and connected to the blade to rotate the blade about the radial axis;

a stepper motor for driving the harmonic drive with relative rotational input with respect to the rotation of the blade rotor;

a bracket disposed about the engine centerline for supporting the stepper motor stationary with respect to the rotation of blade rotor such that the relative rotational input to the stepper motor is generated;

an actuator arm axially extending from the blade for converting the relative rotational input to the harmonic drive to rotation of the blade about the radial axis;

a pin extending through the blade rotor;

a bore positioned at an inner diameter of the blade for receiving the pin such that the blade is rotatable about the pin; and

a radial retention system for restraining radial movement of the blade while allowing rotation of the blade about the radial axis.

9. The variable rotor blade mechanism of claim 8 wherein rotation of the blade about the radial axis by the actuation arm adjusts a pitch of the blade.

10. The variable rotor blade mechanism of claim 8 and further comprising:

an upstream blade rotor positioned upstream of the blade rotor;

an upstream blade section positioned upstream of the blade such that the upstream blade section and the blade are arranged in a two-piece airfoil configuration; and

wherein the rotation of the blade about the radial axis adjusts a camber of the two-piece airfoil configuration.

11. A variable pitch rotor blade for a gas turbine engine, the variable pitch rotor blade comprising:

a blade disk for rotating about an engine centerline during operation of the gas turbine engine;

a blade connected to the blade disk and configured for rotation about a radial axis at an outer diameter of the blade disk;

an actuator arm extending from an inner diameter end of the blade;

a bracket disposed about the engine centerline and for providing a stationary support with respect to rotation of the rotor;

a stepper motor comprising;

a stator mounted to the bracket such that it circumscribes the centerline; and

a rotor configured for rotation about the stator; and

a harmonic drive system comprising;

a flexible gear mounted to the rotor such that it rotates about the centerline with the rotor; and

a rigid gear connected to the actuator arm and engaged with the flexible gear;

wherein the rotor acts as a drive input to the flexible gear to cause relative rotation of the rigid gear about the centerline with respect to the blade disk such that the rigid gear adjusts the position of the actuator arm to adjust a pitch of the blade.

12. The variable pitch rotor blade of claim 11 wherein the rotor further comprises:

a circular inner bore configured for rotation about the stator; and

an elliptical outer diameter for providing harmonic input to the flexible gear.

13. The variable pitch rotor blade of claim 11 wherein the stepper motor comprises stepped engagements such that the rotor advances in incremental steps and such that the rotor can be locked at each incremental step.

14. The variable pitch rotor blade of claim 13 and further comprising a digital control device for providing electrical input to the stator such that the stepper motor is continuously operated to drive the rotor with rotation of the blade disk, or is intermittently operated to allow free rotation of the rotor with rotation of the blade disk.

15. The variable pitch rotor blade of claim 11 and further comprising:

a pin extending through the blade disk;

a bore positioned at an inner diameter of the blade for receiving the pin such that the blade is rotatable about the pin; and

a radial retention system for restraining radial movement of the blade while allowing radial rotation of the blade.

16. A variable camber rotor blade for a gas turbine engine, the variable camber blade comprising:

an upstream blade section mounted to an upstream rotor disk configured for rotation about an engine centerline during operation of the gas turbine engine;

a downstream rotor disk disposed downstream of the upstream rotor disk and configured for rotation about the engine centerline during operation of the gas turbine engine;

a downstream blade section connected to the downstream rotor disk such that the upstream blade section and the downstream blade section form an airfoil body, and wherein the downstream blade section is configured for rotation about a radial axis at an outer diameter of the downstream blade disk;

an actuator arm extending from an inner diameter end of the downstream blade section;

a bracket disposed about the engine centerline and for providing a stationary support with respect to rotation of the downstream rotor disk;

a stepper motor comprising;

a stator mounted to the bracket such that it circumscribes the centerline; and

a rotor configured for rotation about the downstream rotor disk; and

a harmonic drive system comprising;

a flexible gear mounted to the downstream rotor disk such that it rotates about the centerline with the downstream rotor disk; and

a rigid gear connected to the actuator arm and engaged with the flexible gear;

wherein the rotor acts as a drive input to the flexible gear to cause relative rotation of the rigid gear about the downstream rotor disk such that the rigid gear adjusts the position of the actuator arm to adjust position of the downstream blade section, thereby adjusting the camber of the airfoil body.

17. The variable camber rotor blade of claim 16 wherein the rotor further comprises:

a circular inner bore configured for rotation about the stator; and

an elliptical outer diameter for providing harmonic input to the flexible gear.

18. The variable camber rotor blade of claim 16 wherein the stepper motor comprises stepped engagements such that the rotor advances in incremental steps and such that the rotor can be locked at each incremental step.

19. The variable pitch camber rotor blade of claim 18 and further comprising a digital control device for providing electrical input to the stator such that the stepper motor is continuously operated to drive the rotor with rotation of the downstream rotor disk, or is intermittently operated to allow free rotation of the rotor with rotation of the downstream rotor disk.

20. The variable camber rotor blade of claim 16 and further comprising:

a pin extending through the downstream rotor disk;

a bore positioned at an inner diameter of the downstream blade section for receiving the pin such that the downstream blade section is rotatable about the pin; and

a radial retention system for restraining radial movement of the downstream blade section while allowing rotation of the downstream blade section about the radial axis.