Singular stator vane control

Patent metadata

Field	Value
Publication number	US-10288079-B2
Application number	US-201615194294-A
Country	US
Kind code	B2
Filing date	Jun 27, 2016
Priority date	Jun 27, 2016
Publication date	May 14, 2019
Grant date	May 14, 2019

Abstract

Systems and methods for controlling stators of a compressor of a gas turbine engine are provided. The stators and rotatable blades may be included in a stage of the compressor. The rotatable blades may be configured to rotate about an axial axis of the compressor, and each of the stators is rotatable about a corresponding vane axis that extends radially outward from the axial axis of the compressor. Electric motors may be coupled to the stators, where each of the electric motors is configured to individually rotate a corresponding one of the stators in the compressor. A motor controller may be configured to cause the electric motors to rotate the stators in unison or individually.

First claim

What is claimed is:

1. A system comprising:
a plurality of stators in a compressor for a gas turbine engine, the stators and a plurality of rotatable blades included in a stage of the compressor, the rotatable blades configured to rotate about an axis of the compressor, and each of the stators is rotatable about a corresponding vane axis that extends radially outward from the axis of the compressor;
a plurality of electric motors, each of the electric motors is configured to individually rotate a corresponding one of the stators in the compressor;
a motor controller configured to cause the electric motors to rotate the stators in unison; and
a plurality of resolvers corresponding to the stators, wherein the motor controller is further configured to cause one or more of the electric motors to rotate a corresponding one of the stators in a direction until a corresponding stop point is reached, wherein the corresponding stop point is a point at which the corresponding one of the stators is physically prevented from, or encounters resistance to, rotating further in the direction, wherein the motor controller is further configured to receive, from each of the resolvers, an indication of an angular position of the corresponding stop point in the direction the corresponding one of the stators was rotated, wherein the motor controller is further configured to determine an actual angular position of the corresponding one of the stators that corresponds to a target position of the corresponding one of the stators based on the indication of the angular position of the corresponding stop point in the direction the corresponding one of the stators was rotated.

2. The system of claim 1 further comprising a plurality of gear trains, wherein each of the electric motors is mechanically coupled to the corresponding one of the stators by a corresponding one of the gear trains.

3. The system of claim 1 , wherein the motor controller is configured to cause the electric motors to rotate in unison to a target angular position.

4. The system of claim 1 , wherein the motor controller is further configured to cause one or more of the electric motors to rotate one or more of the stators in the stage of the compressor in response to a detection of a stall event and/or a surge event.

5. The system of claim 1 , wherein the motor controller is further configured to cause the electric motors to rotate the stators in unison to a target position based on a compression level indicator.

6. An axial compressor for a gas turbine engine, the axial compressor comprising:
a plurality of blades configured to rotate about a rotation axis of the axial compressor;
a plurality of stators disposed in the axial compressor downstream from and adjacent to the blades, wherein the blades are configured to accelerate a fluid toward the stators when the blades rotate about the rotation axis, the stators are configured to redirect the fluid accelerated by the blades and to convert a circumferential component of the flow of the fluid into pressure, and wherein each of the stators is rotatable about a corresponding vane axis that extends radially outward from the rotation axis of the axial compressor;
a plurality of gear trains, each of the gear trains directly coupled to a corresponding one of the stators via a shaft positioned on the corresponding vane axis;
a plurality of electric motors, each of the electric motors directly coupled to a corresponding one of the gear trains, each of the electric motors configured to individually rotate the corresponding one of the stators via the corresponding one of the gear trains;
a motor controller; and
a plurality of resolvers corresponding to the stators, wherein the motor controller is further configured to cause one or more of the electric motors to rotate a corresponding one of the stators in a direction until a corresponding stop point is reached, wherein the corresponding stop point is a point at which the corresponding one of the stators is physically prevented from, or encounters resistance to, rotating further in the direction, wherein the motor controller is further configured to receive, from each of the resolvers, an indication of an angular position of the corresponding stop point in the direction the corresponding one of the stators was rotated, wherein the motor controller is further configured to determine an actual angular position of the corresponding one of the stators that corresponds to a target position of the corresponding one of the stators based on the indication of the angular position of the corresponding stop point in the direction the corresponding one of the stators was rotated.

7. The axial compressor of claim 6 further comprising a motor controller configured to cause the electric motors to rotate the stators in unison, the motor controller further configured to cause any of the electric motors to rotate the corresponding one of the stators independently from the other of the stators for calibration.

8. The axial compressor of claim 6 further comprising a plurality of motor controllers, each of the motor controllers configured to control a corresponding one of the electric motors, wherein a master motor controller is configured to cause the electric motors to rotate the stators in unison through communication with the motor controllers.

9. The axial compressor of claim 6 , wherein the stators are included in a single stage of the axial compressor.

10. The axial compressor of claim 6 , wherein the stators are included in a portion of a single stage of the axial compressor.

11. A method to control stators, the method comprising:
providing a plurality of stators in a compressor of a gas turbine engine and/or in a turbine of the gas turbine engine, each of the stators is rotatable about a corresponding vane axis that extends radially outward from a longitudinal axis of the compressor and/or the turbine;
providing a plurality of electric motors, each of the electric motors is configured to individually rotate a corresponding one of the stators in the compressor;
causing the electric motors to rotate the stators in unison during operation of the gas turbine engine thereby affecting power output by the gas turbine engine;
calibrating the stators by causing the electric motors to rotate the stators independently from each other in a direction until the stators reach corresponding stop points, receiving a plurality of indications of angular positions of the corresponding stop points from a plurality of resolvers; and
determining actual angular positions of the stators that correspond to target positions of the stators based on the indications of angular positions of the corresponding stop points.

12. The method of claim 11 further comprising:
receiving a plurality of pressure samples from pressure sensors located in a radial cross-sectional planar area of the gas turbine engine;
determine that the pressure samples a match condition of a rotating stall event located in the radial cross-sectional planar area of the gas turbine engine; and
correcting for the rotating stall event by causing one or more of the stators located at or adjacent to a location of the rotating stall event to rotate by activating one or more of the electric motors corresponding to the one or more of the stators.

13. The method of claim 11 further comprising:
receiving a plurality of pressure samples from pressure sensors located in the gas turbine engine;
determine that the pressure samples a match condition of a surge event located in a radial cross-sectional planar area of the gas turbine engine;
correcting for the surge event by causing one or more of the sta

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce North America Tech Inc

Inventors

• Skertic Richard J

Classifications

• F04D27/0246

  by varying geometry within the pumps, e.g. by adjusting vanes · CPC title

• F04D27/002 Primary

  by varying geometry within the pumps, e.g. by adjusting vanes · CPC title

• F04D29/321

  for axial flow compressors · CPC title

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title

• F01D17/162 Primary

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title