System and method for controlling stator assemblies

• US 7,927,067 B2
• Filed: 05/01/2007
• Issued: 04/19/2011
• Est. Priority Date: 05/01/2007
• 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: Wood, Coy Bruce, Chenard, Peter E., Rajamani, Ravi
• Primary Examiner(s): WIEHE, NATHANIEL EDWARD
• Application Number:
  US11/799,251
• Publication Number:
  US 20080273965A1
• Time in Patent Office: 1,449 Days
• Field of Search: 415/118, 415/148, 415/155, 415/159
• US Class Current: 415/118
• CPC Class Codes: F01D 17/02 Arrangement of sensing elements
• 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: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F04D 27/0246 by varying geometry within the pumps, e.g. by adjusting vanes
• CPC Class Codes: F04D 29/563 specially adapted for elastic fluid pumps

Abstract

A variable vane control system for use with a gas turbine engine includes a plurality of vanes, an actuation assembly, a mechanical linkage assembly, and a sensor. Each of the plurality of vanes has an airfoil portion disposed in a gas flowpath of the gas turbine engine, and a position of each of the vanes is adjustable with respect to an angle of attack of the airfoil portion of each vane. The actuation assembly is configured for generating actuation force to position the plurality of vanes. The mechanical linkage assembly operably connects the actuation assembly to at least one of the plurality of vanes. The sensor is configured to sense at least one of the position of the airfoil portions of the plurality of vanes and the mechanical linkage assembly, and to generate a position output signal.

Claims

1. A variable vane control system for use with a gas turbine engine, the system comprising:

a plurality of vanes each having an airfoil portion disposed in a gas flowpath of the gas turbine engine, wherein a position of each of the vanes is adjustable with respect to an angle of attack of the airfoil portion of each vane;

an actuation assembly for generating actuation force to position the plurality of vanes;

a mechanical linkage assembly for operably connecting the actuation assembly to at least one of the plurality of vanes; and

a sensor configured to directly sense the position of a trailing edge portion of the airfoil portion of a first of the plurality of vanes, and to generate a position output signal.

2. The system of claim 1 and further comprising:

control circuitry electrically connected to the sensor and to the actuation assembly, wherein the control circuitry commands the actuation assembly to adjust the positioning of at least one of the plurality of vanes as a function of the position output signal from the sensor.

3. The system of claim 1, wherein the sensor is of a type selected from the group consisting of:

optical sensors, microwave sensors, eddy current sensors and ultrasonic sensors.

4. The system of claim 2, wherein the control circuitry is configured to electronically store position output signals over time.

5. The system of claim 1 and further comprising:

diagnostic circuitry electrically connected to the sensor for generating a diagnostic output as a function of trends in position output signals gathered over time.

6. The system of claim 1 and further comprising:

a ground based processing unit operably connected to the sensor for generating a diagnostic output as a function of trends in position output signals gathered over time.

7. The system of claim 1, wherein the actuation assembly is configured to simultaneously adjust the positioning of each of the plurality of vanes operably connected to the linkage assembly.

8. The system of claim 7 and further comprising:

a linkage sensor, wherein the linkage sensor senses the position of the airfoil portions of the plurality of vanes indirectly by sensing the position of a portion of the linkage assembly to which at least one of the plurality of vanes is operably connected.

9. The system of claim 1, wherein the sensor is a non-contacting type sensor.

10. The system of claim 1, wherein the sensor is angled with respect to the gas flowpath.

11. A variable vane control system for use with a gas turbine engine, the system comprising:

a plurality of vanes each having an airfoil portion, wherein an angle of attack of the airfoil portion of each vane is adjustable such that a position of each vane is variable;

an actuation assembly for controlling the positioning of the plurality of vanes;

a linkage assembly for mechanically connecting the actuation assembly to the plurality of vanes; and

a sensor configured to sense the position of the airfoil portion of at least one of the plurality of vanes, and to generate a position output signal, wherein the sensor is configured to directly sense the position of a trailing edge portion of the airfoil portion of a first of the plurality of vanes; and

control circuitry electrically connected to the sensor and to the actuation assembly, wherein the control circuitry commands the actuation assembly to adjust the positioning of at least one of the plurality of vanes as a function of the position output signal from the sensor.

12. The system of claim 11, wherein the sensor is of a type selected from the group consisting of:

optical sensors, microwave sensors, eddy current sensors and ultrasonic sensors.

13. The system of claim 11, wherein the control circuitry is configured to electronically store position output signals over time.

14. The system of claim 11 and further comprising:

diagnostic circuitry electrically connected to the sensor for generating a diagnostic output as a function of trends in position output signals gathered over time.

15. The system of claim 11 and further comprising:

a ground based processing unit operably connected to the sensor for generating a diagnostic output as a function of trends in position output signals gathered over time.

16. The system of claim 11 and further comprising:

a linkage sensor, wherein the linkage sensor senses the position of the airfoil portions of the plurality of vanes indirectly by sensing the position of a portion of the linkage assembly to which at least one of the plurality of vanes is mechanically connected.

17. The system of claim 11, wherein the sensor is a non-contacting type sensor.

18. The system of claim 11, wherein the sensor is angled with respect to the trailing edge portion of the airfoil portion of a first of the plurality of vanes.

19. A method of controlling variable vane airfoil positioning in a gas turbine engine, the method comprising:

providing a position reference signal that identifies a desired position of a vane airfoil;

sensing an actual position of the vane airfoil as a function of a standoff distance measured between a sensor and a trailing edge portion of the vane airfoil;

generating an actual position signal;

comparing the position reference signal and the actual position signal; and

adjusting the actual position of the vane airfoil as a function of the comparison of the position reference signal and the actual position signal.